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LLC Submittal of NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report, TR-0918-60894, Revision 0
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Issue date:	12/07/2018
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LO-1218-63700 December 7, 2018 Docket No.52-048 U.S. Nuclear Regulatory Commission ATTN: Document Control Desk One White Flint North 11555 Rockville Pike Rockville, MD 20852-2738

SUBJECT:

NuScale Power, LLC Submittal of NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report, TR-0918-60894, Revision 0

REFERENCES:

1. NuScale Letter to the NRC, NuScale Power, LLC Submittal of the NuScale Standard Plant Design Certification Application, dated December 31, 2016

2. NuScale Power, LLC Submittal of Technical Report TR-0716-50439, NuScale Comprehensive Vibration Assessment Program, Revision 0, dated December 2016

3. NuScale Power, LLC Submittal of Technical Report TR-0716-50439, NuScale Comprehensive Vibration Assessment Program, Revision 1, dated January 2018 NuScale Power, LLC (NuScale) submitted a Design Certification Application (DCA) for its Integral Small Modular Reactor Design in Reference 1. Part 2 of Tier 2 of the DCA, NuScale Final Safety Analysis Report Section 3.9.2, Dynamic Testing and Analysis of Systems, Components, and Equipment, described the Comprehensive Vibration Assessment Program (CVAP). References 2 and 3 subsequently submitted details of the NuScale CVAP (Design Analysis) in technical report TR-0716-50439 Revision 0 and Revision 1. Section 6.0 of the CVAP Design Analysis technical report discusses the requirement for a followup separate CVAP Measurement and Inspection Plan technical report to define measurement and inspection plans for the prototype Category I NuScale Power Module.

The purpose of this letter is to provide the NuScale Technical Report NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report, TR-0918-60894, Revision 0. This technical report provides supplementary information, data and analyses for the NuScale CVAP. contains the proprietary version of the report entitled NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report. NuScale requests that the proprietary version be withheld from public disclosure in accordance with the requirements of 10 CFR § 2.390. The enclosed affidavit (Enclosure 3) supports this request. Enclosure 1 has also been determined to contain Export Controlled Information. This information must be protected from disclosure per the requirements of 10 CFR § 810. Enclosure 2 contains the nonproprietary version of the report entitled NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report.

NuScale Power, LLC 1100 NE Circle Blvd., Suite 200 Corvallis, Oregon 97330 Office 541.360-0500 Fax 541.207.3928 www.nuscalepower.com

LO-1218-60894 Page 2 of 2 12/7/18 This letter makes no regulatory commitments and no revisions to any existing regulatory commitments.

If you have any questions, please contact Marty Bryan at 541-452-7172 or at mbryan@nuscalepower.com.

Sincerely, Distribution: Samuel Lee, NRC, OWFN-8G94 Gregory Cranston, NRC, OWFN-8G94 Omid Tabatabai, NRC, OWFN-8G9A Marieliz Vera, NRC, OWFN-8G9A Enclosure 1: "NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report," TR-0918-60894-P, Revision 0, proprietary version Enclosure 2: "NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report," TR-0918-60894-NP, Revision 0, nonproprietary version Enclosure 3: Affidavit of Thomas A. Bergman, AF-1218-663701 NuScale Power, LLC 1100 NE Circle Blvd , Suite 200 Corvallis, Oregon 97330 Office 541.360-0500 Fax 541.207.3928 www.nuscalepower.com

LO-1218-63700 :

NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report, TR-0918-60894-P, Revision 0, proprietary version NuScale Power, LLC 1100 NE Circle Blvd., Suite 200 Corvallis, Oregon 97330 Office 541.360-0500 Fax 541.207.3928 www.nuscalepower.com

LO-1218-63700 :

NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report, TR-0918-60894-NP, Revision 0, nonproprietary version NuScale Power, LLC 1100 NE Circle Blvd., Suite 200 Corvallis, Oregon 97330 Office 541.360-0500 Fax 541.207.3928 www.nuscalepower.com

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report December 2018 Revision 0 Docket No.: 52-048 NuScale Power, LLC 1100 NE Circle Blvd., Suite 200 Corvallis, Oregon 97330 www.nuscalepower.com

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report COPYRIGHT NOTICE This report has been prepared by NuScale Power, LLC and bears a NuScale Power, LLC, copyright notice.

No right to disclose, use, or copy any of the information in this report, other than by the U.S. Nuclear Regulatory Commission (NRC), is authorized without the express, written permission of NuScale Power, LLC.

The NRC is permitted to make the number of copies of the information contained in this report that is necessary for its internal use in connection with generic and plant-specific reviews and approvals, as well as the issuance, denial, amendment, transfer, renewal, modification, suspension, revocation, or violation of a license, permit, order, or regulation subject to the requirements of 10 CFR 2.390 regarding restrictions on public disclosure to the extent such information has been identified as proprietary by NuScale Power, LLC, copyright protection notwithstanding. Regarding nonproprietary versions of these reports, the NRC is permitted to make the number of copies necessary for public viewing in appropriate docket files in public document rooms in Washington, DC, and elsewhere as may be required by NRC regulations. Copies made by the NRC must include this copyright notice and contain the proprietary marking if the original was identified as proprietary.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Department of Energy Acknowledgement and Disclaimer This material is based upon work supported by the Department of Energy under Award Number DE-NE0008820.

This report was prepared as an account of work sponsored by an agency of the United States Government. Neither the United States Government nor any agency thereof, nor any of their employees, makes any warranty, express or implied, or assumes any legal liability or responsibility for the accuracy, completeness, or usefulness of any information, apparatus, product, or process disclosed, or represents that its use would not infringe privately owned rights.

Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise does not necessarily constitute or imply its endorsement, recommendation, or favoring by the United States Government or any agency thereof. The views and opinions of authors expressed herein do not necessarily state or reflect those of the United States Government or any agency thereof.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report CONTENTS Abstract ....................................................................................................................................... 1 Executive Summary .................................................................................................................... 2 1.0 Introduction ..................................................................................................................... 3 1.1 Purpose ................................................................................................................. 3 1.2 Scope .................................................................................................................... 3 1.3 Abbreviations ......................................................................................................... 4 2.0 Background ..................................................................................................................... 8 2.1 Measurement Plan Overview ................................................................................ 8 3.0 Benchmark Testing ....................................................................................................... 10 3.1 Steam Generator Inlet Flow Restrictor Benchmark Testing ................................. 10 3.2 TF-1 Benchmark Testing for Turbulence ............................................................. 40 3.3 TF-2 Benchmark Testing for Turbulence ............................................................. 40 3.4 TF-2 Benchmark Testing for Fluid Elastic Instability ............................................ 41 3.5 TF-3 Build-out Modal Testing............................................................................... 73 4.0 Validation Methodology .............................................................................................. 105 4.1 Use of Test Data ................................................................................................ 105 4.2 Methodology ...................................................................................................... 105 4.3 Validation Approach and Uncertainty Analysis .................................................. 107 4.4 Evaluation Process ............................................................................................ 111 4.5 Evaluation Procedures ...................................................................................... 112 4.6 Experimental Bias Considerations..................................................................... 124 4.7 Expected Results and Validation Range of Experimental Results .................... 126 4.8 Summary ........................................................................................................... 128 5.0 Validation Tests ........................................................................................................... 129 5.1 TF-3 Validation Test ........................................................................................... 129 5.2 Decay Heat Removal System Steam Tee Validation Testing............................. 202 5.3 Steam Generator Inlet Flow Restrictor Validation Testing ................................. 220 6.0 Initial Startup Measurement Testing.......................................................................... 235 7.0 Inspection Program .................................................................................................... 236 7.1 Inspection Methodology .................................................................................... 236 7.2 Inspection Procedure ........................................................................................ 237

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report 7.3 Pre- and Post-Initial Startup Testing Inspection................................................. 237 8.0 Summary and Conclusions ........................................................................................ 244 9.0 References ................................................................................................................... 245 9.1 Referenced Documents ..................................................................................... 245 Appendix A. TF-3 Instrumentation Plan .............................................................................. 246 Appendix B. TF-2 FEI Spectral Plots by Test Series (0 - 300 Hz) ...................................... 255 Appendix C. TF-2 FEI Spectral Plots by Flow Rate (0 - 300 Hz) ........................................ 266 Appendix D. TF-2 FEI Spectral Plots by Test Series (0 - 1000 Hz) .................................... 279 Appendix E. TF-2 FEI Spectral Plots by Flow Rate (0 - 1000 Hz) ...................................... 290 Appendix F. TF-2 FEI Content within Frequency Ranges of Interest ............................... 303 Appendix G. TF-2 FEI Frequency-Specific Amplitudes versus Flow Rate ....................... 311 Appendix H. TF-3 Build-out Testing Frequency Response Function Calculations ......... 318 TABLES Table 1-1 Abbreviations ............................................................................................................ 4 Table 1-2 Definitions ................................................................................................................. 5 Table 2-1 Analysis program verification testing and inspections .............................................. 9 Table 3-1 Steam generator inlet flow restrictor design options ............................................... 14 Table 3-2 Average and maximum root mean square vibration results .................................... 19 Table 3-3 Reynolds similitude values...................................................................................... 38 Table 3-4 Steam generator tube displacements ..................................................................... 38 Table 3-5 Single tube model predicted significant frequencies ............................................... 44 Table 3-6 Placement of strain gauge instrumentation ............................................................. 50 Table 3-7 Test conditions and file names for fluid elastic instability data acquisition .............. 51 Table 3-8 Summary of applied processing parameters .......................................................... 56 Table 3-9 Dynamic root mean square strains measured during TF-2 fluid elastic instability tests ........................................................................................................................ 61 Table 3-10 Dynamic peak strains measured during TF-2 fluid elastic instability tests .............. 62 Table 3-11 Dynamic peak strains by test series (average and maximum) ............................... 63 Table 3-12 Dynamic peak strains by flow rate (average and maximum) .................................. 64 Table 3-13 Relative comparison of content within frequency ranges of interest (0-10 Hz inclusive), sorted by test series ............................................................................... 65 Table 3-14 Relative comparison of content within frequency ranges of interest (excludes 0-10 Hz), sorted by test series ................................................................................ 66 Table 3-15 Relative comparison of content within frequency ranges of interest (excludes 0-10 Hz), sorted by test series ................................................................................ 67 Table 3-16 Acquisition parameters for time and frequency domain .......................................... 76 Table 3-17 Group B, span C (5) accelerometers ...................................................................... 81 Table 3-18 Group C, multi-span ................................................................................................ 84 Table 3-19 Energy transfer across spans ................................................................................. 86 Table 3-20 End span (A and AD) frequency response function summary ................................ 88

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Table 3-21 Support and tube frequency response function summary ...................................... 91 Table 3-22 Frequency response function summary per group ............................................... 103 Table 4-1 Steam generator test model inputs ....................................................................... 113 Table 4-2 Steam generator tube inputs to vortex shedding margin calculation: method B ... 114 Table 4-3 Steam generator tube vortex shedding margin uncertainty method: method B .... 115 Table 4-4 Steam generator tube inputs to vortex shedding margin calculation: method A ... 116 Table 4-5 Steam generator tube vortex shedding margin uncertainty method: method A .... 116 Table 4-6 Fluid elastic instability analysis input parameter types ......................................... 118 Table 4-7 Steam generator tube inputs to fluid elastic instability safety margin calculation ............................................................................................................. 119 Table 4-8 Steam generator tube fluid elastic instability margin uncertainty method ............. 120 Table 4-9 Decay heat removal system steam pipe inputs to acoustic resonance margin calculation ............................................................................................................. 123 Table 4-10 Decay heat removal system steam pipe acoustic resonance margin uncertainty method .................................................................................................................. 124 Table 4-11 Summary of components and flow induced vibration analysis validation methods ................................................................................................................ 128 Table 5-1 Summary of tests .................................................................................................. 129 Table 5-2 Tube array design geometry ................................................................................. 131 Table 5-3 Helical steam generator tube array details ........................................................... 132 Table 5-4 TF-3 test facility operating conditions ................................................................... 132 Table 5-5 Instrumented tubes (accelerometers and strain gauges) ...................................... 134 Table 5-6 Instrumented tubes (accelerometers only) ............................................................ 134 Table 5-7 Instrumented tubes (strain gauges only) ............................................................... 135 Table 5-8 Accelerometers placement for instrumented tube #1 ........................................... 136 Table 5-9 Accelerometers placement for instrumented tube #2 ............................................ 136 Table 5-10 Accelerometers placement for instrumented tube #3 ............................................ 137 Table 5-11 Accelerometers placement for instrumented tube #4 ............................................ 137 Table 5-12 Accelerometers placement for instrumented tube #5 ............................................ 138 Table 5-13 Accelerometers placement for instrumented tube #6 ............................................ 138 Table 5-14 Tube strain gauge placements .............................................................................. 139 Table 5-15 Steam generator tube support accelerometer ...................................................... 139 Table 5-16 Other pressure and temperature instrumentation ................................................. 140 Table 5-17 Partial-tube array modal tests ............................................................................... 142 Table 5-18 Steady-state flow flow-induced vibration tests ...................................................... 147 Table 5-19 Vortex shedding test points1, 2 ............................................................................... 148 Table 5-20 Fluid elastic instability flow tests ........................................................................... 149 Table 5-21 Mass correction for vessels .................................................................................. 161 Table 5-22 Pivot vs. fixed dry modal results for Columns 9 and 13 in x-direction (horizontal) ............................................................................................................ 170 Table 5-23 Pivot vs. fixed dry modal results for Columns 9 and 13 in y-direction (vertical) .... 171 Table 5-24 Pivot vs. fixed dry modal results for Columns 9 and 13 in z-direction (horizontal) ............................................................................................................ 172 Table 5-25 Dry vs. wet modal results for pivot boundary conditions in y-direction ................. 177 Table 5-26 Dry vs. wet modal results for fixed boundary conditions in y-direction ................. 178 Table 5-27 Fine vs. coarse mesh modal results for pivot boundary conditions in x-direction ............................................................................................................. 180

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Table 5-28 Fine vs. coarse mesh modal results for pivot boundary conditions in y-direction ............................................................................................................. 181 Table 5-29 Fine vs. coarse mesh modal results for pivot boundary conditions in z-direction ............................................................................................................. 182 Table 5-30 Fine vs. coarse mesh modal results for fixed boundary conditions in x-direction ............................................................................................................. 183 Table 5-31 Fine vs. coarse mesh modal results for fixed boundary conditions in y-direction ............................................................................................................. 184 Table 5-32 Fine vs. coarse mesh modal results for fixed boundary conditions in z-direction ............................................................................................................. 185 Table 5-33 Top 5 participating modes in y-direction for Column 11 tubes............................... 186 Table 5-34 Summary of full bundle model results ................................................................... 192 Table 5-35 Measurements and sensors .................................................................................. 206 Table 5-36 Input and measurement uncertainties ................................................................... 218 Table 5-37 Expected and allowable results for acoustic resonance and second order shear layers .................................................................................................................... 219 Table 5-38 Range of possible radial clearances between inlet flow restrictor and tube wall ................................................................................................................ 223 Table 5-39 Range of flow conditions for steam generator inlet flow restrictor tests ................ 224 Table 5-40 SG IFR flow test matrix ......................................................................................... 232 Table 7-1 Pre- and post-initial startup testing inspection locations ....................................... 238 Table F-1 Amplitude of spectral content between 0 - 10 Hz ................................................. 304 Table F-2 Amplitude of spectral content between 0-10 Hz (excluding test series G) ............ 305 Table F-3 Amplitude of spectral content between 16-28 Hz ................................................. 306 Table F-4 Amplitude of spectral content between 35-55 Hz ................................................. 307 Table F-5 Amplitude of spectral content between 70-85 Hz ................................................. 308 Table F-6 Amplitude of spectral content between 140-160 Hz ............................................. 309 Table F-7 Amplitude of spectral content between 10-300 Hz ............................................... 310 Table H-1 Testing matrix ........................................................................................................ 319 FIGURES Figure 3-1 Center flow orifice restrictor design ......................................................................... 11 Figure 3-2 Threaded fastener design ....................................................................................... 12 Figure 3-3 Stepped solid annular design.................................................................................. 12 Figure 3-4 Steam generator inlet flow restrictor test facility schematic .................................... 16 Figure 3-5 Test assembly ......................................................................................................... 17 Figure 3-6 Device 1 root mean square acceleration at 110 percent Reynolds similitude and below....................................................................................................................... 20 Figure 3-7 Device 2 and 3 root mean square acceleration ...................................................... 21 Figure 3-8 Device 4-5 root mean square acceleration at 110 percent Reynolds similitude and below....................................................................................................................... 22 Figure 3-9 Device 6 root mean square acceleration at 110 percent Reynolds similitude and below....................................................................................................................... 23 Figure 3-10 Test 6C1 acceleration ............................................................................................. 23 Figure 3-11 Device 7-10 root mean square acceleration at 110 percent Reynolds similitude and below................................................................................................................ 24 Figure 3-12 Test 10C4 acceleration ........................................................................................... 25

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Figure 3-13 Device 11-12 root mean square acceleration at 110 percent Reynolds similitude and below................................................................................................................ 25 Figure 3-14 Test 1A4 (150 percent) acceleration ....................................................................... 29 Figure 3-15 Test 1A4 (150 percent) frequency ........................................................................... 29 Figure 3-16 Test 8A1 acceleration.............................................................................................. 30 Figure 3-17 Test 8A1 frequency ................................................................................................. 30 Figure 3-18 Test 8B2 Reynolds similitude of 100 percent acceleration ...................................... 31 Figure 3-19 Test 8B2 Reynolds similitude of 100 percent frequency ......................................... 31 Figure 3-20 Test 9A3 Reynolds similitude of 100 percent acceleration ...................................... 32 Figure 3-21 Test 9A3 Reynolds similitude of 100 percent frequency ......................................... 32 Figure 3-22 Test 9C3 acceleration ............................................................................................. 33 Figure 3-23 Test 9C3 frequency ................................................................................................. 33 Figure 3-24 Test 10A1 Reynolds similitude of 100 percent acceleration .................................... 34 Figure 3-25 Test 10A1 Reynolds similitude of 100 percent frequency ....................................... 34 Figure 3-26 Test 11C2 acceleration ............................................................................................ 35 Figure 3-27 Test 11C2 frequency ............................................................................................... 35 Figure 3-28 Test 12B1 acceleration............................................................................................ 36 Figure 3-29 Test 12B1 frequency ............................................................................................... 36 Figure 3-30 Steam generator tube displacement ....................................................................... 39 Figure 3-31 TF-2 Fluid-heated test section tubing column scheme ........................................... 42 Figure 3-32 TF-2 Tube support detail ......................................................................................... 43 Figure 3-33 TF-2 Column-5 mass participation by frequency .................................................... 45 Figure 3-34 TF-2 mode shape comparison for Column-5 (actual relative) ................................. 46 Figure 3-35 TF-2 mode shape comparison for Column-5 (weighted by mass participation) ...... 47 Figure 3-36 Placement of strain gauges on tube coils (typical) .................................................. 48 Figure 3-37 Placement of strain gauges on tube coils (S1101-1 and S1101-2 shown) .............. 49 Figure 3-38 Example of average variations in strain gauge signals ........................................... 55 Figure 3-39 Overall power spectral density content comparison - column-3, side strain gauges (top=S07, bottom=S05)........................................................................................... 60 Figure 3-40 Scatter plot of peak dynamic strain versus flow rate ............................................... 68 Figure 3-41 Spectral comparison, 0-50 Hz, datasets D5 versus G5, Column-3 sensors ........... 69 Figure 3-42 Spectral comparison, 0-50 Hz, datasets D6 versus G6, Column-5 sensors ........... 70 Figure 3-43 General layout of helical coil steam generator prototype for vibration testing ........ 75 Figure 3-44 Typical single, long span vertical; frequency response function (blue) and coherence (orange) ................................................................................................. 79 Figure 3-45 Frequency response function response for roving accelerometer along single span (mass loading) ........................................................................................................ 79 Figure 3-46 Lower frequency response (below 25 Hz); frequency response function (blue) and coherence (oOrange) .............................................................................................. 80 Figure 3-47 Coherence only for test 1C-1Z (horizontal/1Z and vertical/3Y direction) ................ 82 Figure 3-48 Impact location effects on Span C (left: mid-span; right: near end of span) ........... 82 Figure 3-49 Coherence only for test 2A-EfwZ (vertical and horizontal direction) ....................... 85 Figure 3-50 2A-EfwZ energy transfer across spans ................................................................... 87 Figure 3-51 Coherence only 5A-5Z (horizontal and vertical direction) ....................................... 89 Figure 3-52 Support/tube testing configuration .......................................................................... 90 Figure 3-53 Coherence for test Sup-103 + Col-12, Span E tub 1+5+9, impact 1-X................. 92 Figure 3-54 Global polynomial curve fit of frequency response functions (top frequency response function magnitude, bottom imaginary magnitude on log-scale) ............. 93

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Figure 3-55 Half-power damping estimations over all frequency response function groups ...... 94 Figure 3-56 Peak damping values (((2(a),(c):1C-1Y-left and (( }}2(a),(c):1A-3Z-right) ............................................................................. 94 Figure 3-57 Amplitude-dependent damping from three time histories (raw): exponential fit - blue; log dec - red............................................................................................ 96 Figure 3-58 Amplitude-dependent damping from three time histories (averaged): exponential fit - blue; log dec - red............................................................................................ 97 Figure 3-59 Amplitude-dependent damping from pull test: exponential fit - blue; log dec

               - red ........................................................................................................................ 98 Figure 3-60 Amplitude-dependent damping: pull pest - black and grey; impact tests - red and bue .......................................................................................................................... 98 Figure 3-61 1C-1Z, Span C, 5 accelerometers (frequency response function, axial-red, vertical-green, horizontal-blue) ............................................................................. 100 Figure 3-62 Mode shape for 1C-1Z at ((                                   }}2(a),(c) ........................................................ 100 Figure 3-63 Mode shape for 1C-1Z at ((                                }} 2(a),(c) ........................................................... 101 Figure 3-64 Mode shape for 1C-1Z at ((                                  }}2(a),(c) ......................................................... 101 Figure 3-65 Mode shape for 1C-1Z at ((                                  }}2(a),(c) ......................................................... 102 Figure 3-66 Comparison of mode shapes between 1C-1Z (((                                                 }}2(a),(c)) and 1A-5Z

((( }} 2(a),(c)) using modal assurance criteria ................................................ 102 Figure 5-1 Coordinate systems shown from global isometric view ........................................ 151 Figure 5-2 Numbering system for circumferential positions (CSYS 0 shown) ........................ 152 Figure 5-3 Representative tubes for individual tube models .................................................. 153 Figure 5-4 Boundary condition locations (column 13 shown) ................................................. 154 Figure 5-5 TF-3 full bundle model geometry .......................................................................... 156 Figure 5-6 TF-3 full bundle model mesh ................................................................................ 157 Figure 5-7 Tube and tube support mesh ................................................................................ 158 Figure 5-8 Modeled vessel mass (left), and top head mass volume (right) ............................ 160 Figure 5-9 Fixed boundary condition at bottom edge of full bundle model ............................. 162 Figure 5-10 Tube to tubesheet coupling: steam tubesheet (top), feedwater tubesheet (bottom)................................................................................................................. 163 Figure 5-11 Tube support to steam generator support coupling: upper connection (top), lower connection (bottom) .............................................................................................. 164 Figure 5-12 Tube to tube support coupling............................................................................... 165 Figure 5-13 Various views of tube support to tube support coupling ........................................ 166 Figure 5-14 Column 9 tube support to inner vessel coupling ................................................... 167 Figure 5-15 Column 13 tube support to outer vessel coupling ................................................. 168 Figure 5-16 Fundamental mode for Column 13 dry pivot case (breathing mode) .................... 173 Figure 5-17 Mode with highest y-direction (vertical) mass participation for Column 13 dry pivot case (beam mode) ................................................................................................ 174 Figure 5-18 Fundamental mode for Column 13 dry fixed case (beam mode of transition bend) ..................................................................................................................... 175 Figure 5-19 Mode with highest y-direction mass participation for Column 13 dry fixed case (beam mode)......................................................................................................... 176 Figure 5-20 Maximum strain intensity locations for Column 11, tube 1, pivot case, dominant vertical modes ....................................................................................................... 187 Figure 5-21 Maximum strain intensity locations for Column 11, tube 1, fixed case, dominant vertical modes ....................................................................................................... 188 © Copyright 2018 by NuScale Power, LLC ix

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Figure 5-22 Maximum strain intensity locations for Column 11, tube 16, pivot case, dominant vertical modes ....................................................................................................... 189 Figure 5-23 Maximum strain intensity locations for Column 11, tube 16, fixed case, dominant vertical modes ....................................................................................................... 190 Figure 5-24 Fundamental mode for full bundle pivot case (breathing mode) ........................... 193 Figure 5-25 Mode with highest x-direction mass participation for full bundle pivot case (rocking mode) .................................................................................................................... 194 Figure 5-26 Mode with highest y-direction mass participation for full bundle pivot case (tube beam mode) .......................................................................................................... 195 Figure 5-27 Entire specimen squeezing mode for full bundle fixed case ................................. 196 Figure 5-28 Tube fundamental mode for full bundle fixed case (beam mode of transition bend)

.............................................................................................................................. 197 Figure 5-29 Tube mode with highest y-direction mass participation for full bundle fixed case (tube beam mode)................................................................................................. 198 Figure 5-30 Twisting mode for full tube bundle fixed (no circ) case ......................................... 199 Figure 5-31 Containment system steam line 2 and decay heat removal system actuation valves .................................................................................................................... 204 Figure 5-32 Drawing of decay heat removal system junctions to containment system main steam pipe ............................................................................................................ 212 Figure 5-33 Steam generator tube inlet flow restrictor and mounting plate .............................. 221 Figure 5-34 Dimensions of inlet flow restrictor and flow restrictor bolt ..................................... 222 Figure 5-35 Preload conditions (not to scale)........................................................................... 231 Figure 7-1 Lower reactor pressure vessel comprehensive vibration assessment program inspection locations............................................................................................... 240 Figure 7-2 Upper reactor pressure vessel comprehensive vibration assessment program inspection locations............................................................................................... 241 Figure 7-3 Steam generator and downcomer comprehensive vibration assessment program inspection locations............................................................................................... 242 Figure 7-4 Steam line comprehensive vibration assessment program inspection locations ................................................................................................................ 243 Figure A-1 Column 11 tube 1 instrumented tube .................................................................... 246 Figure A-2 Column 11 tube 16 instrumented tube .................................................................. 247 Figure A-3 Column 9 tube 15 instrumented tube .................................................................... 248 Figure A-4 Column 9 tube 16 instrumented tube .................................................................... 249 Figure A-5 Column 12 tube 1 instrumented tube .................................................................... 250 Figure A-6 Column 12 tube 2 instrumented tube .................................................................... 251 Figure A-7 Column 11 tube 2 instrumented tube .................................................................... 252 Figure A-8 Column 11 tube 15 instrumented tube .................................................................. 253 Figure A-9 Instrumentation summary ..................................................................................... 254 Figure B-1 Test condition A, channel set 1 ............................................................................. 256 Figure B-2 Test condition A, channel set 2 ............................................................................. 257 Figure B-3 Test condition B, channel set 1 ............................................................................. 258 Figure B-4 Test condition B, channel set 2 ............................................................................. 259 Figure B-5 Test condition C, channel set 1 ............................................................................. 260 Figure B-6 Test condition C, channel set 2 ............................................................................. 261 Figure B-7 Test condition D, channel set 1 ............................................................................. 262 Figure B-8 Test condition D, channel set 2 ............................................................................. 263

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Figure B-9 Test condition G, channel set 1 ............................................................................. 264 Figure B-10 Test condition G, channel set 2 ............................................................................. 265 Figure C-1 Nominal primary-side flow rate of 114 kg/s, channel set 1 .................................... 267 Figure C-2 Nominal primary-side flow rate of 114 kg/s, channel set 2 .................................... 268 Figure C-3 Nominal primary-side flow rate of 143 kg/s, channel set 1 ................................... 269 Figure C-4 Nominal primary-side flow rate of 143 kg/s, channel set 2 ................................... 270 Figure C-5 Nominal primary-side flow rate of 173 kg/s, channel set 1 ................................... 271 Figure C-6 Nominal primary-side flow rate of 173 kg/s, channel set 2 ................................... 272 Figure C-7 Nominal primary-side flow rate of 201 kg/s, channel set 1 ................................... 273 Figure C-8 Nominal primary-side flow rate of 201 kg/s, channel set 2 ................................... 274 Figure C-9 Nominal primary-side flow rate of 230 kg/s, channel set 1 ................................... 275 Figure C-10 Nominal primary-side flow rate of 230 kg/s, channel set 2 ................................... 276 Figure C-11 Nominal primary-side flow rate of 263 kg/s, channel set 1 ................................... 277 Figure C-12 Nominal primary-side flow rate of 263 kg/s, channel set 2 ................................... 278 Figure D-1 Test condition A, channel set 1 ............................................................................. 280 Figure D-2 Test condition A, channel set 2 ............................................................................. 281 Figure D-3 Test condition B, channel set 1 ............................................................................. 282 Figure D-4 Test condition B, channel set 2 ............................................................................. 283 Figure D-5 Test condition C, channel set 1 ............................................................................. 284 Figure D-6 Test condition C, channel set 2 ............................................................................. 285 Figure D-7 Test condition D, channel set 1 ............................................................................. 286 Figure D-8 Test condition D, channel set 2 ............................................................................. 287 Figure D-9 Test condition G, channel set 1 ............................................................................. 288 Figure D-10 Test condition G, channel set 2 ............................................................................. 289 Figure E-1 Nominal primary-side flow rate of 114 kg/s, channel set 1 .................................... 291 Figure E-2 Nominal primary-side flow rate of 114 kg/s, channel set 2 .................................... 292 Figure E-3 Nominal primary-side flow rate of 143 kg/s, channel set 1 ................................... 293 Figure E-4 Nominal primary-side flow rate of 143 kg/s, channel set 2 ................................... 294 Figure E-5 Nominal primary-side flow rate of 173 kg/s, channel set 1 ................................... 295 Figure E-6 Nominal primary-side flow rate of 173 kg/s, channel set 2 ................................... 296 Figure E-7 Nominal primary-side flow rate of 201 kg/s, channel set 1 ................................... 297 Figure E-8 Nominal primary-side flow rate of 201 kg/s, channel set 2 ................................... 298 Figure E-9 Nominal primary-side flow rate of 230 kg/s, channel set 1 ................................... 299 Figure E-10 Nominal primary-side flow rate of 230 kg/s, channel set 2 ................................... 300 Figure E-11 Nominal primary-side flow rate of 260 kg/s, channel set 1 ................................... 301 Figure E-12 Nominal primary-side flow rate of 260 kg/s, channel set 2 ................................... 302 Figure G-1 Dynamic strain, 0-10 Hz versus flow rate ............................................................. 312 Figure G-2 Dynamic strain, 16-28 Hz versus flow rate ........................................................... 313 Figure G-3 Dynamic strain, 35-55 Hz versus flow rate ........................................................... 314 Figure G-4 Dynamic strain, 70-85 Hz versus flow rate ........................................................... 315 Figure G-5 Dynamic strain, 140-160 Hz versus flow rate ....................................................... 316 Figure G-6 Dynamic strain, 10-300 Hz versus flow rate ......................................................... 317 Figure H-1 315-12-1-C-5 (5y) ................................................................................................. 320 Figure H-2 zSgle tube 1sec .................................................................................................... 320 Figure H-3 1A-1Y .................................................................................................................... 321 Figure H-4 1A-1Z .................................................................................................................... 321 Figure H-5 1A-3Z .................................................................................................................... 322 Figure H-6 1A-5Z .................................................................................................................... 322 © Copyright 2018 by NuScale Power, LLC xi

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Licensing Technical Report Figure H-7 1C-1Y .................................................................................................................... 323 Figure H-8 1C-1Z .................................................................................................................... 323 Figure H-9 1C-5Z .................................................................................................................... 324 Figure H-10 1E-1Y .................................................................................................................... 324 Figure H-11 1E-1Z .................................................................................................................... 325 Figure H-12 1E-5Z .................................................................................................................... 325 Figure H-13 2A-CmsZ ............................................................................................................... 326 Figure H-14 2A-EfwZ ................................................................................................................ 326 Figure H-15 2A-EmsZ ............................................................................................................... 327 Figure H-16 2A-GfwZ ................................................................................................................ 327 Figure H-17 2C-CmsZ............................................................................................................... 328 Figure H-18 2C-EfwZ ................................................................................................................ 328 Figure H-19 2C-EmsZ ............................................................................................................... 329 Figure H-20 2C-GfwZ ................................................................................................................ 329 Figure H-21 3C-EmsZ ............................................................................................................... 330 Figure H-22 4A-2Z .................................................................................................................... 331 Figure H-23 4A-3Z .................................................................................................................... 331 Figure H-24 5A-2Z .................................................................................................................... 332 Figure H-25 5A-4Y .................................................................................................................... 332 Figure H-26 5A-5Z .................................................................................................................... 333 Figure H-27 5A-Support Z......................................................................................................... 333 Figure H-28 Sup-103+col-12 span E, Tube 1, 5, 9 impact 1x ................................................... 334 Figure H-29 Sup-103+col-12 span E, Tube 1, 5, 9 impact 1Z................................................... 334 Figure H-30 Supp-to-tube 103 span-E FW-X ............................................................................ 335 Figure H-31 Supp-to-tube 103 span-E FW-X on plate .............................................................. 335 © Copyright 2018 by NuScale Power, LLC xii

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Abstract The NuScale Comprehensive Vibration Assessment Program (CVAP) includes the requirement for individual analytical, measurement, and inspection programs. The NuScale CVAP design analysis program is documented in the NuScale Comprehensive Vibration Assessment Program Technical Report, TR-0716-50439 (Reference 9.1.4). In accordance with Regulatory Guide 1.20, the results of the analysis program serve as the basis for the choice of components and areas to be monitored in the measurement and inspection programs, in order to validate the implementation of the CVAP design analysis program. This technical report provides the details associated with the CVAP measurement and inspection program plans. © Copyright 2018 by NuScale Power, LLC 1

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Executive Summary This report provides the details of the NuScale Comprehensive Vibration Assessment Program (CVAP) measurement and inspection programs. These programs consist of benchmark testing and analysis, validation analysis and testing, an instrumentation plan to detect large amplitude vibration during initial startup testing, and inspection of components screened as susceptible to flow induced vibration (FIV) before and after initial startup testing. This report provides pre-test prediction results for CVAP testing of the NuScale Power Module (NPM) components that have design analyses and are part of the measurement program. The primary goal of the testing is to validate that detrimental effects do not occur during limiting operating conditions. Following the completion of each test, post-test analyses are performed to complete the validation effort. Assessments are also performed based on the initial startup testing and inspection observations. Combined with the benchmarking efforts, the measurement and inspection work scope validates the FIV screening and predictive analyses in the NuScale Comprehensive Vibration Assessment Program Technical Report, TR-0716-50439. © Copyright 2018 by NuScale Power, LLC 2

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 1.0 Introduction 1.1 Purpose The purpose of this technical report is to describe the scope of the NuScale Comprehensive Vibration Assessment Program (CVAP) measurement and inspection programs. This report explains the basis for the components assessed in these programs, the details associated with the planned testing and inspections, and how the results are used to validate the CVAP design analysis program. This report demonstrates how the measurements are used to confirm the adequacy of the design analysis, including the predicted safety margins. 1.2 Scope The NuScale CVAP addresses components exposed to primary or secondary coolant flow in the NuScale Power Module (NPM) through the design analysis and measurement and inspection programs. The scope of this report is the measurement and inspection programs. The measurement program consists of two components. The first is benchmarking the design analysis using test data that is not fully prototypic, but is applicable to susceptible components and aspects of the design analysis and overall validation approach. The second component of the measurement program is prototypic validation testing. This testing is informed from the design analysis and for components with the lowest predicted safety margins. Validation testing is performed either at specially designed test facilities, to permit higher quality and quantity collection of test data, and the ability to operate above licensing basis limits where the onset of strongly-coupled flow induced vibration (FIV) phenomena is predicted to occur, or on the first NPM during initial startup testing. The inspection program includes components that meet the screening criteria for any FIV mechanism. Details associated with the testing scope, extent of inspections, and inspection acceptance criteria are provided in this report. An outline and description of the scope of this report are provided below:

Benchmarking Testing: benchmarking testing was performed for the steam generator inlet flow restrictor (SG IFR), and to assess turbulence and fluid elastic instability (FEI) for the SG tube bundle in the TF-1 and TF-2 test programs. The benchmark test data was used to justify aspects of the design analysis and provide confidence that the validation testing is sufficient to validate the conclusions of the design analysis program.
Validation Methodology: the validation methodology provides a framework for selecting the aspects of the design analysis program that need to be validated, and to establish or confirm that the experiment design provides sufficient data to validate the

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 necessary aspects of the design analysis program. Pre-test prediction calculations implement the validation methodology. These calculations confirm the adequacy of the experimental scope, identify optimal test conditions and locations for sensors, and determine a range of expected and allowable experimental results, considering uncertainties and biases, that validate the design analysis.

Validation Testing: this section discusses the test design for three validation tests:

TF-3, steam generator inlet flow restrictor (SG IFR) and the decay heat removal system (DHRS). Testing details including the test geometry, testing conditions, test matrix, and sensor types and locations are identified. Pre-test predictions based on the experimental design assess applicable uncertainties and biases, and provide the range of expected and allowable experimental results that validate the design analysis.

Measurements during Initial Startup Testing: this section identifies sensors that are temporarily installed during initial startup testing to monitor for large amplitude vibrations. The monitoring locations include the SG, in-core instrument guide tubes (ICIGTs) and control rod drive (CRD) shafts in the upper plenum region, and the connection of the upper and lower riser assemblies.
Inspections: the NuScale CVAP requires inspection of each NPM component that screens for an FIV mechanism. This report provides details related to the inspection procedures and inspection locations, features, examination methods, and acceptance criteria.

1.3 Abbreviations Table 1-1 Abbreviations Term Definition APDL ANSYS parametric design language AR acoustic resonance ASME American Society of Mechanical Engineers CNTS containment system CRD Control rod drive CSYS coordinate system CVAP Comprehensive Vibration Assessment Program DAS data acquisition system DC Average DHRS decay heat removal system DSA dynamic signal analysis FEI fluid elastic instability FFT fast Fourier transform FIV flow-induced vibration FRF frequency response function FW feedwater HCSG helical coil steam generator ICIGT in-core instrument guide tubes © Copyright 2018 by NuScale Power, LLC 4

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Term Definition IFR inlet flow restrictor LFI leakage flow instability LHS Latin hypercube sampling MAC modal acceptance crtieria MS main steam MSIV main steam isolation valve MSS main steam system NPM NuScale Power Module OD outer diameter OM Operations and Maintenance PSD power spectral density RMS root mean square RPV reactor pressure vessel ROTY rotation in Y direction ROTZ rotation in Z direction SIET Sperimentiamo le Tue Idee SG steam generator TB turbulent buffeting TEEAR test equipment error and accuracy report UX displacement in X direction UY displacement in Y direction UZ displacement in Z direction VS vortex shedding VT visual test Table 1-2 Definitions Term Definition Acoustic resonance A phenomenon where an acoustic wave is generated at a frequency that coincides with the natural frequency of a confining structure. Bias In design analysis, bias is the difference between a best estimate and conservative parameter. In an experiment, bias is another term for a test distortion, i.e., a feature of the test that is different from the design analysis condition. Confidence Interval The probability that the true value lies within the specified limits. Critical instrument An instrument whose proper function is required in order to accomplish the objectives of the test campaign. dry tube Refers to a tube exposed to air (not submerged in liquid). It is understood that for theTF-3 testing described in this document the inside of the tubes is dry; liquid is excluded from the inside of the tubes. Expanded Uncertainty An estimate of the plus-or-minus limits of total error, with a defined level of confidence (usually 95%). Fatigue Usage Factor Ratio of the number of vibration cycles anticipated during the lifetime of the component to the allowable cycles. © Copyright 2018 by NuScale Power, LLC 5

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Term Definition Gap or Pitch Velocity (Vgap) Local velocity to which tubes are subject to, for flow in a closely pack tube array. This velocity is developed based on the overall flow area blocked by tubes (and supports as applicable). For example, when half of the available flow area is blocked by tubes/supports, the gap velocity would be 2 times the approach velocity. General visual Method: This level of inspection is made with direct, assisted, or remote visual methods. A mirror may be used to enhance visual access to exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels. Stands, ladders or platforms may be required to gain proximity to the area being checked. Criteria: A visual examination of an interior or exterior area, installation, or assembly to detect general mechanical and structural condition of components and their supports, and to detect surface discontinuities and imperfections. General mechanical and structural condition of components is verified by parameters such as clearances, settings, and physical displacements. Abnormally positioned components, such as misalignment of supports or a pipe outside a pipe hanger, are noted for closer examination. The inspection includes an observation of the condition of the material surfaces, including welds, within the inspection area to detect surface discontinuities and imperfections, such as a loss of integrity at bolted or welded connections, loose or missing parts, debris, cracks, corrosion, erosion, discoloration, and geometric discontinuities, such as gouges, chips, or dents. Long span Based on arrangement of the SG tube supports in the NuScale design, lengths of helical tubing that span beneath each steam plenum are 64 degree arcs. These lengths of tubing are generically referred to as long spans. Lower riser section Reactor internal components from the upper core plate to the upper riser section. Monte Carlo Monte Carlo simulations provide statistical results to problems by performing repeated calculations with randomized input variables, and analyzing the trends in the output data. Pre-Test Analysis The effort to model the test apparatus and assess input, numerical, and measurement uncertainties to inform the expected range of experimental results suitable for validation. Propagation of Uncertainty A test, for example, may report measured values for density () and velocity (V), in addition to their respective uncertainties. A validation analysis calculates dynamic pressure (1 2 ), so its uncertainty must be estimated by propagating the uncertainty of density and velocity. Reflector block The reflector sits inside the core barrel and is made of sections referred to as reflector blocks. Sensitivity coefficient The instantaneous rate of change in the result due to a change in a parameter. © Copyright 2018 by NuScale Power, LLC 6

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Term Definition Short span Based on arrangement of the SG tube supports in the NuScale design, lengths of helical tubing that span between each steam plenum are only 26-degree arcs. These lengths of tubing are generically referred to as short spans. SG plenum There are eight SG plenums (four steam and four feedwater (FW). The plenums contain the SG tube sheets. S-N Curve Plot of stress (S) against the number of cycles to fatigue failure (N), sometimes called endurance limit. Standard uncertainty For a dispersion of values about a mean value, the standard uncertainty is the estimated standard deviation. Strouhal number A dimensionless frequency associated with vortex shedding (VS). TF-1 Test facility designed to study the effects of secondary side boiling in HCSG tubes. Dynamic pressure measurements collected during flow testing. TF-2 Test facility designed to study primary and secondary flows in HCSG tubes, and heat transfer. Strain gauge measurements were collected during flow testing. TF-3 Test facility design to study fluid elastic instability, VS, and turbulence due to primary side flow in HCSG tubes. Testing consists of modal testing in air and in water, and primary side flow testing with extensive instrumentation to detect vibration. Tube light or heavy In reference to the mass of the tube, a light case implies the inside of the tube is filled with steam and the added mass on the primary side has a water density based on hot RCS temperature conditions. A heavy case implies the inside of the tube is filled with FW and the exterior fluid is at a cold RCS temperature. Uncertainty Relating to the presence of an unknown error in a measured quantity or a model calculation. Upper riser section Reactor vessel internals (RVI) components from the lower riser section to the top of the riser. Validation The process of determining the degree to which a model is an accurate representation of the real world from the perspective of the intended uses of the model. wet tube Refers to a tube submerged in liquid. It is understood that for the TF-3 testing described in this document the inside of the tubes are dry; liquid is excluded from the inside of the tubes. The frequency of a wet tube is shifted from the frequency of a dry tube based on consideration of the effect of the surrounding fluid displaced. © Copyright 2018 by NuScale Power, LLC 7

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 2.0 Background This report describes the scope of the NuScale CVAP measurement and inspection programs. The following sections provide an overview of the components that require testing to validate the design analysis, per the NuScale Comprehensive Vibration Assessment Program Technical Report, TR-0716-50439 (Reference 9.1.4). The methodology used to account for uncertainty and bias to demonstrate the test design meets validation objectives is described. Additionally, existing benchmark testing is used to supplement the measurement program validation of the design analysis. 2.1 Measurement Plan Overview The analysis program includes a list of FIV phenomena and a list of components that could be subjected to these phenomena. Due to the low primary coolant flow rates and passive safety designs, many regions of the NPM are not susceptible to FIV and do not meet FIV screening criteria. For NPM components or structures that meet the screening criteria for a phenomenon, analysis is performed to confirm whether the structure or component is susceptible to the FIV phenomena. For the NPM components that are evaluated for turbulent buffeting (TB), the vibrational amplitude and stresses are determined. For phenomena with the exception of TB, the FIV mechanisms are characteristic of a strong fluid-structure coupling system. The NPM components are designed with sufficient margin of safety to the potential onset of these FIV phenomena. Turbulent buffeting occurs when a component is subject to turbulent flow, which is the dominant flow condition of the primary and secondary coolant. For TB, the fluid-structure coupling is weak and results in low amplitudes of vibration. Provided the impact stresses and fatigue usage are not detrimental to the component or structure over the design life, the acceptance criteria for this source of flow excitation are met. Per Section 2.2 of Regulatory Guide 1.20 (Reference 9.1.5), the purpose of the measurement program is: to verify the structural integrity of the reactor internals, determine the margin of safety associated with steady-state and anticipated transient conditions for normal operation, and confirm the results of the vibration analysis. The results of the measurement program are used to validate FIV analysis inputs, results, and the margins of safety. Due to the first-of-a-kind (prototype) NPM design, component screening analysis errs on the side of including potentially susceptible components, even when they could be excluded based on engineering judgment or precedent. This is an approach that minimizes the risk of failing to analyze a significant component. Compared to the existing pressurized water reactor and boiling water reactor designs, the natural circulation design of the NPM is inherently less susceptible to FIV due to the lower primary coolant velocities. Based on these factors, FIV analysis results demonstrate that many components have large margins of safety. The margin of safety is the means by which structural integrity is assured. Therefore, when a margin of safety is sufficiently large, validation by testing is not necessary. The scope of the measurement program is determined based on the results of the analysis program, as summarized in Table 2-1. © Copyright 2018 by NuScale Power, LLC 8

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 2-1 Analysis program verification testing and inspections Mechanisms with Prototype Testing Susceptible less than 100% Component Mechanisms Safety Margin Test Facility Initial Startup DHRS steam piping DHRS steam piping AR AR - testing SG helical tubing FEI, VS, TB FEI, VS, TB TF-3 testing - SG tube inlet flow LFI, TB LFI SG IFR testing - restrictors

Where, AR = acoustic resonance, DHRS = decay heat removal system, SG= steam generator, FEI = fluid elastic instability, VS = vortex shedding, and LFI = leakage flow instability.

Each prototype test used to validate a safety margin less than 100 percent considers applicable uncertainties and biases in the pre-test prediction to ensure that the test design meets the objective of validating the design analysis safety margin. © Copyright 2018 by NuScale Power, LLC 9

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.0 Benchmark Testing In the NuScale CVAP, benchmark testing is used to justify important aspects of the design analysis. Benchmarking supplements literature and industry accepted methods to provide confidence that the measurements taken during the validation program do not produce unanticipated results requiring modifications to the design analysis methods. Four sets of test data are used for benchmarking: TF-1, TF-2, SG IFR testing, and TF-3 Build-out modal testing. 3.1 Steam Generator Inlet Flow Restrictor Benchmark Testing The SG IFR is designed to provide a pressure loss at the entrance of each SG tube. The pressure loss is necessary to prevent density wave oscillations from forming in the SG tubes, which could result in undesirable steam outlet conditions and thermal fatigue. The primary design parameter associated with the SG IFR is the hydraulic performance of the device, specifically the loss coefficient. Other significant considerations for the component design include manufacturability, ease of removal for inspection of SG tubes, and vibration performance. The purpose of this test was to inform the design of the SG IFR component. The SG IFR is considered susceptible to leakage FIV and TB. The SG IFR is the only reactor module component that is susceptible to leakage FIV. As such, analytical predictions are not performed for this mechanism as a part of the CVAP design analysis program. Instead, acceptable performance is demonstrated with testing. Design analysis is performed for turbulence. Testing to support the CVAP is planned for leakage flow. The preliminary testing discussed herein provides confidence that future testing of the final SG IFR design will demonstrate acceptable FIV performance. This section summarizes the preliminary designs that were tested and the outcome of the testing. The test data was evaluated to determine when vibration was present. Spectral analysis of the acceleration data was performed to characterize the frequency of the vibration for tests in which vibration was higher than expected. Additionally, this report compares similar designs tested to the final SG IFR design and provides recommendations to be considered for the CVAP SG IFR testing to provide improved vibration data. 3.1.1 Steam Generator Inlet Flow Restrictor Design Options Tested Three different restrictor design options were tested: a center flow orifice restrictor, annular flow orifice restrictors, and annular flow stepped restrictors. Figure 3-1 shows the center orifice design, which does not insert inside of the SG tube. Figure 3-2 shows the threaded design and Figure 3-3 shows the stepped design. The center flow orifice restrictor design consists of individual orifice inserts that are mounted on a plate upstream of each tube inlet and seated at each tube inlet. The flow travels through the center of the restrictor directly into the tube. For this design, there is potential for bypass flow to occur where the restrictor is seated on the SG tube. This region © Copyright 2018 by NuScale Power, LLC 10

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 represents a narrow, annular flow path and at higher bypass flow rates could, produce a sufficient differential pressure to generate leakage flow instability (LFI). The annular designs are inserted in the tube and achieve the pressure loss through the reduced flow area they generate. The two annular flow restrictors are threaded and stepped designs. The threaded design is essentially a bolt. The desired form loss is achieved by specifying a thread diameter and insertion length. Of the designs tested, this arrangement has the least susceptibility to LFI because the restrictor is the most rigid [shorter insertion length and larger average outer diameter (OD)] and does not produce a diverging flow path. The stepped design consists of a solid rod with a series of stepped cylinders along the length. The desired loss coefficient is obtained by varying the total number of stepped sections inserted into the tube, the step OD, and the spacing between steps. Designs that provide two to five steps inserted were tested. Two different step ODs (0.510 and 0.515 inches) and two different step spacing values (0.50 inch and 0.75 inch) were investigated. ((

                                                                                                      }}2(a),(c),ECI Figure 3-1      Center flow orifice restrictor design

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                      }}2(a),(c),ECI Figure 3-2      Threaded fastener design

((

                                                                                                      }}2(a),(c),ECI Figure 3-3      Stepped solid annular design

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The SG tube inner diameter in the test is (( }}2(a),(c),ECI inch for the first (( }}2(a),(c),ECI inches to simulate the inner diameter of the portion of the tube that is hydraulically expanded in the FW plenum tubesheet. The tubesheet length is shorter in the test design compared to the final design. This does not affect the hydraulic performance or vibration of the restrictor device. It does affect the measured accelerations since a portion of the tube containing the restrictor is unsupported due to the shorter tubesheet length compared to the final design. Stainless steel type 304 is used in lieu of Alloy 690. An accelerometer was installed on the outside of the tube during testing to allow collection of vibration test results. The accelerometer was affixed to the tube with a threaded hex nut, located approximately 1.75 inches from the mounting plate. This location is adjacent to the inserted flow restrictor. The location of the accelerometer is shown in Figure 3-5. For the threaded and stepped designs, a range of insertion lengths were tested to meet thermal hydraulic test needs. Results show the effect of insertion length and pressure drop on vibration for these designs. Table 3-1 provides a description of the tested devices. The measured loss coefficients are provided to indicate the relative pressure loss each device provides. © Copyright 2018 by NuScale Power, LLC 13

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-1 Steam generator inlet flow restrictor design options Device Measured Loss Nominal Length Nominal Inner Device Type Number Coefficient (inch) Diameter (inch) Center orifice 1 (( }}2(a),(c),ECI Insertion Length Thread Type (inch) Threaded 2 (( }}2(a),(c),ECI ASME B1.1-2003 fastener 3 (( }}2(a),(c),ECI 1/2-13 UNC-2A Insertion Length Step Spacing & (inch) Outer Diameter 4 ((

                                                                                                     }}2(a),(c),ECI 5               ((
                                                                                                     }}2(a),(c),ECI 6               ((
                                                                                                     }}2(a),(c),ECI 7               ((
                                                                                                     }}2(a),(c),ECI Stepped annular        8               ((
                                                                                                     }}2(a),(c),ECI 9               ((
                                                                                                     }}2(a),(c),ECI 10              ((
                                                                                                     }}2(a),(c),ECI 11              ((
                                                                                                     }}2(a),(c),ECI 12              ((
                                                                                                     }}2(a),(c),ECI 3.1.1.1 Comparison of Preliminary Designs Tested to Final Design The final SG IFR design is a five-step design, with a step OD of ((                        }}2(a),(c),ECI inches, and steps that are ((                }}2(a),(c),ECI inches long and spaced ((               }}2(a),(c),ECI inches apart. Including the alignment cone, the insertion length is ((                           }}2(a),(c),ECI inches.

Device 6 is the most similar to the final design, because it is a stepped design with the same number of steps and the most similar insertion length and step dimensions. The differences between Device 6 and the final SG IFR design are summarized below. The distance between steps and the step length in the SG IFR design is (( }}2(a),(c),ECI inches. In the test configuration, a step spacing of (( }}2(a),(c),ECI inches was used for tests 4-10 and (( }}2(a),(c),ECI inches was used for tests 11-12. While these dimensions bound the dimension of the final design, no device provided the exact step spacing. The test design provided a step length of (( }}2(a),(c),ECI inches, which is less than the final design of (( }} 2(a),(c),ECI inches. © Copyright 2018 by NuScale Power, LLC 14

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Similar dimensional differences in the length and diameter of the alignment cone (located at the end of the flow restrictor) also exist. In the tested design, the alignment cone length is (( }}2(a),(c),ECI inches and the end width is (( }}2(a),(c),ECI inches. In the final design the length is (( }}2(a),(c),ECI inches and the end width is (( }}2(a),(c),ECI inches. The minor dimensional differences in the alignment cone are relevant for leakage FIV because the alignment cone provides a diverging flow path, which has been shown to increase the susceptibility of a component to leakage FIV. Lastly, there are construction differences. In the final design, the flow restrictor consists of a bolt with a threaded alignment cone that attaches to the end. The stepped flow restrictor has an inner diameter (( }}2(a),(c),ECI inches larger than the OD of the bolt. It is held in place by compression provided by the mounting plate and the washer and hex head nut. In the tested configuration, the flow restrictor assembly is a single, solid element. In the final design, the compression provided by the nut and the gap between the bolt and flow restrictor could introduce operational biases and uncertainties that are investigated to ensure they do not affect vibration for a bounding range of compression and alignment conditions. 3.1.1.2 Steam Generator Inlet Flow Restrictor Test Conditions The tests are performed at a nominal ambient temperature of 70 degrees Fahrenheit, and a range of 60 degrees Fahrenheit to 120 degrees Fahrenheit is allowed. Each test is run with a fixed FW inlet pressure that is nominally 100 psia, with an allowed range of 80 to 150 psia. Steady-state test conditions are established for five minutes before starting the test. During the test, fluid conditions are controlled to +/-1 percent of the target pressure, +/-2 degrees Fahrenheit for temperature and +/-2 percent of the target flow rate. A total of 15 restrictors were manufactured and tested. This value is based on three restrictors for each device type, including the different step spacing and OD for the step design. Testing three different copies of the nominally identical restrictor quantifies the effect of differences due to manufacturing tolerances and fit-up on the flow testing results. Tests were conducted in one of the four FW plenum assemblies. The four assemblies are provided for efficiency because each time a restrictor is replaced, the test loop needs to be drained. The test identification value is based on the device number (Table 3-1), the device copy (A, B, C), and the plenum number (1-4). Tests were performed at flow rates that provided Reynolds similitude of approximately 1 percent, 15 percent, 50 percent, 90 percent, 100 percent and 110 percent. Cavitation checks were also performed for select devices at the highest Reynolds flow condition by increasing the inlet pressure. Misalignment tests were also performed for Devices 3 and 6. In these tests, the device was installed such that it was in contact with the SG tube wall. Flow rates for 15 percent and 100 percent Reynolds similitude were tested. © Copyright 2018 by NuScale Power, LLC 15

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.1.1.3 Test Facility Overview The overall facility design consists of a test loop that connects to a header with four, parallel test assemblies. Each assembly consists of a FW plenum, flow restrictor device, and SG tube. Only one assembly was tested at a time. The ball valves were used to isolate the test assemblies that were not in use. The test fluid was tap water filtered by a 1 micron filter installed between the two pumps. Valves downstream of the second pump are used to adjust the system pressure and a valve downstream of the test apparatus is used to regulate flow rate. A schematic of the test facility design is provided in Figure 3-4. Figure 3-4 Steam generator inlet flow restrictor test facility schematic The FW plenum is four-inch, schedule 40 pipe. It contains two sets of perforated plates to straighten the flow before it arrives at the restrictor mounting plate. The FW plenum provides absolute pressure measurement, a tap for differential pressure measurement from the plenum to downstream of the flow restrictor in the SG tube, and an accelerometer © Copyright 2018 by NuScale Power, LLC 16

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 on the exterior of the SG tube. The FW plenum and nearby test loop components are shown in Figure 3-5. Additionally, the test facility contains scales used in the gravimetric flow rate determination, a data acquisition system (DAS) to process instrument signals, and a boroscope that was used to visually inspect the inside of the SG tubes. ((

                                                                                                          }}2(a),(c)

Figure 3-5 Test assembly 3.1.1.4 Testing Procedure The testing procedure consisted of installing the restrictor devices to be tested into each test assembly, and performing instrument and DAS functional checks. Next, the system is filled with water and air is vented. Before starting flow testing, the DAS was set to continuously record instrument signals. Flow is started and aligned to the assembly to be tested. Because gravimetric flow rate measurement was used, the flow testing consisted of setting the flow to achieve the expected differential pressure associated with the 50 percent Reynolds similitude flow condition. The test conditions at approximately 50 percent flow were then used to calculate the test value for the restrictor loss coefficient. Differential pressures for the remaining Reynolds similitude flow rates (15 percent, 90 percent, 100 percent and 110 percent) were © Copyright 2018 by NuScale Power, LLC 17

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 calculated using the experimentally determined restrictor loss coefficient. Then, the remaining flow tests were executed in the test loop by adjusting the flow control valve. Based on this approach, differences exist between the target and actual flow rates achieved for each Reynolds similitude case. This is acceptable because data was collected over a range of flow rates that spanned the prototypic secondary flow conditions. Gravimetric flow rate provided the actual, average flow rate at the conclusion of each test. In addition to the flow rates noted above, restrictor devices were tested at low flow rates, near 1 percent Reynolds similitude. Also, Devices 1, 3, 6, 7 and 10 were checked for cavitation by increasing the inlet pressure at the 110 percent flow rate condition. A cavitation number was determined for each type of restrictor design. Higher inlet pressures provide more stability to cavitation; therefore, cavitation is not a concern in the final design since normal operating pressure is much greater than the test pressure conditions. When the four installed assemblies had been tested, the loop was drained to permit installation of the next set of orifice devices. Visual inspections of the tubes were completed using the boroscope to assess if there was visible damage due to vibration of the restrictor device. 3.1.1.5 Assessment of Root Mean Square Vibration Results The accelerometer results for each device and flow rate condition were evaluated to confirm which devices and flow rate conditions result in levels of tube vibration that may indicate the presence of leakage flow instability. The test data is provided in three formats: continuous save files, dynamic signal analysis (DSA) files, and select data files. The continuous save files contain accelerometer measurements and root mean square (RMS) acceleration values that are averaged, both over 0.5 second intervals. The DSA files contain the dynamic signal from the 4000 Hz accelerometer over 30 seconds. The select data files contain the overall averages of the acceleration and RMS acceleration for each flow rate condition tested. The average RMS acceleration and maximum acceleration values are used to demonstrate the devices and flow conditions where leakage flow instability may be indicated. Vibration levels, at which there is a possibility of leakage flow instability, typically occurred at the highest flow rate tested. Only Device 1A was flow tested at approximately 150 percent Reynolds similitude. Other devices had a maximum flow test at Reynolds similitude of approximately 110 percent. Table 3-2 was generated by determining the tests with the highest average RMS acceleration values and highest maximum acceleration valves. The table provides the 10 tests with the highest average RMS acceleration values. Additionally, the absolute value of the maximum acceleration was determined for each test at the Reynolds similitude 110 percent case and at a lower similitude condition, if the highest average RMS vibration occurred there. Three tests have high maximum acceleration values (judged to be greater than about 75 dg) but normal average RMS acceleration values (judged to be less than about 30 dg): test 6C1, 10C4, and 11C2. These three tests are also included in the table to provide explanation of the test results. © Copyright 2018 by NuScale Power, LLC 18

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-2 Average and maximum root mean square vibration results Approximate Average RMS Device Device Plenum Maximum Acceleration Device Reynolds Acceleration Description Number Tested (dg) Percentage (dg) Center 1 A 4 150 (( }}2(a),(c) orifice Stepped annular 6 C 1 110 (( }}2(a),(c) OD 0.510 inch Space 0.5 inch 7 A 1 Note (2) (( }}2(a),(c) 7 B 4 Note (2) (( }}2(a),(c) 8 A 1 110 (( }}2(a),(c) Stepped annular 8 B 2 100 (( }}2(a),(c) OD 0.515 inch 9 A 3 100 (( }}2(a),(c) Space 0.5 inch 9 C 3 110 (( }}2(a),(c) 10 A 1 100 (( }}2(a),(c) 10 C 4 110 (( }}2(a),(c) Stepped 11 C 2 110 (( }}2(a),(c) annular 12 B 1 110 (( }}2(a),(c) OD 0.515 inch Space 0.75 12 B 1 90 (( }}2(a),(c) inch Notes: (1) Maximum acceleration for Device 1 tested at 110% is (( }}2(a),(c) dg; average acceleration is (( }}2(a),(c) dg for test 1A4. (2) DSA and select data files are not provided for Device 7. The continuous save file is used to determine acceleration values; however, there is not enough information in that file to correlate the period of vibration to a specific flow rate case. It is assumed that the values reported in this table correspond to the 110% Reynolds similitude flow test. (3) These values are the maximum reported in the continuous save file, which is an average of the 4000 Hz readings each half second. Therefore, these are not true maximum values like the others in this table. (4) A select data file was not provided for this test; therefore, an average RMS acceleration is calculated using the continuous save file. (5) High acceleration due to functional tap test during the flow testing. The center orifice design experienced significant vibration at the 150 percent Reynolds similitude condition. At and below 110 percent, the average RMS accelerations remained below 3 dg for the center orifice configurations and flow rates tested as shown in Figure 3-6. This device was located in the FW plenum rather than the SG tube, where the accelerometer is mounted. Therefore, the sensed vibration in and around the restrictor is higher than was transmitted to and measured at the tube. If significant TB or leakage FIV were present, this would be transmitted to the tube. The low accelerations in Figure 3-6 show that the device performed acceptably at and below 110 percent Reynolds similitude. The RMS accelerations generally increase with increasing flow rate, and represent the acceleration of the tube itself due to turbulent, annular flow. © Copyright 2018 by NuScale Power, LLC 19

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-6 Device 1 root mean square acceleration at 110 percent Reynolds similitude and below Devices 2 and 3 are the threaded annular design. This design did not experience significant vibration at or below the maximum flow rate tested of 110 percent Reynold similitude. Tests 3A2, 3A3, 3B2, 3B3, 3C3 and 3C4 shown in Figure 3-7 represent flow testing with the restrictor misaligned. In this testing, the restrictor was mounted such that it was touching the inside of the tube. The measured accelerations are higher for the misaligned tests, but are still low, which suggests that the turbulent excitation does not cause high levels of vibration even when contact occurs for the threaded annular design. Overall, the accelerations measured for Devices 2 and 3 are higher than for Device 1 due to the higher velocities in the tube and the location of the restrictor adjacent to the accelerometer rather than in the FW plenum. © Copyright 2018 by NuScale Power, LLC 20

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                    }}2(a),(c)

Figure 3-7 Device 2 and 3 root mean square acceleration Devices 4, 5 and 6 represent the stepped annular design with the smaller step spacing and smaller step OD. The OD of the step is (( }}2(a),(c) inches and the spacing between steps is (( }} 2(a),(c) inch. Device 4 has three steps inserted into the SG tube, Device 5 has four steps inserted, and Device 6 has five steps inserted. Average RMS vibration levels were low, as shown in Figure 3-8 and Figure 3-9. The misaligned cases for Device 6 did not have significantly higher acceleration results compared to the cases where the device was properly aligned. Only two devices (5B2 and 5C2) saw average RMS accelerations near (( }}2(a),(c) dg at the 110 percent Reynolds similitude condition, and maximum accelerations for these cases remained below (( }}2(a),(c) dg. Case 6C1 had intermittent high acceleration readings. The time history acceleration for this test is shown in Figure 3-10. While the cause of the intermittent increases in acceleration readings is not known, the maximum accelerations are less than (( }}2(a),(c) dg and do not indicate a vibration concern. © Copyright 2018 by NuScale Power, LLC 21

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-9 Device 6 root mean square acceleration at 110 percent Reynolds similitude and below ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The final two sets of stepped annular restrictors, with the larger step OD of (( }}2(a),(c) inches, experienced the highest vibration levels, as shown in Figure 3-11 and Figure 3-13. Time history results are not available for Device 7, but 7A1 and 7B4 experienced vibration in excess of what can be attributed to fluid turbulence alone. Tests 8A1, 9A3 and 9C3 also experienced vibration. The average and maximum accelerations for Tests 8B2, 9A3 and 10A1 at Reynolds similitude of 100% are higher than the reported accelerations at 110 percent, although other device and plenum numbers for devices 8, 9 and 10 tested at 110% conditions also have similar or higher average and maximum acceleration results. ((

                                                                                                          }}2(a),(c)

Figure 3-11 Device 7-10 root mean square acceleration at 110 percent Reynolds similitude and below Test 10C4 has a high maximum acceleration, which is due to a functional test where the SG tube is lightly tapped with a screwdriver to test the accelerometer. This is evident in the acceleration readings near 7.5 seconds in Figure 3-12. © Copyright 2018 by NuScale Power, LLC 24

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-12 Test 10C4 acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Tests 11C2, 12B1 (at (( }}2(a),(c)) and 12B1 (at (( }}2(a),(c)) experienced high maximum vibration values. For the 11C2 and 12B1 at (( }}2(a),(c) tests, the average RMS acceleration is low ((( }}2(a),(c) dg, respectively). Only the (( }}2(a),(c) spectral analysis results for 12B1 are discussed in Section 3.1.1.6. Visually, the results with the highest responses do not have an evident vibration signature, which would be characteristic of leakage FIV. Spectral analysis is performed to confirm if there is a frequency signature in the accelerometer readings. The time history response is shown in the following section along with the spectral plots. 3.1.1.6 Spectral Analysis of Vibration Results For the devices that experienced vibration, spectral analysis of acceleration data is performed to determine if the vibration is dominant at a specific frequency, as would be seen with the leakage FIV mechanism. The acceleration data was collected at 4000 Hz. This provides an upper frequency limit (Nyquist frequency) of 2000 Hz, per Equation 13.1 of Reference 9.1.3. fs fN = Equation 3-1 2 Where, fN = Nyquist frequency (Hz) and fs = Sampling frequency (Hz). The frequency resolution of the 4000 Hz sensor is about 1 Hz per Equation 13.10 of Reference 9.1.3, assuming a sampling block of 2k=4096 (maximum sampling block for the Fourier analysis add-in in Excel). As shown in this equation, there are two ways to provide a finer frequency resolution. One is to increase the sampling block size, n. Another is to decrease the sampling rate. The first and second modes of the final design SG IFR are approximately 150 Hz and 1000 Hz. Assuming a conservatively low damping estimate of (( }}2(a),(c), the half bandwidth for the fundamental frequency is 1.5 Hz per Equation 3.13 of Reference 9.1.3. Because that is larger than the 1 Hz frequency resolution, the frequency resolution of the test is acceptable. Resolution is also affected by the processing method (use of a single FFT, with essentially a rectangular data window), and the fact that the accelerometer is located on the tube outer wall rather than the restrictor device. More sophisticated analysis including generation of power spectra using the Welch method could be performed for this data; however, since the flow velocities in this preliminary data that experienced vibration correspond to beyond design basis flow conditions, it is not judged to be necessary to have a high frequency resolution. If vibration is observed in final testing, there will be sufficient measurements and analysis to quantitatively justify whether the vibration are from turbulence or leakage flow. © Copyright 2018 by NuScale Power, LLC 26

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 1 f f = = s Equation 3-2 nT n fw = 2 f00 Equation 3-3 Where, f = Frequency resolution (Hz), n = Sample block size (-), T = Sampling interval (s), fs = Sampling frequency (Hz), f w = Resonant peak half width (Hz), f0 = Un-damped natural frequency (Hz), and 0 = Damping (-). Spectral analyses of the devices that experienced vibration are performed using Microsoft Excel. A Fourier transform of the time history results is performed to determine if there is a dominant vibration frequency. The Fourier analysis function is used from the Data Analysis Toolpak. To use the function, the input range is specified as the 2k values of the acceleration history. The fast Fourier transform (FFT) outputs 2k complex number values. The magnitude of each value is obtained per Equation 3-4, and the associated frequency for the nth value is per Equation 3-5. 2* IMABS (FFTcomplex ) FFTmag = k Equation 3-4 2 nfs fn = Equation 3-5 2k Where, FFTmag = FFT Amplitude (-), IMABS(FFTcomplex ) = Magnitude of complex number (-), k = Integer that determines sample block size (-), © Copyright 2018 by NuScale Power, LLC 27

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 fn = Frequency for nth FFT amplitude (Hz), n = Zero to maximum sample block size (-), and fs = Sampling frequency (Hz). The amplitude associated with each frequency is calculated for up to 4000 Hz for each test; however, the plots display the first 500 Hz for clarity. If LFI were present in the acceleration data, it would coincide with the fundamental mode of the restrictor device, which is approximately (( }}2(a),(c). Spectral results between 500 Hz and 4000 Hz were reviewed and amplitudes are similar to the results below 500 Hz that are shown in the spectral plots in the body of this report. The tests with the highest acceleration results (not attributed to tap testing or an anomalous reading) are 1A4 at Reynolds similitude of 150 percent, 8A1 at Reynolds similitude of 110%, 8B2 at Reynolds similitude of 100 percent, 9A3 at Reynolds similitude of 100 percent, 9C3 at Reynolds similitude of 110%, 10A1 at Reynolds similitude of 100 percent, 11C2 at Reynolds similitude of 110%, and 12B1 at Reynolds similitude of 110%. There are no noticeable vibration signatures in the acceleration versus time plots. Additionally, the spectral analysis does not indicate there is a dominant frequency for any of these tests. This suggests that the accelerations that were seen were random in nature and are not vibration due to leakage flow instability. Leakage FIV would have a frequency signature that is similar to that of the vibrating component, because it is a strongly-coupled FIV phenomenon. Because the acceleration measurement is taken at the tube and not on the device itself, noise could result and obscure the device signature. Additionally, when high vibrations were experienced they tended to be significantly higher than the vibration levels at the next tested flow condition, which is indicative of onset of a leakage flow instability rather than the gradual increase in vibration due to a turbulent response. It is concluded that the higher vibration seen in these tests is due to contact between the restrictor and the tube due to random vibration caused by TB. Further testing and analysis will confirm or refute this. It should also be noted that the instances of high vibration occurred at flow rates in excess of the design licensing basis flow conditions, so the vibrations discussed in this report correspond to operating conditions that are beyond design basis. Maximum design flow velocities in the NuScale design correspond to the results below Reynolds similitude of 50% in these tests. Acceleration and amplitude graphs for these tests are provided in Figure 3-14 through Figure 3-29. © Copyright 2018 by NuScale Power, LLC 28

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-14 Test 1A4 (150 percent) acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-16 Test 8A1 acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-18 Test 8B2 Reynolds similitude of 100 percent acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-20 Test 9A3 Reynolds similitude of 100 percent acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-22 Test 9C3 acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-24 Test 10A1 Reynolds similitude of 100 percent acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-26 Test 11C2 acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-28 Test 12B1 acceleration ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Reynolds similitude was used to generate the required test flow rate conditions because the primary goal of the test was to confirm the ability of the restrictor to provide the necessary form loss. Because the testing was performed at low temperature conditions, the velocities required to achieve Reynolds similitude are higher in the test than they are for fluid at normal operating conditions. Therefore, the operating velocities are well bounded by the test velocities. Table 3-3 quantifies these differences. Velocities are calculated in the region of the tube without the restrictor device, and at the locations with the maximum constriction in the tube assuming the case of the (( }}2(a),(c) step OD (Devices 4-6). This step OD was selected for the velocity calculation because it matches the final design value. Additionally, velocities are calculated at normal operating conditions, and the minimum and maximum test conditions. The testing is performed between 60 degrees Fahrenheit to 120 degrees Fahrenheit and 80 psia to 150 psia. Reynolds number is calculated per Equation 3-6 and Equation 3-7. vd Re = Equation 3-6 m v= Equation 3-7 aN Where, Re = Reynolds number (-),

                                           =   Density (lb/in.3),

v = Velocity (in./s), d = Diametrical clearance (in.), m = Mass flow rate to SG (lb/s), a = Area of flow (in.3), and N = Number of SG tubes (-). Table 3-3 shows that the velocity at the minimum temperature conditions of the test is (( }}2(a),(c) percent of the velocity at normal operating conditions at the flow restrictor. At the maximum tested conditions, the velocity is (( }}2(a),(c) percent of the normal operating flow velocity. © Copyright 2018 by NuScale Power, LLC 37

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-3 Reynolds similitude values Temperature Pressure Location Velocity (in./s) Reynolds Number (°F) (psia) In tube, normal operating (( }}2(a),(c) 300 525 At constriction, normal operating (( }}2(a),(c) In tube, minimum test condition (( }}2(a),(c) At constriction, minimum test 60 80 (( }}2(a),(c) condition In tube, maximum test condition (( }}2(a),(c) At constriction, maximum test 120 150 (( }}2(a),(c) condition The acceleration results were integrated to provide the displacement at the sensor location. In this test, the accelerometers were located on the exterior of the SG tube, downstream of where the tube exits the tube sheet. The source of vibration is from the turbulent flow inside the tube, and in the case of higher acceleration results, due to the restrictor impacting the tube wall. For the misaligned cases, the restrictor was directly in contact with the SG tube inner wall. For aligned cases, the radial clearance between the restrictor and the tube outer wall is (( }}2(a),(c) inch for the stepped design. The SG tube displacement is calculated by double integration of the acceleration time history. The integration is performed numerically using the midpoint rule. Table 3-4 provides the maximum displacements for select tests, and Figure 3-30 plots the displacements at the beginning of each test run. Note that because only a portion of the time history is plotted, the maximum displacements in Table 3-4 are higher than the data shown in Figure 3-30. The observed displacements of the tube are smaller than the radial clearance between the restrictor and the tube wall. This is expected as the tube displacement is a result of the vibration of the restrictor. For the test case most similar to the final design and tested at velocities 180 percent to 450 percent of the licensing basis secondary side flow rate, the maximum displacement is (( }}2(a),(c). Table 3-4 Steam generator tube displacements Test Test Description Maximum Displacement (inch) Threaded design 1A4 (( }}2(a),(c) Highest flow velocity (Reynolds of 150%) and accelerations Stepped design 6C1 (( }}2(a),(c) Reynolds of 110%, design is most similar to final design Stepped design 8A1 Highest maximum accelerations for stepped design (( }}2(a),(c) Reynolds number 110% Stepped design 8B2 Moderate accelerations (( }}2(a),(c) Reynolds number 100% © Copyright 2018 by NuScale Power, LLC 38

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-30 Steam generator tube displacement 3.1.1.7 Considerations for Future Regulatory Guide 1.20 Testing The test program for the vibration testing for the SG IFR design demonstrated that for the range of designs tested, LFI is not a concern, and while impact between the restrictor device and the tube occurred between approximately ((

                    }}2(a),(c) of the normal operating velocities, vibration levels characteristic of impact were not observed at normal operating velocities.

The following items were considered in the development of the CVAP SG IFR testing:

Modal testing should be performed to confirm the frequencies of the restrictor in the test apparatus structure. Due to differences associated with the test assembly compared to the plant design, this could alter the natural frequency seen at the accelerometer.
A longer sampling time further improves the frequency resolution. The test should provide real time frequency analysis of the accelerometer readings, considering the entire length of the test data.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

Accelerometers should be placed in more than one location for each assembly to provide redundancy in the measurements and a measure of experimental uncertainty. Direct measurement of restrictor vibration should be made, but if that is not possible, predictions of the expected tube vibration due to turbulent or leakage flow impact from the restrictor should be performed to inform optimal sensor placement locations and interpretation of real time frequency results during the test.
Predicted reduced flow velocities (which are a function of flow velocity and structural frequency) should be determined for the SG IFR final design and the test velocities chosen considering these values.
The testing should be long enough to achieve a minimum of 1 million vibration cycles assuming the restrictor is vibrating at its fundamental frequency. Using these results, an adequate inspection frequency for the component design life can be determined in advance of the Regulatory Guide 1.20 inspections following initial startup testing.

3.1.1.8 Conclusions Based on the lack of vibration signatures in the acceleration results and no dominant frequency peaks in the spectral analysis, these initial test results demonstrate that LFI and TB are not a concern for these designs. Some designs, when tested at the highest Reynolds similitude conditions, experienced increased vibration due to contact between the restrictor and SG tube. The contact appears to have resulted from turbulence or a leakage flow response; however, these higher accelerations were only observed at beyond-design-basis flow velocity conditions. The testing duration combined with the measured acceleration levels were not long enough to produce degradation of the restrictor or the SG tube. High levels of vibration were not present at the lower Reynolds similitude conditions, where the velocity is similar to the velocity present at normal operating conditions. The vibration that was observed would be characteristic of operating at approximately ((

                    }}2(a),(c) flow conditions in terms of the fluid velocities. Therefore, while small differences exist between the tested and final SG IFR designs and improvements are recommended for future CVAP Regulatory Guide 1.20 testing, the initial testing provides a level of confidence that the SG IFR design does not experience leakage FIV or degradation due to turbulence at normal operating design conditions in the plant.

Validation testing is planned to confirm the final SG IFR design is not susceptible to vibration in accordance with Regulatory Guide 1.20. See Section 5.3 for a discussion of the requirements for the SG IFR validation testing. 3.2 TF-1 Benchmark Testing for Turbulence This information will be provided at the next scheduled revision of the technical report. 3.3 TF-2 Benchmark Testing for Turbulence This information will be provided at the next scheduled revision of the technical report. © Copyright 2018 by NuScale Power, LLC 40

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.4 TF-2 Benchmark Testing for Fluid Elastic Instability In the process of benchmarking the thermal-hydraulic performance of the prototypic HCSG, NuScale commissioned Sperimentiamo le Tue Idee (SIET) to construct and test two separate test specimens. Test Facility #1 (TF-1) utilized electric direct heating of several individual helical coil tubes to investigate thermal hydraulic behavior within the secondary-side (HCSG tubes). Test Facility #2 (TF-2) was a more-complex specimen, consisting of a 5-column, partially-prototypic HCSG assembly inserted into a test vessel and operated at a range of conditions, with variations in both primary- and secondary-side parameters. Given that it represents a smaller version of the ultimate fully-prototypic design, TF-2 was used to obtain a limited sample of data to characterize the response of individual HCSG tubes to various flow conditions. These measurements were accomplished by affixing axially-oriented strain gauges to the outside of specific tubes. During testing, TF-2 was subjected to both normal and above-normal operating conditions, including a series of cases wherein primary flow rates were increased to approximately (( }}2(a),(c) of normal operating maximum to assess whether FEI) excitation of the HCSG tubing is feasible. This section provides a detailed analysis of the strain gauge measurements obtained from TF-2 during FEI testing conditions, including the methodology, results, relevant observations, and the ultimate conclusion that the onset of FEI was not observed in any of the tests. While the TF-2 test was not fully-prototypic, the measurements and subsequent results presented herein are used in conjunction with other testing program results to validate the HCSG CVAP design analysis. 3.4.1 TF-2 Test Design The primary purpose for fabrication and testing of TF-2 was qualification of the NuScale thermal hydraulic models, and confirmation of fluid property specifications and assumptions. SIET possesses an existing test facility (GEST) with the pressure vessel and associated pumps and equipment necessary to perform high-pressure, high-temperature testing of vessel internal components. A prototypical assembly was created to mimic the as-designed HCSG, with representative tubes of identical OD and pitch. Modifications were made to the end portal designs to simplify manufacturing. The size of the specimen was limited by the size of the GEST vessel, which necessitated using Columns 1-5 (of 21 total) as shown in Figure 3-31. This is less-desirable for the FEI assessment because the inner-most tubes have the lowest reduced velocities and require the highest driving flow to reach the onset point. © Copyright 2018 by NuScale Power, LLC 41

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-31 TF-2 Fluid-heated test section tubing column scheme Assessment of vibration mechanisms, including FEI, was not taken into consideration during initial scoping activities for the test program. The opportunity to obtain additional, value-added data in support of CVAP benchmarking efforts was acted on once recognized; however, at that stage it was not possible to implement a comprehensive instrumentation configuration for FIV. There were physical and environmental challenges associated with the sensors themselves. In addition, the design and construction of TF-2 did not facilitate use of a fully-prototypic tube support configuration. The actual NuScale design is based on eight tube support columns, which are comprised of interlocking plates with bent extruded tabs as shown in Figure 3-32. The support columns are arranged in a consistent pattern at azimuths of (( }}2(a),(c),and so on, such that the longest unsupported span of the HCSG tubing is (( }}2(a),(c). © Copyright 2018 by NuScale Power, LLC 42

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-32 TF-2 Tube support detail Conversely, TF-2 was fabricated with four support columns (at ((

                }}2(a),(c)), for an effective span length of ((      }}2(a),(c). This is beneficial for the FEI assessment because, compared to the fully-prototypic support configuration, the longer spans result in lower frequencies. The TF-2 supports restrain motion in a similar fashion as the tabbed supports in the fully-prototypic design. For either configuration, the interface at each tab/guide approximates a pinned connection. The presence of multiple tabs in close proximity serves to reduce rotation about the support column and constrains the significant modes to individual bending of the unsupported spans. Minor differences in thermal expansion between the tubing, tube supports, reactor pressure vessel (RPV) riser, and RPV wall cumulatively result in the tubing being pinned tightly against one side of the supports, further supporting the above determination on modal constraints. Variations in support interface rigidity may introduce variations in localized static strains within individual tubing spans.

Given the preceding discussion, the natural frequencies and mode shapes of the TF-2 tubing are not expected to match those from NuScales fully-prototypic design models, including the FEI analysis. In order to facilitate comparison and evaluation of the resulting data, NuScale generated modal predictions for several single tube configurations within TF-2. Because the corresponding NuScale modal analysis has not been finalized as of issuance of this report, the corresponding mode shapes and frequencies presented herein are treated as an assumption. Given the geometry and support arrangement of the helical © Copyright 2018 by NuScale Power, LLC 43

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 array, there are a number of modes, many with similar, closely-spaced frequencies and response profiles. The frequencies that are of interest based on mass participation are provided in Table 3-5. Results for the columns were similar, but Column-5 was selected as the primary set of outputs for further processing given that its slightly-longer unsupported spans result in the lowest fundamental frequencies. Figure 3-33 plots the directional mass participation results for TF-2 Column-5 with respect to frequency. From this plot, the frequencies that provide significant contribution to potential tubing movements are ascertained. The TF-2 models were generated in a global/cartesian coordinate system, wherein the Y-direction is vertical and the X- and Z-directions are either axial to or perpendicular with the tubing, depending on azimuth. From this plot, Table 3-5 was created to list the anticipated significant frequencies that may be observed in the dynamic data. Table 3-5 Single tube model predicted significant frequencies Frequency Range (Hz) Response Direction Notes (( }}2(a),(c) Vertical (Y) Tube breathing mode (( }}2(a),(c) Radial (X, Z) First mode bending (most spans) (( }}2(a),(c) Radial (X, Z) First mode bending (select intermediate spans) (( }}2(a),(c) Vertical (Y) First mode bending (( }}2(a),(c) Radial (X, Z) Complex, higher bending modes Figure 3-34 provides a graphical comparison of total square-root-of-the-sum-of-the-squares relative response for the five modes with the largest mass participation factors. The plot series names include the mode number, associated frequency, and mass participation ranking and primary direction of excitation. Mode-1 (((

                    }}2(a),(c) mass participation factor) is also included in the plot to illustrate the breathing mode response of the tubing. Figure 3-35 depicts the same data as Figure 3-34, but with each modes relative displacements adjusted by a weighting factor equivalent to its mass participation divided by the maximum mass participation. This illustrates the relative predicted impact of each mode on the overall response.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                                     }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                                     }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The in-vessel instruments were exposed to a fluid environment over the full range of operating parameters, which restricts the applicable sensors to a small range. Also, there were physical challenges in terms of limited space to install or affix sensors in the space between the inner (annual) and outer walls. Given these challenges, SIET chose to employ Kyowa strain gauges (Model KHC-20-120-G9-16), which are affixed to the tubing by capacitive discharge welding. These sensors have been deployed for in-vessel measurements of boiling water reactor steam dryers. The noise floor is quite high compared with 350 strain gauges, which have a higher gauge resistance and improved signal-to-noise ratio. The indicated strain gauges were installed in pairs at six different locations (12 total sensors). Columns 1, 3, and 5 were chosen to represent the range of available geometries within TF-2. For each column, strain gauges were installed on one select tube, at a Lower and an Upper location. These locations were generally 11/2 helical turns from the respective FW or steam plenums. At each location, one strain gauge was installed on the tube extrados (side) and another was installed on the top. Both strain gauges were oriented axially. Refer to Figure 3-36 for a schematic illustrating the placement of strain gauges at each location and Figure 3-37 for a photograph of the sensors installed at the lower location of Column-1. Table 3-6 summarizes channel and location information for the installed strain gauges. Because the actual damage mechanism associated with FEI is excessive tube motion leading to adverse wear and impacting, it is important to understand how measured strains relate to actual tube displacements. This relationship varies depending on sensor placement and support configuration. Figure 3-36 Placement of strain gauges on tube coils (typical) © Copyright 2018 by NuScale Power, LLC 48

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c))

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-6 Placement of strain gauge instrumentation Sensor Sensor Placement (Specific) Sensor Placement (General) Description Elevation Linear Azimuth / to Nearest Name ID Column Tube Plenum Position (m) (m) (°) Support S1101-1 S01 Side (( FW S1101-2 S02 Top }}2(a),(c) 1 20 S1102-1 S03 Side (( MS S1102-2 S04 Top }}2(a),(c) S3101-1 S05 Side (( FW S3101-2 S06 Top }}2(a),(c) 3 21 S3102-1 S07 Side (( MS S3102-2 S08 Top }}2(a),(c) S5101-1 S09 Side (( FW S5101-2 S10 Top }}2(a),(c) 5 11 S5102-1 S11 Side (( S5102-2 S12 MS Top

                                                                                                          }}2(a),(c)

Notes: 1. The Plenum column defines sensor location based on the nearest inlet/outlet - -FW or MS.

2. Global elevations are measured from a datum several meters below the steam generator.

3. Linear positions are measured from the inlet (FW) orifice of an individual tube, along its centerline.

4. Global azimuths are measured from a 0° reference at the inlet (FW) plenum. In this arrangement, tube supports are at global azimuths of (( }}2(a),(c) and so on.

5. Sensors S03 and S04 (Column-1, Upper/MS Location) were determined to be non-functional upon installation, and the data from these channels is excluded from subsequent analysis hereinafter.

Table 3-7 summarizes the test series, plateaus, and filenames that were selected for further processing, including the applicable steady-state fluid parameters at the time of acquisition. It also presents a shortened alpha-numeric naming convention that is used to identify/discuss specific datasets throughout the remainder of this section. Test series TF0005 and TF0006 did not contain datasets at ramped flow conditions, but only at maximum flow conditions. It is assumed that these datasets are outliers wherein SIET was attempting to establish steady-state flow conditions at elevated temperature and pressure. © Copyright 2018 by NuScale Power, LLC 50

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-7 Test conditions and file names for fluid elastic instability data acquisition Primary Side Secondary Side Test Series Test ID Flow Temp. Pres. Temp. Conditions (kg/s) (°F) (psi) (°F) 114.4 A1 141.7 A2 172.5 A3 TF0001 199.2 Ambient (( }}2(a),(c) A4 230.5 A5 263.3 A6 113.7 B1 143.3 B2 174.6 B3 TF0002 205.0 Ambient (( }}2(a),(c) B4 229.5 B5 262.5 B6 113.2 C1 142.2 C2 175.5 C3 TF0003 Ambient (( 200.7 }}2(a),(c) C4 234.5 C5 263.6 C6 113.5 D1 145.7 D2 170.6 D3 TF0004 202.0 249.9 (( }}2(a),(c) D4 232.6 D5 266.8 D6 TF0005 252.7 580.0 (( }}2(a),(c) E6 260.2 F6a TF0006 262.3 499.9 (( }}2(a),(c) F6b 168.4 G3 199.0 G4 TF0007 449.8 (( }}2(a),(c) 227.0 G5 256.0 G6 Notes: 1. The indicated temperatures represent inlet values. The secondary-side parameters represent average values across tube columns. Where present, singular values represent an average or nominal value for datasets within a particular test series.

2. The indicated test IDs (right-most column) were assigned to simplify reference to individual datasets or conditions. The 1st character (alpha-indicator) refers to a specific test series with consistent primary and secondary side parameters (note: primary flow varies); the 2nd character (numeric) is a sequential index increasing with flow rate.

The FEI data files listed in Table 3-7 were reviewed to evaluate waveform (time) and spectral (frequency) content. A consistent processing approach was applied to each of the data files in Table 3-7, to enable like-for-like comparisons. This processing consisted of eliminating spurious signal noise and computing statistics or estimates to inform the FEI © Copyright 2018 by NuScale Power, LLC 51

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 evaluation. The general steps and characteristics of the processing script are described below for reference.

The raw waveform files exhibit variation between datasets and individual channels in terms of average (DC) value(s). Figure 3-38 exemplifies these DC variations by plotting the raw waveform data for sensors S01, S05, and S09 (one in each column) at the maximum primary flow for each test series (i.e., datasets A6, B6, C6, D6, and G4). These variations were anticipated given the sensor type and configuration, as well as the uncertain boundary conditions on individual tubes when the HCSG assembly is thermally loaded. Given the randomness of the variations, it is not possible to infer meaningful results by comparing the static values (DC/average) between datasets or individual channels. Removal of the DC content (by subtracting the average) results in reasonable dynamic waveforms, which are comparable between datasets or channels. Thus, the DC content of the waveforms was removed during processing.
Digital filtering was used to restrict the signal content to the frequency range of interest for the HCSG and to eliminate spurious electrical noise. Filters were based on

((

                           }}2(a),(c). The filters were applied in the forward and reverse direction to avoid phase distortion, using the filtfilt function in Matlab.

o If present, FEI excitation within the HCSG is expected to amplify the first-mode bending frequencies of the individual tube columns. These frequencies range from approximately (( }}2(a),(c) (radial direction) to (( }}2(a),(c) (vertical direction), depending on the assumed boundary conditions. Given the support configuration and general flexibility of the thin-walled tubes, higher-order modes may also be visible within the data, up to 100 Hz per the modal analysis. For the FEI analysis herein, a digital bandpass filter was used to de-emphasize content outside of the frequency range of interest. Specifically, the filter negates the impact of low-frequency drift and slow oscillations that are visible in many of the unadulterated waveforms. ((

                                                               }}2(a),(c).

o The TF-1 dynamic pressure data exhibits a notable response peak between ((

                                    }}2(a),(c) within the dynamic pressure data obtained from the secondary-side sensors. Thus, a second or alternate processing run was performed with a bandpass filter range of 5 to 1,000 Hz to evaluate whether the data contains any higher-frequency peaks of interest that align with the TF-1 content. A separate set of processing parameters are applicable to the higher-frequency bandpass, which are referred to as Run-2 hereinafter. The 3-300 Hz bandpass noted in the previous item is referred to as Run-1. Table 3-8 provides a summary of the exact processing/filtering parameters applied during Run-1 and Run-2.

o The strain gauge signals exhibit some electrical line noise ((( }}2(a),(c)) or its multiples ((( }} 2(a),(c), and so on). In order to delineate content at apparent structural frequencies and normalize overall results between datasets, these electrical frequencies (where present) were removed using bandstop (notch) filters. For each peak, a 6th-order filter was applied, with a bandwidth of (( }}2(a),(c) depending on the amplitude and width of the target © Copyright 2018 by NuScale Power, LLC 52

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 frequency. For Run-2, filtering of electrical multiples (i.e., (( }}2(a),(c) and higher) introduced additional spectral noise. Thus, the bandstop filters for Run-2 were applied in an identical fashion as Run-1, such that some amount of electrical noise remained present at (( }}2(a),(c) and above.

For certain channels, the digital filtering operations produced a ringing effect at the beginning and end of the resulting waveform where the digital filters struggle to track the target raw signal from unknown initial conditions. Therefore, before calculating the overall values and frequency transforms for each channel, one-half second of data was truncated from the start and end of each channels waveform to remove potential ringing effects. The net effect of this operation is that the overall length of each channel waveform is reduced from 5 seconds (raw) to 4 seconds (processed).
After these operations were completed, overall values were obtained from the processed waveforms for each channel of each dataset. Values were obtained in terms of RMS, zero-to-peak (0-pk), and peak-to-peak (pk-pk) measures, although only the RMS and 0-pk results will be used in the remainder of this report.
The processed time domain data was converted to the frequency domain using an FFT algorithm; specifically, the pwelch function within Matlab, which calculates the broadband-normalized power spectral density (PSD) of a signal. A frequency resolution (bin width or f) of (( }}2(a),(c) was applied for all channels, resulting in multiple waveform data blocks of (( }}2(a),(c) duration. For the large frequency range in Run-2, a f=(( }} 2(a),(c) was applied to obtain 1-second data blocks). An overlap of 50 percent was used to increase the number of data blocks in the computation. A Hanning window was used in conjunction with the FFT algorithm to avoid spectral bin leakage due to varying start and end conditions of each block, thereby improving spectral bin resolution. Use of the Hanning window in this manner has a global scaling effect on each block, which in turn requires multiplication by an adjustment factor (1.5) in order for frequency domain amplitudes to match time domain content at specific frequencies. The windowed, scaled FFT results for each block are then linearly averaged to compute the overall PSD. This averaging process improves spectral resolution and normalizes the effects of frequency-specific amplitude perturbations. The entire process of resolving the waveform into overlapped blocks, performing the FFT conversion, windowing, scaling, and averaging is self-contained and controlled by the pwelch function and its parameter inputs.

For random vibration signals such as those obtained from the TF-2 strain gauges, spectral plots are represented in RMS units to simplify identification and characterization of dominant peaks. Thus, the overall PSDs computed as described in the preceding item were converted to RMS spectra, using the expression in Equation 3-8. Equation 3-8 () = () f Where, Srms(f) = Frequency domain spectral output in terms of RMS value, Spsd(f) = Frequency domain spectral output in terms of PSD value (i.e., from pwelch), © Copyright 2018 by NuScale Power, LLC 53

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 f = Spectral resolution or bin width, and Fwindow = Window adjustment factor (1.5 for Hanning window). For any signal, Parsevals theorem holds that the total energy content in the time domain must equal the energy content within the resulting frequency domain. Thus, for the spectra obtained from the frequency domain conversions described above, it is possible to compute an overall RMS value over a specific frequency range using a square-root-of-the-sum-of-the-squares approach. This relationship is expressed in generic form (i.e., for an FFT algorithm without windowing, scaling, and averaging) in Equation 3-9. The integral limits for the spectral term (right-hand side) of Equation 3-9 were modified to reflect a frequency range of interest (i.e., flow to Fhigh instead of 0 to F). The expression in Equation 3-9 is applicable to the normalized (single-sided), raw (complex) output of generic FFT algorithms. For this application, use of the pwelch function in the manner described above automatically returns a single-sided, magnitude-only (non-complex) spectrum, which is properly scaled for the applied windowing and averaging parameters. Consequently, the expression used to compute overall RMS values from the pwelch spectral results was modified for span-specific calculations as shown in Equation 3-10. 1 2 Equation 3-9

             =             ()           =            =          ()

Where, Wrms = Time domain RMS measurement from signal waveform, W(t) = Discretized time domain waveform, containing N number of points, T = Period/length of time domain signal(s), dt = Difference in time between measurement points (i.e., inverse of sampling rate), Srms = Frequency domain RMS measurement from normalized (single-sided) Fourier transform, S(f) = Normalized Fourier transform raw output (in complex form), F = Maximum discretized frequency of the continuous Fourier transform. For N waveform points, = 2, and df = Difference in frequency between bins (i.e., f). 1 Equation 3-10 _ = () Where, Srms_f = Frequency-band-specific RMS measurement computed from pwelch spectrum output, flow = Lower bound of the frequency span of interest, and fhigh = Upper bound of the frequency span of interest. © Copyright 2018 by NuScale Power, LLC 54

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                   }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-8 Summary of applied processing parameters Parameter: Run-1 Run-2 DC Removal Yes Yes (( Bandpass Filter

                                                                                                          }}2(a),(c)

(( Notch Filters (Electrical Noise)

                                                                                                          }}2(a),(c)

(( Waveform Truncation

                                                                                                          }}2(a),(c)

(( Frequency Spectra/PSD

                                                                                                          }}2(a),(c)

Notes: 1. A nominal value of (( }}2(a),(c) was used for notch filter bandwidth in most cases; the 2(a),(c) (( }} setting was applied in select cases where the width of the (( }}2(a),(c) primary electrical noise peak warranted additional reduction of the adjacent frequency bins.

2. The indicated notch filters at (( }}2(a),(c) were only applied when review of the spectra indicated content present at those frequencies.

3.4.2 TF-2 FEI Benchmarking Analysis Results The datasets listed in Table 3-7 were processed and the results collected in intermediate output files, containing summarized overall or statistical values, as well as digitized spectral tables. The intermediate results were then formatted into representative tables and plots for further assessment and interpretation. The list below summarizes the results obtained in this fashion. Unless otherwise explicitly specified, the tables, plots, and summary values specified below were obtained from datasets processed according to the standard parameters specified in Run-1 in Table 3-8. The waveform duration ((( }}2(a),(c)) is short and does not facilitate accurate characterization of frequencies when acquiring random vibration data as is typical of FIV excitation. Specifically, for turbulence or FEI, one can observe variations in the amplitude of response peaks over the course of (( }}2(a),(c) due to minor differences or local effects in the fluid excitation function. The concern is particularly relevant at low frequencies ((( }}2(a),(c)), as there are fewer cycles for the FFT algorithm to attempt to characterize and, if acquisition is triggered during a period of relative calm, the response may not be visible. © Copyright 2018 by NuScale Power, LLC 56

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The overall noise floor of the data, on average (( }}2(a),(c) (PSD units), is higher than desirable for such measurements. This is evident when viewing combined spectral or PSD plots in which the resultant data for the datasets is overlaid. A reference example is provided in Figure 3-39 for several of the Column-3 sensors. As noted previously, this elevated noise is not unexpected given the type of strain gauges used. The increased noise floor does not impact the ability to characterize observable peaks, but obscures minor peaks (in particular for modes that are not excited by the flow conditions). This issue is compounded by the aforementioned short waveform duration. Table 3-9 and Table 3-10 provide overall values in terms of RMS and 0-pk units. The tables are fitted with data bars to facilitate quick visualization of datasets/channels that fall outside of the norm. Table 3-11 and Table 3-12 provide summarized overall 0-pk values by test series and primary flow rate, respectively. Average and maximum values are reported for each category and the test series or flow rate with the overall largest value for each channel is summarized at the bottom of the table. These tables help to illustrate whether specific parameters have a marked effect on overall dynamic content. The FFT outputs were used to create comparison spectral plots for the datasets and channels. The plots were grouped in two different fashions: by test condition and by primary flow rate. Additional notes are as follows: Datasets E6, F6a and F6b were excluded from these spectral plots. The primary- and secondary-side flow conditions for these datasets are similar to dataset G6, but the spectral data is not a direct match. These datasets appear to be outliers, because flow was not ramped in a similar fashion as test series A-D and G. Appendix B contains plots from 0-300 Hz arranged by test series, consistent with filters applied according to Run-1. Appendix C plots contain the same 0-300 Hz data arranged by primary flow rate. Data was also plotted from 0-1,000 Hz, consistent with the bandpass filter applied according to the alternate parameters specified in Run-2 in Table 3-8. Appendix D contains the plots arranged by test series and Appendix E contains the plots arranged by primary flow rate. Datasets within test series G exhibited more content at electrical noise multiples (i.e., (( }}2(a),(c), and so on) as compared to prior recordings. It was not possible to filter out the electrical peaks without introducing additional spectral noise, so bandstop filters were limited to multiples between 50 and 300 Hz. Thus, the plots in Appendices D and E exhibit electrical noise peaks at higher multiples (350 Hz and above), specifically for test series G. The spectral plots were reviewed for frequency content. Most datasets or channels exhibit content at frequencies not predicted within the assumed modal analysis results; in many cases, the amplitude of these peaks is larger than any within the predicted frequency bands. The most-common additional peaks were: 1) a low-frequency response (<10 Hz),

2) a series/group of peaks in the (( }}2(a),(c) range, and 3) another group or set of fairly-sharp peaks in the (( }} 2(a),(c) range. Accordingly, the method shown in Equation 3-10 and its accompanying discussion are used to compute frequency-range-

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 specific RMS values. The results of those computations are provided in tabular form in Appendix F. The frequency ranges that were evaluated are as follows:

        *    ((                 }}2(a),(c): Tube breathing mode, plus large responses observed on several channels. Application of the bandpass filter (((                            }}2(a),(c) per Table 3-8) served to minimize content at frequencies below ((                     }}2(a),(c).
        *    ((                   }}2(a),(c): First-mode bending in horizontal plane, visible responses within data.
        *    ((                   }}2(a),(c): First-mode bending in vertical plane, visible responses within data.
        *    ((                   }}2(a),(c): visible responses within data, predominantly at ((
                        }}2(a),(c) (frequency and amplitude varies by channel and dataset).
        *    ((                       }}2(a),(c): visible responses within data.

The observed significant frequencies (above) were compared with potential sources of known excitation within the system. Outside of electrical content, which was removed by filtering, the only other potential source of forced excitation would be vane passing frequency pulsations from the driving pump(s). There were no consistent peaks within the data at (( }}2(a),(c) or multiples thereof. The data from Table 3-9 and Appendix F was combined in Table 3-13, to create a consolidated view of the various frequencies and amplitudes of interest for each dataset and channel. The table was generated by comparing the frequency-bin-specific RMS values from the tables in Appendix F to the overall RMS values from Table 3-9; most of the numbers in the table thus represent a percentage of the total signal energy. There is no technical basis for this calculation, as it compares values calculated from a single-sided frequency domain representation to those obtained directly from the raw time domain. As such, the numbers in the table should be treated as representative trends, not an exact measure of fractional energy. Conditional formatting is used to further delineate peaks. Table 3-14 and Table 3-15 mimic the consolidated view within Table 3-13, but with low-frequency content (0-10 Hz) excluded to highlight changes in response at the presumed tubing response modes. Table 3-14 is sorted by test series and dataset, while Table 3-15 presents the same data sorted by flow rate. The overall peak dynamic strains from Table 3-10 were plotted versus flow rate to illustrate any escalation of content with increased primary flow. Figure 3-40 provides the resulting plot. Data labels are included for points with overall values greater than ((

                }}2(a),(c) to help identify datasets where large responses were observed. The plot provides a graphical representation of any non-linear escalation in tubing vibration with flow rate. If one or more resonant responses were present within the range of the TF-2 test series, whether driven by FEI, VS, or TB, it would be evident within Figure 3-40.

The amplitude-versus-flow scatter plot framework in Figure 3-40 was repeated for the frequency-range-specific RMS computations in Appendix F. The resulting plots are provided in Appendix G. © Copyright 2018 by NuScale Power, LLC 58

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The low-frequency responses observed primarily within test series G (primary conditions at (( }}2(a),(c), secondary side boiling at (( w }} 2(a),(c)) were further evaluated by plotting those spectra against their corresponding datasets from test series D (((

                                                }}2(a),(c)). Figure 3-41 provides a comparison for Column-3 (Sensors S05-S08) for Datasets D5 and G5. Figure 3-42 provides a comparison for Column-5 (Sensors S09-S12) for Datasets D6 and G6. From the data, it is evident that the peak frequency of interest is at or near the lower cutoff for the bandpass filter

((( }}2(a),(c)), with the exact response varying somewhat by channel and dataset. The corresponding raw waveforms were superimposed on the spectral plots to further clarify the difference in signals between channels with the low-frequency response component. © Copyright 2018 by NuScale Power, LLC 59

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-9 Dynamic root mean square strains measured during TF-2 fluid elastic instability tests ((

                                                                                                            }}2(a),(c)

Note: 1. The blue data bars reflect a common scale across datasets/channels, from 0 to the maximum value listed in the table ((( }}2(a),(c) from dataset G4, channel S10). © Copyright 2018 by NuScale Power, LLC 61

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-10 Dynamic peak strains measured during TF-2 fluid elastic instability tests ((

                                                                                                            }}2(a),(c)

Note: 1. The blue data bars reflect a common scale across datasets/channels, from 0 to the maximum value listed in the table ((( }}2(a),(c) from dataset G3, channel S06). © Copyright 2018 by NuScale Power, LLC 62

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-11 Dynamic peak strains by test series (average and maximum) ((

                                                                                                              }}2(a),(c)

Notes 1. Values in the table represent the average or maximum across datasets within the indicated test series.

2. The blue data bars represent a common scale across the average values, from 0 to the maximum value listed in the table ((( }}2(a),(c)).

3. The yellow data bars represent a common scale across the maximum values, from 0 to the overall maximum listed in the table ((( }}2(a),(c)).

4. The green data bars represent a common scale across the maximum values, from 0 to the overall maximum listed in the table ((( }}2(a),(c)).

5. The summary rows at the bottom of the table indicate the test series during which the highest average, maximum, and standard deviation values were observed within individual datasets.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-12 Dynamic peak strains by flow rate (average and maximum) ((

                                                                                                                         }}2(a),(c Notes: 1. Flow rates listed above represent an average of the values listed in Table 3-7 for applicable datasets. For example, the first value (((               }}2(a),(c) is the average flow rate for Datasets A1, B1, C1 and D1; the last value (((            }}2(a),(c) is the average for Datasets A6, B6, C6, D6 and G4.

2. Values in the table represent the average or maximum across datasets within the indicated test series.

3. The blue, yellow and green data bars are as-described in the footnotes to Table 3-11.

4. The summary rows at the bottom of the table indicate the flow rates at which the highest average, maximum, and standard deviation values were observed within individual datasets.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-13 Relative comparison of content within frequency ranges of interest (0-10 Hz inclusive), sorted by test series ((

                                                                                                                                                                                                                                                                                          }}2(a),(c)

Notes: 1. Values listed in the Overall columns were obtained from Table 3-9 (i.e., in units of -RMS).

2. The values in the colored columns were obtained by dividing the frequency-bin-specific RMS energy by the overall value, and thus represent an effective percentage of total signal energy within the given spectral band(s). These values should not be treated as absolutes; they are for trending/comparison purposes only.

3. The conditional formatting/highlights are frequency-bin-specific across all channels. For example, within the (( }}2(a),(c) bin, formatting is applied over the range from the minimum value ((( }}2(a),(c) from dataset G6, channels S09 and S10) to the maximum value ((( }}2(a),(c) from dataset C1, channel S11), which includes 310 values in total (31 datasets x 10 working channels).

4. The rule(s) for the applied conditional formatting were arrived at through several iterations of parameters, with final selection qualitative in nature. Conditional criteria are as follows:

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-14 Relative comparison of content within frequency ranges of interest (excludes 0-10 Hz), sorted by test series ((

                                                                                                                                                                                                                                                        }}2(a),(c)

Notes: 1. Values listed in the Overall ((( }}2(a),(c)) columns were obtained from Table F-7 (i.e., (( }}2(a),(c) inclusive, in units of -RMS).

2. Other footnotes from Table 3-13 are applicable herein.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-15 Relative comparison of content within frequency ranges of interest (excludes 0-10 Hz), sorted by test series ((

                                                                                                                                                                                                                                                                   }}2(a),(c)

Notes: 1. Values listed in the Overall ((( }}2(a),(c)) columns were obtained from Table F-7 (i.e., (( }}2(a),(c) inclusive, in units of -RMS).

2. Flow rates listed above represent an average of the values listed in Table 3-7 for applicable datasets, similar to the representation in Table 3-12.

3. Other footnotes from Table 3-13 are applicable herein.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                                             }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                                        }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Observations on the TF-2 data evaluation are summarized below:

Data was acquired at various primary and secondary-side conditions, as documented in Table 3-7. The length of each waveform recording ((( }}2(a),(c) seconds) was insufficient to effectively characterize the frequencies of interest given the random variations present in typical FIV data. This concern is most-pronounced at low frequencies.
Channels S03 and S04 (Column-1, Upper Location) were inoperable for all evaluated test data.
The sensor locations with respect to the nearest supports (Table 3-6) are not ideal from the standpoint of measuring maximum bending strains; many of the sensors are near the neutral-strain point for a fixed-fixed or pinned-pinned beam. That said, any significant response that is present (such as FEI) should still be plainly visible.
A mid-span measurement of (( }}2(a),(c) would represent approximately

(( }}2(a),(c) of displacement for a representative tube. This static deflection correlation may be extended to vibration at a primary driving frequency, such as that which would be expected from significant FEI excitation. As shown in Table 3-10, the peak value observed during FEI testing was (( }}2(a),(c), and the average value was below (( }} 2(a),(c). Furthermore, the reported values represent a composite overall and values at individual frequencies are much lower.The maximum observed single-frequency peak was (( }}2(a),(c) and on average, the maximum across all datasets and channels was (( }}2(a),(c). Reported value applies for frequencies greater than (( }}2(a),(c). Responses at low frequencies exhibited significant variation between datasets and it is not possible to establish bounding amplitudes considering the short duration of the recorded waveforms. The low amplitude of individual frequency peaks versus composite overalls suggests that the primary excitation on the TF-2 tubes was broad-band in nature, presumably due to general flow turbulence or buffeting. o The resultant value of (( }}2(a),(c) within the example calculation corresponds to a Displacement/Diameter ratio of approximately (( }}2(a),(c), or displacement of (( }}2(a),(c) in metric units. Comparing these values to several of the aforementioned literature sources, a measured strain of (( }}2(a),(c) peak falls at the extreme lower end of most published test data.

RMS frequency spectra were generated to compare the responses on each individual channel with respect to test series or primary flow. The plots contained in Appendices B through E were reviewed for significant content and the following frequencies were consistently observed:

o (( }}2(a),(c): low-frequency content that appeared to be present only during test series with secondary-side flow (i.e., C and G). Figure 3-41 and Figure 3-42 contain additional spectral comparisons for select datasets and sensors that exhibited responses in this realm. o (( }}2(a),(c): presumed to be horizontal-plane, first-mode bending. o (( }}2(a),(c): presumed to be first-mode bending about the vertical axis. o (( }}2(a),(c): prominent group of peak(s) present in most datasets; does not specifically match an assumed modal response; may be an upper-order mode. © Copyright 2018 by NuScale Power, LLC 71

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 o (( }}2(a),(c) prominent peak present in many datasets; does not specifically match an assumed modal response; may be an upper-order mode.

None of the observed frequencies align with potential sources of mechanical excitation. Specifically, the tubing does not appear to contain content at the driving pump(s) vane passing frequencies. Therefore, the observed peaks were determined to be structural responses, indicative of first-mode bending, as well as upper-order complex modes.
Appendices D and E provide spectra plotted to 1,000 Hz. These plots were reviewed and compared against the PSD results from TF-1 to determine whether the notable secondary-side response between (( }}2(a),(c) is also evident in the TF-2 data. Although several peaks are evident at specific frequencies (as noted above), none of the TF-2 data exhibited a broad-band response such as that observed in the TF-1 data. It is concluded that the (( }}2(a),(c) secondary-side response was either not present within TF-2, or present but not strong enough to induce a global structural response of the HCSG tubing.
Frequency-bin-specific RMS values were computed (Appendix F) and collated (Table 3-13 and Table 3-14) to illustrate where variation exists in the data. Based on review of those tables:

o The spectral plots do contain evidence of the first-mode bending peaks for the tubing; namely, responses at approximately (( }}2(a),(c) are visible in select plots. The amplitude of these responses is small, typically on the order of (( }}2(a),(c), indicating that large motions of the tubing center-spans is not occurring. o The variation responses within the FEI frequency ranges of interest are somewhat random. In general, the data appears to illustrate a slightly-increasing trend with primary flow, which is expected. In certain cases, the maximum values occurred during datasets with less-than-maximum primary flow. This can be observed from Table 3-15 in the response within the (( }}2(a),(c) band for sensor S07. o The low-frequency responses ((( }}2(a),(c)) are only visibly significant for datasets with secondary-side flow, in particularl for test series G (boiling conditions). This is readily-apparent from Table 3-13, but also evident within the overalls (Table 3-9 through Table 3-12) and spectral comparisons (Appendices B and C). Figure 3-41and Figure 3-42 further illustrate this phenomenon by comparing select datasets and sensors within test series G to corresponding data from test series D (stagnant secondary flow). Review of the raw waveforms (refer to the inlays in Figure 3-41 and Figure 3-42 for examples) suggest that the observed response is a physical effect measured by the strain gauge sensors, not a signal anomaly or sensor malfunction. The effect is consistently apparent within the lower sensor locations (those closer to the FW plenum), which suggests that it may be a function of secondary-side excitation. The responses in question were most pronounced within test series G (secondary-side boiling), even compared to test series C (single-phase flow, roughly six times the mass rate as series G), suggesting that the effect is exacerbated by elevated temperatures or fluid phase changes. © Copyright 2018 by NuScale Power, LLC 72

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The truncated (( }}2(a),(c) recordings are insufficient to allow for consistent characterization of the low-frequency responses. For example, it is unclear whether the large spike observed in S05/S06/S09/S10 near the start of both the G5 and G6 datasets is a one-time or repeating event. Based on the limited data available, it appears that the observed response was generally between (( }}2(a),(c). The single-tube modal results exhibit only one frequency below (( }}2(a),(c): the fundamental breathing mode of the helix at (( }}2(a),(c), which is not expected to be excited by primary-fluid flow. Thus, the observed low-frequency response is likely a combined structural mode of the TF-2 tubing and support configuration. Based on the data evaluation herein, including the observations above, FEI excitation of the HCSG tubes did not occur throughout the entirety of TF-2 FEI testing. This conclusion is largely based on the lack of amplification of responses within the assumed primary bending mode frequency ranges and is further reinforced by the low levels measured across the entire frequency span of interest. If FEI were present, one would expect to see a significant increase or emergence of sharp peaks in the first-mode bending frequency range ((( }}2(a),(c)). Table 3-14 shows that the actual FEI data contains no such amplification; values generally trend upward with flow, but in some cases even decrease at the maximum primary flow rates. Figure 3-40 plots the data from TF-2 and it is clear that an exponential increase in vibration levels at higher flow rates was not observed, as would be the case if the critical velocity were reached. Furthermore, the points at which elevated vibration levels were observed at elevated flow rates can be correlated to the low-frequency, secondary-side effect noted above. Even after accounting for a sub-optimal test setup (TF-2 size limited to Columns 1-5, i.e., shortest spans, ((

                    }}2(a),(c) recording length, and sensor locations), the lack of first-mode response escalation indicates the fully-prototypic HCSG design is not susceptible to FEI excitation within its normal operating parameters.

3.5 TF-3 Build-out Modal Testing For CVAP validation testing, NuScale has elected to construct the prototypic test facility (TF-3) with five tube columns of identical geometry as Columns 9 through 13 of the fully-prototypic design. At the time of the build-out modal testing, TF-3 was partially constructed, with two tube columns complete: Column-13 (outermost) and Column-12. Each column is divided into four plenums, each of which contains sixteen 304/316 stainless steel tubes (64 total tubes per column). The spacing and overlap of the tubes are such that access to the Column-13 tubes is extremely limited; therefore, the in-situ testing was focused on the accessible Column-12 tubes. The HCSG was positioned in a horizontal orientation that could be manipulated to adjust the relative position and azimuth of the tubes, plenums, and supports. Each tube has a (( }}2(a),(c) OD and (( }}2(a),(c) wall thickness. Tube spans between supports for Column-12 are approximately (( }}2(a),(c) (long span) and (( }}2(a),(c) (short span), with an approximate tubing weight of (( }} 2(a),(c) . © Copyright 2018 by NuScale Power, LLC 73

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Testing was targeted at the accessible Column-12 tubes, ranging from the bottom of the HCSG (denoted Span A, FW inlet) to the top (Span AD, MS outlet). The in-situ testing was primarily a discovery task, intended to inform approach and parameters for future regimented testing. As such, emphasis was placed on testing a multitude of span, support, and sensor variations, with less emphasis on repeatability and like-for-like comparisons between spans. Nonetheless, efforts were focused toward consistent, accurate determination of the following variables:

1. Modal parameter estimations including

a. Natural frequency

b. Damping

c. Mode shape(s)

2. Excitation methods

3. Effects of boundary conditions

4. Measurement and signal fidelity A general overview of the HCSG test setup is shown in Figure 3-43, with annotations detailing terminology used throughout the remainder of this report. The sensing chain used for acquisition and analysis is documented in Table H-1.

The general nomenclature used for the test IDs includes a group to identify the sensor(s) azimuth and plenum (accounting for rotation of the pressure vessel), spans, identified as segments between supports (starting with Span A/FW plenum and progressing through Span AD/MS plenum), and the general impact location/direction. These references were modified slightly throughout testing to capture varying conditions and lessons learned, and are specifically denoted in the notes below the tables and figures herein. The individual tests were categorized into six groups by the unique test configuration. These configurations represent unique tubes, spans, and/or components that were tested and can be summarized by the following: A. Single Spans - Single Accelerometer B. Span C - (5) Accelerometers C. Multi-span (C through G) - Single Accelerometer per Span D. Plenum transitions Span A (FW-side) and Span AD (MS-side) - Multiple Accelerometers E. Support and Tube Testing F. Support Only Note: the testing conducted as part of Group E included characterization of responses from both support(s) and tubing. Upon further analysis, these responses offered sufficient characterization of lower-frequency modes impacting the supports, such that the Group F tests could be regarded as redundant. Therefore, the Group F data is not analyzed further. © Copyright 2018 by NuScale Power, LLC 74

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-43 General layout of helical coil steam generator prototype for vibration testing 3.5.1 Data Acquisition and Test Methods Modal testing to characterize the HCSG tubing and support parameters was conducted n impulse excitation from an instrumented hammer with various accelerometer configurations to measure the ensuing response(s). The vibration data was recorded primarily in the frequency domain and for select tests, in the time domain. The following acquisition parameters were used: © Copyright 2018 by NuScale Power, LLC 75

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-16 Acquisition parameters for time and frequency domain Domain No. Samples Resolution Ending Time Linear Averages Time (sec) (( }}2(a),(c) Frequency (Hz) (( }}2(a),(c) During the acquisitions, a force (impact hammer) and exponential window for the input was applied. The force window value was assigned unity over the leading five percent of the time record following the initial impulse trigger, followed by a cosine taper to zero for the remainder of the time record (eliminating noise). An exponential window was also applied and set to unity (identical to that applied to the response accelerometers) for all frequency domain calculations. Because the exponential window was set to 1.0 at the end of the acquisition (i.e., no amplitude effect), no corrections for damping are needed as the force/input signal was unaltered for the period of application. Frequency response functions (FRFs) were calculated by the Fourier spectrum of the acceleration response divided by the Fourier spectrum of the excitation force (impact hammer). Four FRF averages from four separate impacts were used to calculate these results; this number of averages was determined experimentally, and represents the best compromise for maintaining consistency of response peaks while reducing noise at non- responsive frequencies. The acquisition duration (typically 4 seconds) and tube damping resulted in a reduction of amplitude to (( }}2(a),(c) of the maximum imparted response. This is sufficient to reduce window leakage in FFT computations. Leakage is a signal processing bias error due to the limited definition of a periodic waveform or transient over the sampling period. The error is leaked across all spectral lines and over the entire frequency range representing noise and reducing signal-to-noise ratio of the measurement. Given the limited time available, windowing was not completely optimized during this initial testing. Future testing should apply an exponential fit that can be used to define a time constant/end value of the exponential window to improve the overall signal-to-noise ratio (especially for less predominant modes). A soft hammer tip with a mass extender was used for excitation. The soft tip is used to spread the force energy (pulse width) over a longer time and excite lower frequencies. The combination of hammer tip and impulse energy (mass extender, impact velocity) describe the force input used for modal parameter estimation. Any changes to these variables will affect modal parameter estimation. Spectral coherence was calculated for each FRF, estimating the relation between two signals (input/hammer vs. the response). These values range from zero to one over the frequency range of interest, where one represents a perfect correlation. Values less than one can be attributed to several factors:

Anti-resonance locations or locations where the FRF value is close to zero
Resonance locations (FRF peaks) where the effect of leakage is pronounced. Note windowing reduces leakage and does not eliminate it.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

The measured response contains contributions caused by extraneous noise, non-linearity, or other forces not contained in the measurement input.
Impact locations/directions were slightly altered between averages.

The coherence metric was used to define various useable frequency ranges for the analysis groups; generally, values greater than (( }}2(a),(c) were considered acceptable. Modal parameters, especially when used for analytical modes, are considered global structure properties. However, the tube and HCSG support structure has a combination of local and global modes. The local modes or those specific to a span have difficulty transferring across a sufficiently stiff boundary. These modes typically require local excitation and measurement to characterize, similar to the single span testing. For multi-span, tube and component testing, the stiffness of this boundary or tightness of supports change between each span and each support from fixed to relatively free. This results in varying levels of energy transfer across these boundaries and the measurement of both local and global modes between supports, tubes, and spans. Mass loading of the structure can affect modal parameter estimation. The weight of an individual accelerometer used for this testing is (( }}2(a),(c) ounces and the cable is (( }}2(a),(c) (not including conductor). This compares to about (( }}2(a),(c) percent mass loading across a long span for a single accelerometer (most tests herein) and between (( }}2(a),(c) percent for five accelerometers (depending on the cable length left suspended). This effect will be discussed further when using multiple accelerometers to characterize a mode. 3.5.2 Analytically Predicted Modes Section 5.1.2 contains a summary of modal predictions for Columns 9 and 13 (innermost and outermost of the TF). These modes are summarized below for comparison to the ensuing results presented herein. The lower end of the range represents the frequency for Column 9 and the upper end of the range is the frequency for Column 13.

Highest mass participation in the vertical direction o (( }}2(a),(c) (pinned boundary conditions) o (( }}2(a),(c) (fixed boundary conditions)
Highest mass participation in the horizontal direction o (( }}2(a),(c) (pinned boundary conditions) o (( }}2(a),(c) (fixed boundary conditions)

For the in-situ testing that was conducted, there is good agreement for the first predominant mode in the vertical direction, which is more closely approximated by a fixed boundary condition (generally reported herein in the (( }}2(a),(c) range). Similarly, the predominant horizontal mode from testing was most often present in the (( }}2(a),(c) range. © Copyright 2018 by NuScale Power, LLC 77

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.5.3 Frequency Response Function Analysis Table H-1 summarizes testing parameters, sensor locations, and configurations used during the acquisition. FRF calculations from 0-400 Hz for each group of tests is provided in Figure H-1 through Figure H-31 of Appendix H. The following sub-sections discuss the FRF results for each of the groups. Group A: Single Span - Single Accelerometer On the first day, several initial tests were conducted on individual tubes, altering various acquisition parameters to identify an acceptable set for repeat testing. A typical acquisition is as demonstrated in Figure 3-44 for these tests. A subset of tests was selected for this group to illustrate the analysis over a simplified number of responses. A single long span (Span C, first long span after FW plenum) was tested, with the resulting FRF shown in Figure 3-44. The FRF and coherence is overlaid to demonstrate a spurious response (highlighted in yellow) along with the evident response peaks (((

                         }}2(a),(c), highlighted in gray). The FRF response is also slightly skewed, especially at the lower frequency peak. Both effects are indications of non-linearity. This is also likely an effect of multiple closely-spaced modes, as detailed in Group B test responses (refer to the following section).

Another test was conducted to enhance the resolution of mode shapes using a roving response test and Maxwells reciprocity. Twelve roving FRF measurements along a single span are shown in Figure 3-45 using a single impact location. The use of reciprocity and roving to define a mode shape assumes the structure is dynamically symmetric. The combination of mass loading (albeit to a lower extent) and non-linearity negated the principals assumed for reciprocity, with the peaks shifting between measurements. For this reason, roving response tests were not used for further analysis, and are not recommended for any subsequent testing. Use of non-tubing impact excitation locations (e.g., supports) and reduced acquisition periods (i.e., one second) allowed for further characterization of lower frequency modes. The reduction in the acquisition period (from (( }}2(a),(c)) reduces the averaged noise (if present) in the signals and computed FRFs, but also adversely affects the frequency resolution (increased bin sizes from (( }}2(a),(c)), which, in turn, affects the accuracy of damping calculations in the frequency domain such as half-power. As shown in Figure 3-46, a (( }}2(a),(c) mode (normally where low coherence prevents characterization) was captured using a smaller time window to reduce the noise following the transient. It is not clear if the removal of the ring supports for this test also affected the improved coherence at lower frequencies. The discussion of Group E will also describe the lower modes excited from support locations. The variation of responses along spans is evident throughout the testing where various modes became difficult to excite repeatedly. Variation was mainly attributed to the boundary conditions (HCSG support tightness ranged from fixed to some variety of pinned), impact energy (direction/magnitude), and non-linearity. Not all modes were excited and in general the lower frequency modes (below (( }}2(a),(c)) were the most difficult to excite consistently. © Copyright 2018 by NuScale Power, LLC 78

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-44 Typical single, long span vertical; frequency response function (blue) and coherence (orange) ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-46 Lower frequency response (below 25 Hz); frequency response function (blue) and coherence (oOrange) Group B: Span C - Five Accelerometers This group of tests entailed instrumentation of one span (Span C, first long span after FW plenum) with five equally-spaced accelerometers. The span was rotated during the tests from a bottom-azimuth orientation (4:00-5:00), to the side (2:30-3:30), and the top (11:30 to 12:30). The primary purpose of this test group was to determine the effects of varying boundary conditions based on vessel rotation/azimuth (i.e., compression applied by support rings), and allow for improved mode shape characterization by multiple accelerometer locations. Generally, there were three frequency response ranges of interest: ((

                                                }}2(a),(c). Rotation of the RPV or HCSG caused a slight shift among the responses. Shifts within the FRF peaks were mostly bounded within

(( }}2(a),(c) (depending on the mode). The lower frequency modes (between (( }}2(a),(c)) were predominantly in the vertical direction, while the largest-amplitude FRF responses were in the horizontal direction (between (( }}2(a),(c)). The location of the impact (near each end and mid-span A summary of the FRF results during this testing are shown in Table 3-17 and the FRFs are plotted for each test in Appendix H, Figure H-3 through Figure H-13. Impact locations mid-span produced improved characterization for the first predominant mode and impact locations near the ends of the span offered the best characterization across the upper modes. The latter is demonstrated by a mid-span and end-impact for tests 1A-3Z and 1A-5Z. Additionally, the direction of the impact improves the © Copyright 2018 by NuScale Power, LLC 80

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 characterization for predominant horizontal and vertical modes, however, both impact directions result in detecting the same modes. The improved characterization is a result of a majority of the overall energy imparted into the tube directed along the impact axis (e.g., y-vertical, z-horizontal), resulting in a higher signal-to-noise ratio of the responses for modes predominant in the impact direction. The coherence between the input and output were generally calculated above 0.9 over the frequency range of (( }}2(a),(c) as shown in Figure 3-47 (below). Table 3-17 Group B, span C (5) accelerometers ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                                   }}2(a),(c)

Figure 3-47 Coherence only for test 1C-1Z (horizontal/1Z and vertical/3Y direction) ((

                                                                                                                   }}2(a),(c)

Figure 3-48 Impact location effects on Span C (left: mid-span; right: near end of span) Note for Figure 3-48: Both impacts measured all five locations and the impact was imparted in the horizontal direction at two locations, midspan (location 3) and near the support (sensor location 5). © Copyright 2018 by NuScale Power, LLC 82

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Group C: Multi-span (C through G) - Single Accelerometer per Span This group of tests entailed instrumentation/characterization of five spans (C, D, E, F, and G), each with a single accelerometer mounted mid-span. Spans D and F represent a short span ((( }}2(a),(c)) whereas Spans C, E, and G are long spans ((( }} 2(a),(c)). The set of spans was also rotated from an azimuth where Span C was orientated at 06:00 (BDC) and Span G was at 12:00 (TDC) to where Span C was oriented at 09:00 and Span G was at 03:00. The primary purpose of this group of testing was to determine the effects of changing boundary conditions through rotation and the variations in local modal parameters between like spans. Generally, two modes were present in the first orientation (( }}2(a),(c). Excitation was limited to the longer tubes with no consistent presence or dominating frequency between the long spans and short spans. These frequencies increased ((

                }}2(a),(c) during rotation elevating to ((                           }}2(a),(c). Both lower modes were clearly responding for each long span with the lower mode mostly clearly represented from Span E impacts. It is unclear if the two modes were influenced by boundary conditions as the end conditions were quite similar among the spans. The lower modes (((
                   }}2(a),(c)) were predominant in the vertical direction for this testing.

The next set of predominant modes was at (( }}2(a),(c); these also shifted by 2 Hz after the rotation. The last set of modes near (( }}2(a),(c) (predominant within a group of closely spaced modes) was shifted by approximately (( }}2(a),(c) upon rotation. The mid-span location demonstrated primarily vertical predominant modes over these upper frequency ranges. A separate test was also conducted within Span E (3C-EmsZ), where tubes 2, 6, 10, and 14 were tested with single mid-span accelerometers, impacting tube 6. The first mode frequencies ranged from (( }}2(a),(c). A single tube excitation was effective in exciting the first mode in adjacent tubes, albeit with elevated noise and elevated modes were no longer discernable. A summary of the FRF results during this testing are shown in Table 3-18 and the FRFs are plotted for each test in Appendix H, Figure H-13 through Figure H-21. © Copyright 2018 by NuScale Power, LLC 83

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-18 Group C, multi-span ((

                                                                                                          }}2(a),(c)

Notes: 1. Test ID references azimuth of Spans, 2A (C-12:00, G-6:00), 2C (C-9:00, G-3:00), 3C (E-12:00)-Impacted Span on FW or MS side of span in the z-horizontal direction). © Copyright 2018 by NuScale Power, LLC 84

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The coherence between the input and output were generally calculated above (( }}2(a),(c) over the frequency range of (( }}2(a),(c), as exemplified by Figure 3-49. ((

                                                                                                                  }}2(a),(c)

Figure 3-49 Coherence only for test 2A-EfwZ (vertical and horizontal direction) The majority of FRF peaks are present not only in one FRF or span, but across each of the individual spans, even though each span exhibits localized modes (long and short spans). The energy transfer across spans (cross-communication) was investigated using both the FRF magnitude and coherence of the input (hammer) and response signals on each span. From a single test impacting the center span of Span E, two modes were excited ((( }}2(a),(c)). From this test alone, it is unclear which mode is local to Span E or if both are local. As shown in Table 3-19, the first predominant mode at (( }}2(a),(c) is dominate in Span E (impact location) at more than five times the response (g/lbf) of the other responses, but the peak is present in three out of four of the adjacent spans at a reduced magnitude. This FRF peak occurs on similar span lengths (i.e., Spans C, E, G) at (( }}2(a),(c) of the impacted spans FRF response magnitude, which suggests a similar local mode is present along the spans although not properly excited. For the (( }}2(a),(c) peak there is clearly amplification on Span G (FRF magnitude six times that of Span E) and very slight amplification on Span C (albeit with low coherence) indicating a clear resonance near this frequency for Span G. The presence of local modes specific to a span and the identification of modes cross-communicating from adjacent spans is only clear when analyzing the FRFs across multiple spans in a single test. The ambiguity in response (i.e., multiple closely spaced peak responses at each sensor) is more clearly identified by local exaction to each span while measuring adjacent spans. © Copyright 2018 by NuScale Power, LLC 85

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Utilizing Figure 3-50 (below), three FRFs for each span are provided for three impact locations (Span E, top left; Span C, top right; Span G, bottom right). All five span responses are plotted for each impact (C, D, E, F, and G) varying by color. Coherence is plotted for the Span E impact test (lower left). From all these tests it becomes apparent there are multiple closely-spaced modes between (( }}2(a),(c) which are not easily distinguished in these tests. For Span E, there is a predominant mode at (( }}2(a),(c). For Span G, the predominant mode is at (( }}2(a),(c). A comparison of boundary conditions between spans does not explain the differences in the predominant mode responses. The HCSG supports are relatively the same tightness for Span C and Span E (cumulative relative tightness of 5), while Span G was slightly looser (cumulative tightness of 6. Each end of the span was tested by hand to determine the relative tightness of the support on a scale of 0-5, where 0 was nearly a fixed boundary and 5 was very loose. The algebraic sum from each end of the span is reported here as the cumulative tightness.). Although clear peaks in the FRF response can be seen from Spans E and G (whether they were impacted directly or not), The Span C response was much less clear or pronounced and even when impacted directly (upper right plot, Figure 3-50), poor responses were measured. This span would require additional testing to fully characterize the FRF response and it appears the span was not properly excited with cross-communication from modes on Span E and Span G dominating the response. In addition, modes below 140 Hz were not excited on short spans (D and F), which may be because of lack of excitation local to each span (i.e., impacts were only completed on long spans). Table 3-19 Energy transfer across spans ((

                                                                                                                  }}2(a),(c)

Notes: 1. Impact location was on FW side of Span E with responses measured across five spans (C, D, E, F, G) by single mid-span accelerometer. FRF magnitude and coherence are provided for this test across two peak FRF responses at (( }}2(a),(c). The input/output ratio is the ratio of FRF amplitude from Span E (closest to excitation source) to adjacent span FRF responses to quantify amplification and attenuation. © Copyright 2018 by NuScale Power, LLC 86

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-50 2A-EfwZ energy transfer across spans Group D: End Spans (A and AD) - Multiple Accelerometers This group of tests characterized the response of the end spans (transition bends) on both the top and bottom of the HCSG (FW and steam plenums), for the shortest and longest tubes within each of these spans. These spans are fixed on one end (plenum orifice) and supported by the HCSG supports on the other end. The tubes were excited by a hammer impulse on each tube and on the HCSG support. Predominant measured frequencies are summarized in Table 3-20. © Copyright 2018 by NuScale Power, LLC 87

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-20 End span (A and AD) frequency response function summary ((

                                                                                                                        }}2(a),(c)

Notes: 1. Test ID reference indicates Span (4A-spanA and 5A-span AD)- impact sensor and direction. Two sensors were placed on the shorter tube (1) and three sensors were placed on the longer tube span (15 or 16). Comparing the short sections at each end of the HCSG, the FW side (4A-2Z) shows the predominant responses in the (( }}2(a),(c) range, whereas the MS side (5A-2Z) shows the first set of predominant frequencies lower ((( }}2(a),(c) range). This is likely a cause of the boundary conditions where one end is fixed and the other simply-supported end is tighter on the FW side when compared to the MS side. Additionally, the unsupported length of each tube at the transition to the plenums is different, leading to differences in the measured frequencies. A predominant response from the support was also measured at (( }}2(a),(c) and present on the shorter tube. Using a separate sensor affixed to the support (#6, Test 5A-Support6Z) and impacting that support, the (( }}2(a),(c) response was clearly evident on the support sensor and through cross-communication was also observed on the shorter tube response (sensors 1 and 2). Excitation of the support and tube resulted in similar responses in the lower frequency range ((( }}2(a),(c)); responses were muted above those frequencies when not directly excited at the tube. The fixed-end on these spans offered very clean responses and high signal-to-noise ratios. All modes were excited in the horizontal direction, which also corresponded to the largest energy response. Coherence between the signals was generally above (( }}2(a),(c) over the frequencies (( }}2(a),(c) as shown in Figure 3-51 (below). This coherence plot represents the best input/output relationship among all tests conducted, with a value of nearly 1.0 across the entire frequency range. Also, the plot exhibits little evidence of noise and cross-communication at FRF peaks, and a much more deterministic response below (( }}2(a),(c). © Copyright 2018 by NuScale Power, LLC 88

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                              }}2(a),(c)

Figure 3-51 Coherence only 5A-5Z (horizontal and vertical direction) Notes: 1. Vertical coherence (4Y, midspan of tube 16) compared with the impact hammer (999Z) and horizontal coherence (5Z, near the first support) compared with impact hammer (999Z). Group E: Support and Tube Testing Group E entailed testing of the HCSG support and tubing as one structure. Seven equally-spaced accelerometers were placed along the vertical axis of a support and mid-span accelerometers were placed on adjacent tubes. This group of tests is unique from other groups in that the support was impacted and used to excite modes within the tubes. In addition, the boundary conditions were unique in that the seven support rings were removed for these tests. The testing configuration is shown in Figure 3-52. Four tests were conducted, first measuring three adjacent tubes (1, 5, 9) impacting the support in the axial (tube direction) and the horizontal (z-direction). The next two tests instrumented tubes 1, 2, 5, 6, 9, 10, 13, and 14 representing the majority of the sixteen tubes across Span E. In addition, a larger hammer (1 mV/lbf compared to the smaller 5 mV/lbf) was used to excite the tube and support structure. A summary of the FRF results is presented in Table 3-21 for the four tests in this group. Overall, the signal-to-noise ratio decreased for this testing as the energy transferred through the support to the tubes was as much as two orders of magnitude less than other FRF peaks (FRF peaks on the order of (( }}2(a),(c)). A relatively weak axial tube mode (lowest FRF magnitude of Group E) was detected at (( }}2(a),(c) Hz for the initial axial impact direction (Sup-103 + Col-12, Span E Tub 1+5+9, Impact 1-X) and became less prominent in the second test in the same impact direction (Supp-to-Tube 103 Span E FW-X ) due to elevated noise in the lower frequencies. The FRF magnitude was © Copyright 2018 by NuScale Power, LLC 89

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 similar between the support and tube response indicating a global mode. When impacting in the horizontal direction a (( }}2(a),(c) mode was excited again in the axial direction (Sup-103 + Col-12, Span E Tub 1+5+9, Impact 1-Z) and present in nearly all measurement directions (likely a local mode from the support). In general, axial and horizontal modes were detected at (( }}2(a),(c) across all tests most likely originating as local modes from the support because there was little to no variance for each tube and the magnitude of the FRF response were largest on the support (except for (( }}2(a),(c)). Most of the tubes tested exhibited predominant vertical modes between (( }}2(a),(c) with some outliers detected up to (( }}2(a),(c). Coherence was above (( }}2(a),(c) over the lower frequencies mostly due to the different method of excitation, as shown in Figure 3-53. ((

                                                                                                           }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 3-21 Support and tube frequency response function summary ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                             }}2(a),(c)

Figure 3-53 Coherence for test Sup-103 + Col-12, Span E tub 1+5+9, impact 1-X Notes: 1. Provided in axial (901x-direction), vertical (901y-direction) and horizontal (901z-direction) 3.5.4 Damping Estimation 3.5.4.1 Half-power Method for Damping Estimations A global polynomial curve fit was used to approximate damping using the half-power method. The curve fit was applied over multiple FRFs (all valid sensors per impact test) to calculate a global fit per measurement direction. The fit was applied over discrete frequencies to increase the accuracy of the fit function as shown in Figure 3-54. Figure 3-54 represents the FRF magnitude (g/lbf) in the top plot and the bottom is the imaginary part (log-scale) of the FRF used to identify peaks for fitting. Due to noise within the FRFs, a filter was applied to report damping values greater than (( }}2(a),(c). The removal of those peaks shifted the average value from (( }}2(a),(c). Damping estimations were calculated for each group and represent various FRF peaks. These are plotted in Figure 3-55. The range of damping values is ((

                    }}2(a),(c). Multiple closely-spaced peaks coupled with non-linear FRF responses resulted in broadening FRF peaks used to calculate damping with the half-power method.

This effect is well demonstrated for peak damping values of ((

                    }}2(a),(c) in Figure 3-56.

Based upon the 250 damping values, a 95 percent confidence interval describing the average damping over the reported frequency range using the half-power method is expected to be between (( }}2(a),(c). Similarly for a 95 percent confidence interval, a single damping value (not an average) from the tube would be expected to fall between (( }}2(a),(c). Because more impact © Copyright 2018 by NuScale Power, LLC 92

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 hammer tests were performed than pull tests, these statistics are skewed towards representing damping due to small amplitude vibration (TB) rather than the larger amplitude vibration expected from strongly-coupled phenomena such as VS and FEI. ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-55 Half-power damping estimations over all frequency response function groups ((

                                                                                                          }}2(a),(c)

Figure 3-56 Peak damping values ((( }}2(a),(c):1C-1Y-left and (( }}2(a),(c):1A-3Z-right) 3.5.4.2 Exponential and Log-decrement Methods In addition of the half-power methods, the exponential and log-decrement methods are also assessed. Exponential Fit An exponential curve is fitted to subsets of the 45 positive peaks. The exponential fit assumes a decay of the positive peaks in the form of where is the damping ratio, is the estimated natural frequency of the considered data, and is time. Subsets of the positive peaks are used to calculate the exponents coefficient. The subsets include © Copyright 2018 by NuScale Power, LLC 94

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 positive peaks in groups of 5, 9, 13, 17, and 21 positive peaks per data block. These are referred to as runs in the following text. For each of these runs, an exponential fit is performed starting with the first peak (i.e., 1 of 45) and the exponential coefficient ( ) recorded. The run is then shifted to the second positive peak (i.e., 2 of 45) to calculate a new exponential coefficient, then the third peak, and so on. The calculated exponential coefficient is divided by the runs corresponding natural frequency estimate to determine a damping ratio estimate. Because the natural frequency may change with amplitude the natural frequency estimate for each run is calculated as ( )

                                            =                                                   Equation 3-11

( ) ( ) By developing a damping ratio estimate at various initial peaks, an amplitude dependent damping ratio estimate can be obtained. Logarithmic Decrement The logarithmic decrement is calculated as:

                                                         =                                   Equation 3-12 where  is the logarithmic decrement,  is a maxima free vibration displacement amplitude (i.e., one of the 45 positive peaks), and                      represents the maxima free vibration displacement amplitude measured  periods from  . The damping ratio is then written as:
                                                         =                                     Equation 3-13 The damping ratio is calculated for an array of initial peaks and subsequent peaks (i.e.,

the Ns). The exponential fit and logarithmic decrement damping estimates from three processed displacement time histories are overlaid and shown in Figure 3-57. The three displacement time histories come from the 315-12-1-C-6 (5y) time ((( }}2(a),(c) filter), 2A-EfwZt_8Y ((( }}2(a),(c) filter), and 2A-GfwZt_10Y ((( }}2(a),(c) filter) data sets. Note the frequency range of interest for the three data sets centered around (( }}2(a),(c). The three impact tests are bounded by tube displacements less than 2.5 mils. The majority of oscillations used for damping calculations are less than 1 mil. These amplitude ranges are expected to be most representative of the TB mechanism. The data shown in Figure 3-57 is the raw data from both the exponential fit and logarithmic decrement. As such, it contains various N values because each N value for a time history is associated with an amplitude value. The damping values in Figure 3-57 that are significantly above or below the mean (Figure 3-58) are generally due to low N values. The negative damping values in both the exponential fit and logarithmic decrement methods (Figure 3-57, Figure 3-59, and Figure 3-60) are attributed to filtering, which resulted in positive peaks having lower displacement amplitudes than the subsequent peaks. The damping ratios greater than 1.5 percent correspond to the amplitudes associated with N=1 and N=2. © Copyright 2018 by NuScale Power, LLC 95

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-57 Amplitude-dependent damping from three time histories (raw): exponential fit - blue; log dec - red 3.5.4.3 Amplitude Dependency Three vibration mechanisms are prone to the HCSG tube design include buffeting, VS, and FEI. These mechanisms are expected to manifest at differing amplitudes if excited during operation. Ranking the mechanisms from the expected smallest amplitude to the largest: TB, VS, FEI. Amplitude dependency was not a specific focus of the initial testing. The various tests were post-processed into displacement units and a best effort was applied to evaluate the effect of amplitude dependency. Figure 3-58 shows a processed version of the data from Figure 3-57 where the damping estimates at each amplitude are averaged and then plotted. For example, all 20 logarithmic decrement damping estimates for a given displacement amplitude are averaged together and the average is plotted. There is a clear trend of damping increasing with response amplitude for both methods. © Copyright 2018 by NuScale Power, LLC 96

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                              }}2(a),(c)

Figure 3-58 Amplitude-dependent damping from three time histories (averaged): exponential fit

               - blue; log dec - red While most of the data was collected with an impact hammer one pull test was performed, and the output recorded. The tube was physically displaced by hand, released, and allowed to undergo free vibration.

A plot of displacement amplitude versus damping using the exponential fit and logarithmic decrement methods are shown in Figure 3-59. Figure 3-60 overlays the damping data from the pull test to the damping data to the three previously discussed time histories. Peak displacement responses used for damping are roughly (( }}2(a),(c) mils and represent the largest damping values calculated, up to (( }} 2(a),(c). Figure 3-60 shows that even neglecting the first (( }}2(a),(c) positive peak data points from the pull test (starting near (( }}2(a),(c)), the pull test indicates more damping than the three tests noted above. © Copyright 2018 by NuScale Power, LLC 97

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-59 Amplitude-dependent damping from pull test: exponential fit - blue; log dec - red ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.5.5 Mode Shapes A geometry file of a single tube and HCSG supports was used to evaluate specific mode shapes for Group B (Span C). Group B was chosen because it was unique in providing five measurement locations to fully define mode shapes, whereas other tests specifically focused on FRF responses with a single mid-span location. An overview of the five locations and FRFs used is provided in Figure 3-61. For the mode shapes, points between the measurements were interpolated and the points on the end ((( }}2(a),(c)) were fixed. There are three frequency regimes of interest near ((

                   }}2(a),(c). The first mode analyzed is predominant in the vertical direction. The second and third modes are most predominant in the horizontal directions while still contributing slightly in the vertical direction.

The first predominant mode is represented as multiple, closely-spaced peaks within in the FRF. Two modes were chosen to evaluate the mode shapes: 1) (( }}2(a),(c) representing a broad smooth peak, and 2) (( }} 2(a),(c) representing a sharp FRF peak. The mode shapes (shown both deflected and non-deflected) are provided in Figure 3-62 and Figure 3-63. These figures show very similar mode shapes between the closely-spaced modes predominant motion in the vertical directions and much less pronounced motion horizontally. In addition, very little motion is occurring in the axial direction. These modes most closely represent the first bending mode of a simply supported or fixed-beam. The second predominant mode near (( }}2(a),(c) represents the largest FRF response. Again, multiple peaks are present near this mode as closely-spaced modes. A predominant horizontal mode is shown in Figure 3-64. This mode is best characterized as a second bending mode of a beam with the mid-point relatively motionless. The third predominant mode near (( }}2(a),(c) is one of many peaks between (( }}2(a),(c). This peak was chosen consistent with its relative response in all directions. The predominant horizontal mode shape is shown in Figure 3-65. The mode is best characterized as a third bending mode of a beam with two inflection points. Because a single test (1C-1Z) was used to develop all mode shapes, a comparison to another test (1A-5Z) was used to quantify variability. Figure 3-66 shows two mode shapes for qualitative comparison. These shapes are very similar even at two frequencies and two different tests ((( }}2(a),(c)). A quantitative evaluation using a modal assurance criterion (MAC) value demonstrates very consistent mode shapes (MAC value (( }}2(a),(c)). A MAC value is a statistical indicator for correlating the complex vectors for nodes pairs between two tests (amplitude and phase). The indicator is most sensitive to large differences and relatively insensitive to small differences in mode shapes making it ideal for use in empirical testing. The numeric correlation is bounded between 0 and 1, with 1 indicating fully consistent mode shapes. A value near 0 indicates the modes are not consistent. © Copyright 2018 by NuScale Power, LLC 99

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-61 1C-1Z, Span C, 5 accelerometers (frequency response function, axial-red, vertical-green, horizontal-blue) ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 3-63 Mode shape for 1C-1Z at (( }}2(a),(c) ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                             }}2(a),(c)

Figure 3-65 Mode shape for 1C-1Z at (( }}2(a),(c) ((

                                                                                                             }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 3.5.6 Build-Out Modal Testing Conclusions Five groups of tests were completed to characterize frequency response, damping, and mode shapes. The individual test configurations for all tests in this report are summarized in the test matrix in Table H-1. Local modes for various span lengths and boundary conditions resulted in three predominant modes over a range of frequencies for the majority of tests. The first predominant mode ranged from (( }}2(a),(c) with one exception in Group A and those in Group E. Excitation of the HCSG support showed measurements on the adjacent tubes to have multiple low-frequency FRF peaks between (( }}2(a),(c) (these tests had support rings removed). The FRF peaks specific to supports also introduced lower modes between (( }}2(a),(c) for Group E. Lower modes below (( }}2(a),(c) were difficult to excite and not present in responses for Groups B, C, and D. A summary of frequency ranges over predominant modes for all testing groups is provided in Table 3-22. Table 3-22 Frequency response function summary per group ((

                                                                                                          }}2(a),(c)

Modes were excited more clearly within the measured FRFs when excited mid-span for the first predominant mode and near the ends for the second and third predominant modes. The influence of local modes unique to each span and boundary condition in the HCSG creates additional complexity in evaluation and multiple tests may be required to discern specific modes within each span. With impact excitation, the data suggests modes can be excited up to one adjacent span of similar length from the excitation source. Fixed-end conditions, or nearly fixed-end, offer the best location for impact testing and elevated signal-to-noise ratios. Multiple methods were used to calculate damping with the following trends:

Half-power method exhibited the largest variance

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

Logarithmic decrement can improve variance using the 3rd peak and subsequent peaks to calculate
Half-power generally produced higher estimates when compared to logarithmic decrement
Logarithmic decrement has issues resolving damping for upper modes

((( }}2(a),(c)). It is noteworthy that FEI is expected to be predominant for the first-mode bending, or less than (( }}2(a),(c) based on the current testing data and TB and VS are also expected at frequencies below (( }}2(a),(c).

Exponential fit produced generally lower damping values than logarithmic decrement with less variance (evident at larger initial tube displacements).

Amplitude dependency on damping was observed for both logarithmic decrement and exponential damping estimations and can be summarized as follows: o Impact testing was limited to (( }}2(a),(c) of tube displacement with the majority below (( }}2(a),(c). Damping values generally increased with amplitude ranging from (( }}2(a),(c) with a few points between (( }}2(a),(c). o Pull testing for excitation was limited to (( }}2(a),(c) of initial displacement (single test). Damping values were between (( }}2(a),(c) over the ((

                          }}2(a),(c)   range and up to the ((                             }} 2(a),(c)  displacement with an exponential fit. The trend and scatter increased for elevated displacements with a maximum damping (logarithmic decrement) of ((                                           }}2(a),(c).

Mode shapes of Span C characterized the three predominant frequency responses as: o first-mode bending in the vertical direction o second-mode bending in the predominantly horizontal direction o third-mode bending in the predominantly horizontal direction Impact testing provided good repeatability of FRFs across multiple tests. The mode shapes were also repeatable from various locations (i.e., different span locations) of excitation. © Copyright 2018 by NuScale Power, LLC 104

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 4.0 Validation Methodology The validation methodology provides a framework for selecting the aspects of the design analysis program to be validated and establishes or confirms that the experimental design provides sufficient data to validate the necessary aspects of the design analysis program. Pre-test prediction calculations implement the validation methodology. These calculations confirm the adequacy of the experimental scope. This includes identifying optimal test conditions and locations for sensors, and determining a range of expected and allowable experimental results, considering uncertainties and biases, that validate the design analysis. 4.1 Use of Test Data Every measurement has some minor error, that results in a difference between the measured value and the true value. This difference between the measured and true value is the total error that is comprised of two components: random error and systematic error (Reference 9.1.2). Random error varies randomly in repeated measurements throughout the conduct of a test, whereas the systematic error remains constant, for example due to imperfect calibration or data reduction techniques. Accurate measurement requires minimizing both random and systematic errors. The test data received by NuScale will have with it a test equipment error and accuracy report (TEEAR), which provides the estimated value of expanded uncertainty for each recorded quantity (direct and derived). When each test is complete and the TEEAR uncertainty values are available, they will be substituted for experimental uncertainty (uD) as discussed in Section 4.2. 4.2 Methodology Pre-test predictions develop and apply a series of calculations and finite-element models to generate best estimate and allowable responses for the components in the test. The output of the analyses is compared to prototype test results from the vibration and stress measurement program to validate the analytical approach in the design analyses and the margin of safety. The implementation of this methodology is discussed in detail for individual NPM components in the context of the corresponding FIV analysis method in Sections 4.3, 4.4, 4.5, and 4.6. This validation process accounts for the fact that model predictions and analytical methods rely on engineering simplifications, and that test results are inevitably affected by practical differences (see Section 4.6) and instrument uncertainty that introduces errors into the validation process. Equation 4-1 to Equation 4-6 are presented for derivation of the validation approach. Following the logic presented in Section 1-5 of Reference 9.1.2, a predicted value S is compared to an experiment data value D for purposes of validation. The comparison error or discrepancy is:

                                             =                                              Equation 4-1

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The validation comparison error, E, incorporates errors from both the analysis and the test, as shown below. The true value of the variable of interest is denoted as T, so the error in the predicted value, S, is the difference between S and T:

                                             =                                              Equation 4-2 Similarly, the error in the measured value, D, is the difference between D and T:
                                             =                                               Equation 4-3 Using Equations 4-1 through 4-3, the validation comparison error E is expressed as:
                              = ( + )  ( + ) =                                          Equation 4-4 Knowledge of the true value T is not known with certainty, so the application of Equation 4-4 is continued through the definition of additional terms. The errors in the predicted value S are assigned to one of three categories included in the following summation:
                                   =           +       +                                     Equation 4-5 (i)       The error model due to assumptions and approximations in design analysis (ii)      The error num due to the numerical solution of the equations (relevant to complex computer codes, e.g., finite element analysis)

(iii) The error input due to variability in the input parameters to the pre-test analysis. The objective of a validation exercise is to ascertain the magnitude of model to within an uncertainty range. However, this error can be obscured by errors from the analysis solution scheme and/or the error embedded in the pre-test prediction input parameters, as well as the test result error. Re-arranging Equation 4-5 and using Equation 4-4:

                                     = +                                                  Equation 4-6 Equation 4-6 is not solved directly. Once a test is complete and measurement data is collected, the sign and magnitude of E are known from Equation 4-1, but the remaining terms on the right-hand side of Equation 4-6 are not known with certainty. In the Reference 9.1.2 approach, each error term is viewed as a single realization from a parent probability distribution. The standard deviation of each parent population (also called standard

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 uncertainty) corresponding to these errors is taken as uD, unum, and uinput. Thus, the standard uncertainty associated with the estimate of model is expressed as a validation uncertainty as follows:

                                     =        +         +                                    Equation 4-7 Consequently, Equation 4-6 and the range defined in Equation 4-8, characterize an interval within which model falls. Therefore, the determination of the validation comparison error E provides a direct assessment of the prediction error with uval as the validation standard uncertainty.
                                               +/-                                               Equation 4-8 4.3      Validation Approach and Uncertainty Analysis Based on the validation methodology described in Section 4.2, the uncertainty analysis applies the following guidelines, with Equation 4-8 as the basis for the validation exercise in the post-test analysis:

If the absolute value of the validation comparison error E is much greater than the validation standard uncertainty uval, then model is approximately equal to E (i.e., it accounts for most of the observed difference between analysis result and test data).

In this case, there is an incentive to enhance the accuracy of the analysis to reduce model error.

If the absolute value of the validation comparison error E is less than or equal to uval, then model is within the noise level created by uncertainties in the solution scheme, inputs, and test data used to perform the validation. In this case, there is small benefit to pursuing model improvements to achieve better accuracy.
If uval is identified with a particular family of probability distributions, then a confidence interval can be defined. For instance, assuming (input+num-D) is from a Gaussian distribution, the expanded uncertainty with 95 percent confidence is U95 = 2 uval.

Thus, (E +/- U95) provides an interval in which model resides about 95 times out of 100. The following sections provide the detailed methodology for calculating the validation metrics E and uval for each of the FIV phenomena examined in the measurement program. uval is calculated in the pre-test prediction and E cannot be finalized until the post-test analysis, when errors in the measured values can be assessed. uval is also used in the pre-test prediction to inform the expected and allowable range of experimental results that validate the design analyses. © Copyright 2018 by NuScale Power, LLC 107

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 4.3.1 Propagation of Uncertainties into a Result Engineering variables of interest are often functions of other variables based on a well-known mathematical relationship. In this validation methodology, the engineering variables of interest are the safety margins associated with the onset of an FIV phenomenon or other FIV results such as the fatigue margin for a SG tube. The effect of random standard uncertainty in the constituent variables, denoted as uXi, is approximated by the Taylor series method (Reference 9.1.2). Consider a result R expressed in terms of the average or assigned values of the independent parameters Xi that enter into the result. That is,

                                        = ( ,  ,  ,  )                                    Equation 4-9 Where I signifies the total number of parameters involved in R. When there is a known mathematical relationship between the result and its parameters, sensitivity coefficients i are calculated by partial differentiation (Equation 3-2-2 of Reference 9.1.2):
                                              =                                               Equation 4-10 The absolute standard uncertainty of the result is calculated based on square root sum of squares of each uncertainty term, as follows:
                                       =        (  )                                        Equation 4-11 An alternative to partial differentiation by analytical derivation is to use central finite differences. This implies that the sensitivity coefficients are calculated as shown below:

(. . , + , . . ) (. . , , . . )

                        =                                                                     Equation 4-12 2

It is implicit that the sensitivity coefficient in Equation 4-10 is evaluated at the nominal value of the parametric vector. Note that many design analysis input parameters have been biased to be conservative (versus best-estimate or nominal). Therefore, care is taken in the pre-test prediction to use best-estimate inputs in the absolute standard uncertainty calculation to ensure an appropriate range for the expected measurement results is obtained. If using Equation 4-12, a choice is made to set the value of the perturbation size Xi. If Xi is too large then truncation error is large, so a practically small value is © Copyright 2018 by NuScale Power, LLC 108

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 recommended. It is often useful to set Xi equal to the ratio of the variables standard error to its nominal (mean) value. 4.3.2 Calculation of Input Parameter Uncertainty Based on the guidance in Reference 9.1.2, there are two different approaches for estimating uinput. The approach depends on whether a local or global view of uncertainty estimation process is followed. In this report, both are presented as valid options because of the diversity in the FIV phenomena and their analytical methods, and to provide flexibility for the analyst when performing pre-test analysis. 4.3.2.1 Local Method An analysis prediction S with np uncorrelated input parameters is effectively a result developed from the arithmetic construction or manipulation of the underlying input parameters. Hence, the same uncertainty propagation method discussed in Section 4.3.1 is used to evaluate uinput, namely: Equation 4-13

where uXi is the standard uncertainty in input parameter Xi. Ideally, uXi should come from prior experiments, although engineering judgment may be accepted instead to estimate it or may require validation based on the measurement program results. 4.3.2.2 Global Method The sensitivity coefficient method presented in the preceding section is termed local sensitivity and uncertainty propagation because the function evaluations are in a narrow (local) neighborhood of the mean parameter value. This approach does not capture highly nonlinear behavior in the input parameter space. For this reason, sampling-based methods using a Monte Carlo technique is used to mitigate the limitation in the local method. Reference 9.1.2 specifies using the Latin Hypercube Sampling (LHS) method to achieve a reasonable number of samples, equivalent to nLHS np +1, where np is the number of variables in the function being evaluated. Once the analysis is performed using nLHS parameter vectors, whose constituent values are paired at random, the mean value and standard deviation from the different parametric runs is calculated using Equation 4-14 and Equation 4-15, respectively (Equations 3-3-1 and 3-3-2 of Reference 9.1.2). © Copyright 2018 by NuScale Power, LLC 109

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 1

                                         =                                                  Equation 4-14 1                                                 Equation 4-15
                                    =                  (  )

1 The validation exercise that employs the LHS method demonstrates statistical convergence by performing sensitivity runs with an increasing number of samples. In addition, if the distribution function of the input variables is assumed, then sensitivity of uinput to this assumption is explored. 4.3.3 Calculation of Mesh Numerical Uncertainty In some FIV evaluations, the analysis relies on a computer model that is developed using finite-element methods. In this case, the solution process introduces uncertainty in the overall model result due to the fact that discretized equations are used and/or iterative matrix solvers are executed (the latter only for nonlinear systems). Finite element models are used to determine the vibration mode shape and natural frequency in many FIV evaluations. Estimation of numerical uncertainty is not required for hand calculations in which the input parameters are obtained from mathematical or empirical correlations. The Grid Convergence Index method is a means to estimate the numerical uncertainty that arises from the use of computational grids with different resolution capabilities that aim to output a result . Considering three numerical meshes (fine; medium; coarse) to have characteristic cell sizes h1 < h2 < h3, and refinement factors r21 = h2 / h1 and r32 = h3 / h2, the order of convergence, p, is calculated as: ln + ()

                                    =                                                         Equation 4-16 ln( )

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

                                           = 1                                          Equation 4-18
                  =          (difference in result between coarse and medium mesh)        Equation 4-19
                   =           (difference in result between medium and fine mesh)        Equation 4-20 A uniform and integer mesh refinement factor is used (for example r = 2) to implement this method. Numerical uncertainty is then estimated from the Grid Convergence Index, given below, with a factor of safety Fs = 3 (Recommended it for unstructured grid refinement.

Also, three grid solutions should be sufficiently conservative): l l

                                          =  =                                            Equation 4-21 1

Note that if, for example, the order of the discretization scheme is known to be p=2 (second order), and the medium mesh cell size (h2) is uniformly decreased by half in all directions (r=2), then unum from Equation 4-21 becomes the absolute value of the difference between the result on the fine and medium grid ( l1 - 2l). For linear modal analysis, this value is small because there is a weak dependence of calculated frequency on grid density. 4.4 Evaluation Process The overall process for the pre-test prediction and post-test assessments is summarized below. Some values may require assumptions at the time of the pre-test prediction depending on the status of the test design. In the post-test assessment, the uncertainties are confirmed or adjusted as necessary based on the final test design and results. Pre-Test Prediction

1. Using best-estimate input and accounting for experimental biases, calculate safety margin and critical parameters for the test (frequencies, critical or lock-in velocities, and so on).

2. Calculate input, measurement and numerical uncertainties.

3. Using the parameters determined above, quantify the range of allowable test results that adequately validate the design analysis.

These steps provide confidence that considering the experimental biases, and input, measurement and numerical uncertainties, the test design is adequate to validate the design analysis. © Copyright 2018 by NuScale Power, LLC 111

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Post-Test Assessment

1. Determine if changes to the expected or allowable range in the pre-test prediction are required based on considerations such as finalization of the test design, confirmation of measurement uncertainties, or the as-tested conditions.

2. Confirm test results match predictions and are within the allowable range for validation.

3. Quantify the validation comparison error and model error to confirm they are acceptable.

These steps complete the validation of the design analysis using the test results. If the modeling error is greater than the validation comparison error, the design analysis is to be updated to decrease modeling error. Additionally, if the test results do not match predictions, the design analysis is to be revised based on the conclusions of the testing. 4.5 Evaluation Procedures 4.5.1 Turbulent Buffeting of Steam Generator Tube This methodology will be provided in the next revision of this technical report. 4.5.2 Vortex Shedding Consider the results of the test to provide the natural frequency in water (fn_T), mode shape (T), and associated uncertainty (uD). An ANSYS model to simulate the test geometry is developed using the same configuration, as well as environment and boundary conditions as the experiment. The model predictions for the fundamental mode natural frequency and mode shape are fn_M and M, respectively. 4.5.2.1 Calculate Model Error Using Equation 4-1, calculate the modeling error based on maximum of different modes: ESG_f =l fn_M - fn_T l, ESG_ =l M - T l, ESG = max(ESG_f, ESG_), based on normalized values. The above comparison errors are examined for at least the first mode results. If higher modes are reviewed the same procedure is followed, but the first mode is more limiting to the margin assessment. Also, because is not a single value but a function of SG height, the maximum difference is used on the basis of a unity normalized mode shape. 4.5.2.2 Calculate Model Uncertainty The uncertainty associated with the result from modeling of the SG test is referred to as uval, and consists of input, numerical, and measurement uncertainties, combined per © Copyright 2018 by NuScale Power, LLC 112

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Equation 4-7, and discussed in the following sections. The analysis ensures that the resultant uval l ESG l, otherwise the modeling approach is to be modified to reduce the error. 4.5.2.2.1 Input Uncertainty The inputs to the modal analysis of the test configuration are listed in Table 4-1. The sampling method discussed in Section 4.3.2.2 is used to generate a series of model predictions from which an input uncertainty is estimated (Equation 4-15). Note that sampling of different boundary conditions is not necessary unless the modeling error is much larger than the overall uncertainty (uval << l ESG l). Table 4-1 Steam generator test model inputs Input Parameter Basis for Variability Geometric Dimensions Manufacturing tolerances affect the nominal values specified for the model Mass Effect of hydrodynamic mass in actual tube bundle is likely different than that estimated by formula, which is based on a correlation for single flexible tube surrounded by an array of rigid tubes (note: the correlation relies on pitch and diameter) Boundary Conditions SG boundary conditions are subject to variability based on considerations such as fit-up with the supports, manufacturing tolerances, compression and thermal expansion. Boundary conditions are expected to be fixed, pivot or a combination. Boundary conditions may vary throughout the tube bundle. 4.5.2.2.2 Numerical Uncertainty The numerical uncertainty in the modal analysis (unum) is estimated using the approach discussed in Section 4.3.3 using nominal model inputs. 4.5.2.2.3 Measurement Uncertainty In the post-test analysis, the measurement data uncertainty is used directly as provided by the test if it is reported for the frequency and mode shape and no other action is required. In the pre-test analysis, a propagation calculation is performed to obtain uD (Section 4.1) similar to the approach for estimating input uncertainty. 4.5.2.3 Estimate Uncertainty in Safety Margin for Steam Generator Tube in NuScale Power Module There are four methods to show acceptable margin to VS lock-in. The three methods applicable to tube arrays are described below for completeness; however, they may not all be necessary to execute the pre-test prediction. Method B is described first, as it corresponds to the minimum safety margin in the design analysis. Method B requires that the reduced damping (CRD) is greater than the minimum threshold value of 64. The corresponding safety margin is represented using Equation 4-22. © Copyright 2018 by NuScale Power, LLC 113

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 1 4 ()

                          =       1=                                        1               Equation 4-22 64         64                 ()

The input parameters in Equation 4-22 are discussed in Table 4-2, and assigned generic labels. The process in Section 4.3.1 is used to determine the analytically predicted allowable range for the safety margin in Equation 4-22 and evaluate the effect of uncertainty in the different parameters. Equation 4-22 is re-written as: ( , )

                                       =                       1                             Equation 4-23

( , ) where S = /16, g, and h are the definite integrals. Table 4-3 shows the details of performing the calculation on Equation 4-23, which is performed separately for the light and heavy tube cases. The SG mode shape relative magnitude is zero at the beginning and end of the tube, so (0) = ( ) = 0. Table 4-2 Steam generator tube inputs to vortex shedding margin calculation: method B Temporary Label Input Parameter Basis X1 Damping ratio in air A nominal value of damping is used. This parameter is {} measured in a dedicated test, so its uncertainty is propagated. X2 Total mass of tube Total mass includes the mass of the tube metal, secondary { mtot } fluid, and hydrodynamic mass (virtual mass on primary side). Uncertainty in those contributing factors propagates to the total. Nominal values for light and heavy cases are developed. X3 Fluid density { } The primary fluid temperature variation along the SG radius and height is a source of uncertainty in the calculation, which assumes a constant value for RCS (cold or hot region). X4 Tube outer diameter Manufacturing tolerances affect the nominal value specified {D} for the calculation. X5 Overall length of tube Manufacturing tolerances affect the nominal value specified { ltube } for the calculation. X6 Length of tube In the design analysis, this is assumed from the lowest subject to cross flow elevation to the elevation corresponding to the second tube { le } support, considering both active and inactive supports. Its uncertainty propagates to the margin calculation. X7 Fundamental modal The free-vibration mode shape of the SG tube is obtained shape { 1 } using an ANSYS modal analysis. This parameter includes uncertainty in the modal analysis modeling, considering both the range of possible mode shapes based on boundary conditions and the components of the mode shape that could be excited by cross flow. © Copyright 2018 by NuScale Power, LLC 114

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 4-3 Steam generator tube vortex shedding margin uncertainty method: method B Step Description Procedure 1 Analytic derivative of ( , ) Equation 4-23 with , where g and h are definite integrals ( , ) respect to X1 evaluated at the nominal values uX1 Uncertainty in X1 Obtain from measurement data of damping ratio in air 2 Analytic derivative of ( , ) Equation 4-23 with , evaluated at the nominal values ( , ) respect to X2 uX2 Uncertainty in X2 Uncertainty in total tube mass is determined from the uncertainty in secondary fluid density, tube material density, and RCS density (i.e., uX2 [us2+u6902+urcs2]0.5) 3 Analytic derivative of ( , ) Equation 4-23 with , evaluated at the nominal values ( , ) respect to X3 uX3 Uncertainty in X3 Obtain from RCS density range across SG (uncertainty due to fluid temperature variation) 4 Analytic derivative of ( , ) Equation 4-23 with , evaluated at the nominal values ( , ) respect to X4 uX4 Uncertainty in X4 Obtain from standard deviation of SG outer diameters as generated by manufacturing tolerances distribution 5 Analytic derivative of ( ) Equation 4-23 with =0 ( , ) respect to X5 uX5 Uncertainty in X5 Not propagated 6 Analytic derivative of ( , ) Equation 4-23 with ( )

                                                                         , evaluated at the nominal values respect to X6 uX6                  Uncertainty in X6              Obtain from range of tube length exposed to flow based on tolerances in the configuration of supports and their assumed effectiveness 7                   Sensitivity coefficient is     Equate to 1.0 (justified because model uncertainty is taken as unity because         expected to be small) modal analysis is linear uX7                  Uncertainty in X7              Same as uval in Section 4.5.2.2.

uR Equation 4-11

                                                             +        +     +       +    +      +

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 4-4 Steam generator tube inputs to vortex shedding margin calculation: method A Temporary Label Input Parameter Basis X8 velocity { v } This parameter includes uncertainties in the assumed primary coolant flow velocity. X9 Natural Frequency { fn } This parameter includes uncertainties in the SG tube natural frequency. X10 Tube outer diameter { D } This parameter includes uncertainties associated with manufacturing tolerances. Table 4-5 Steam generator tube vortex shedding margin uncertainty method: method A Step Description Procedure 8 Analytic derivative of 1 Equation 4-24 with respect to X8 X9 X10 uX8 Uncertainty in X8 Uncertainty in velocity based on differences in primary coolant flow rate, due to considerations such as calculation method and temperature. 9 Analytic derivative of X8 Equation 4-24 with respect to X9 X 92 X10 uX9 Uncertainty in X9 Uncertainty in natural frequency considering parameter such as possible boundary conditions, tube masses. 10 Analytic derivative of X8 Equation 4-24 with respect to X10 X 9 X102 uX10 Uncertainty in X10 Uncertainty in tube outer diameter considering manufacturing tolerances. uR Equation 4-11

                                                                             +       + +

Method C uses the same variables as Methods A and B, but with different acceptance criteria limits. Specifically, the reduced damping needs to be greater than 1.2 instead of 64 and the reduced velocity needs to be less than 3.3 instead of 1.0. The reduced velocity limit does not affect the analytic derivatives. The safety margin value can be calculated using Equation 4-24 with 3.3 substituted for the value of 1 from Method A. For the reduced damping, Equation 4-23 can be used with the value of S modified to 0.3 instead of /16. When using Method C, the reduced damping and reduced velocity both are evaluated to determine expected and allowable ranges. © Copyright 2018 by NuScale Power, LLC 116

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 4.5.3 Fluid-Elastic Instability of SG Tubes The method for validating the design analysis process by testing measurements is described below. 4.5.3.1 Calculate Model Error Model error is quantified at the completion of the post-test analysis per Equation 4-1. For the FEI assessment, model error is calculated for each measured or derived parameter that is a calculation result, such as the frequencies, mode shapes, and pitch velocity. The model error is then compared to the validation standard uncertainty to ensure the validation metric are consistent with the inequality in Equation 4-8. No estimation of model error is required during the pre-test analysis. 4.5.3.2 Calculate Model Uncertainty Model uncertainty is comprised of input uncertainty, numerical uncertainty, and measurement uncertainty. These uncertainties are evaluated in the pre-test prediction. Some values require assumptions at the time of the pre-test prediction depending on the status of the test design. In the post-test assessment, the uncertainties are confirmed or adjusted as necessary based on the final test design. In the pre-test analysis, the predicted uncertainties are used to determine the range of allowable test results that validate the design analysis. See Section 4.7 for additional details regarding this aspect of the pre-test analysis. In the post-test analysis, the range is confirmed using final uncertainty values, and the validation uncertainty is compared to the model error as described in Section 4.5.3.1. 4.5.3.2.1 Input Uncertainty The effect of input parameter uncertainty on simulation uncertainty is calculated using the local or global methods that are discussed in Sections 4.3.2.1 and 4.3.2.2, respectively. The local method is sufficient for input parameters that are relevant to FEI. If the effects of large differences in the input parameter need to be investigated the global method is to be used. The categories of inputs relevant for the FEI analysis of the test configuration are listed in Table 4-6. The sampling methods discussed in Section 4.3.2.2 are used to generate a series of predictions from which an input uncertainty can be estimated (Equation 4-15). In the pre-test analysis, the significant inputs within each category in Table 4-6 are to be considered. Examples of the types of input parameter variability for each category are also identified in the table. The input parameters that are considered in the input uncertainty assessment are to be justified in the pre-test analysis. © Copyright 2018 by NuScale Power, LLC 117

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 4-6 Fluid elastic instability analysis input parameter types Input Parameter Category Example Input Parameter Variability Modal The effects of as-built conditions and allowed variability in test conditions on the pitch velocity are considered. Thermal hydraulic The effect of the following on the pitch velocity are considered: allowed variation in test conditions, calculation methods for determining local velocities, and the effect of as-built conditions on local velocities. Design The effect of as-built conditions on the critical velocity are considered. Empirical Uncertainties in the empirical correlations used to determine the critical velocity are considered. 4.5.3.2.2 Numerical Uncertainty Numerical uncertainty is assessed in the pre-test prediction. Completion of testing does not affect the predicted numerical uncertainty. Numerical uncertainty applies to the modal analysis of the SG tube and the integration of the mode shapes over the length of the tube, which is performed as a summation approximation. The numerical uncertainty in the modal analysis (unum) is estimated using the approach discussed in Section 4.3.3 using nominal inputs. 4.5.3.2.3 Measurement Uncertainty Measurement uncertainty is estimated in the pre-test prediction and a final evaluation is performed in the post-test assessment. Depending on the maturity of the test design at the time of the pre-test prediction, engineering judgment is used to estimate measurement uncertainty values. In this event, appropriate assumptions are made that are reasonable both in terms of the test design and the ability to validate the design analysis. The results of the pre-test prediction are used to identify any changes that need to be incorporated into the detailed test design to accommodate reasonable measurement uncertainty. Open items are established to track the assumption until it has been incorporated. In the post-test analysis, the measurement data uncertainty is used directly as provided by the test and no other action is required. In the pre-test analysis, a propagation calculation is performed to obtain uD (Section 4.1) similar to the approach for estimating input uncertainty. 4.5.3.3 Estimate Uncertainty in Safety Margin The margin to the onset of FEI is based on the difference between the reduced mode shape weighted mean pitch velocity and the critical velocity, as shown in the following equation. The uncertainties in the modal, thermal hydraulic, design and empirical inputs are evaluated to quantify the effect of each parameter on the design analysis safety margin. © Copyright 2018 by NuScale Power, LLC 118

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 v cos( ) M i0.5 SFFEI = 1 a m2 Equation 4-25 C 2 D The input parameters in Equation 4-25 are discussed in Table 4-7, and assigned generic labels in Equation 4-26. X1 cos( ) X 2,i0.5 SFFEI = 1 X8 X 2 X Equation 4-26 X7 3 2 4 X5 X6 The process in Section 4.3.1 is used to determine the effect of input parameter uncertainty on the safety margin value as outlined in Table 4-8. Table 4-7 Steam generator tube inputs to fluid elastic instability safety margin calculation Temporary Label Input Parameter Basis X1 velocity This parameter includes uncertainties in the assumed primary coolant flow velocity. X2 modal multiplier This parameter includes uncertainty in the modal analysis modeling uncertainty, considering both the range of possible mode shapes based on boundary conditions and the components of the mode shape that could be excited by cross flow. X3 mass This parameter includes uncertainty in the mass of the tube and the surrounding fluid. X4 damping This parameter includes uncertainty, which is finalized when the damping value is measured. X5 density This parameter includes uncertainty in the operating temperature of the primary coolant. X6 tube outer diameter This parameter includes minor uncertainties in the manufacturing tolerances of the tube. X7 , X8 Connors constants These parameters include uncertainties associated with characterizing the onset of FEI for helical tubes. © Copyright 2018 by NuScale Power, LLC 119

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 4-8 Steam generator tube fluid elastic instability margin uncertainty method Step Description Procedure 1 Analytic derivative of Equation cos( ) X 2,i0.5 4-26 with respect to X1 X8 X 2 X 4 X7 3 2 X5 X6 uX1 Uncertainty in X1 Uncertainty in velocity based on differences in primary coolant flow rate, due to considerations such as calculation method and temperature. 2 Analytic derivative of Equation X1 cos( ) 4-26 with respect to X2 X8 0.5 X 2 X 4 2X 2, i X7 3 2 X5 X6 uX2 Uncertainty in X2 Uncertainty in modal multiplier considering differences in tube and fluid mass, material properties and boundary conditions. 3 Analytic derivative of Equation 4-26 with respect to X3 X8 X1 cos( ) X 2,i0.5 X8 X 2 X X3 X 7 3 2 4 X5 X 6 uX3 Uncertainty in X3 Uncertainty in linear mass density considering differences in tube and hydrodynamic mass. 4 Analytic derivative of Equation 4-26 with respect to X4 X8 X1 cos( ) X 2,i0.5 X8 X 2 X X4 X7 3 2 4 X5 X 6 uX4 Uncertainty in X4 Uncertainty in damping considering the potential range of expected damping at the design analysis condition. 5 Analytic derivative of Equation 4-26 with respect to X5 X8 X1 cos( ) X 2,i0.5 X8 X 2 X X5 X 7 3 2 4 X5 X 6 uX5 Uncertainty in X5 Uncertainty in density considering the range of potential primary fluid temperatures at the design analysis condition. 6 Analytic derivative of Equation 4-26 with respect to X6 2X8 X1 cos( ) X2,i0.5 X8 X 2 X X6 X7 3 2 4 X5 X 6 uX6 Uncertainty in X6 Obtain from standard deviation of SG outer diameters as generated by manufacturing tolerances distribution. © Copyright 2018 by NuScale Power, LLC 120

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Step Description Procedure 7 Analytic derivative of Equation 4-26 with respect to X7 X 8 X1 cos( ) X 2,i0.5 X8 2 X 2 X 4 X 3 7 2 X5 X6 uX7 Uncertainty in X7 Consider a range of empirical constants appropriate to bound FEI for the helical SG tubes. 8 Analytic derivative of Equation X 2 X 4-26 with respect to X8 X8 X1 cos( ) X2,i0.5 log 3 2 4 X5 X 6 X8 X3 2 X4 X7 2 X5 X 6 uX8 Uncertainty in X8 Consider a range of empirical constants appropriate to bound FEI for the helical SG tubes. uR Equation 4-11

                                                                 +     + +       +     +      + 
                                                          +      +

4.5.4 Acoustic Resonance The method for validating the design analysis process by testing measurements is described below. 4.5.4.1 Calculate Model Error Model error is quantified at the completion of the post-test analysis per Equation 4-1. For the acoustic resonance (AR) assessment, model error is calculated for each measured or derived parameter that is a calculation result, such as the acoustic frequencies and velocity. The model error is compared to the validation standard uncertainty to ensure the validation metric are consistent with the inequality in Equation 4-8. No estimation of model error is required during the pre-test analysis. 4.5.4.2 Calculate Model Uncertainty Model uncertainty is comprised of input uncertainty, numerical uncertainty, and measurement uncertainty. These uncertainties are evaluated in the pre-test prediction. Some values may require assumptions at the time of the pre-test prediction depending on the status of the test design. In the post-test assessment, the uncertainties are confirmed or adjusted as necessary based on the final test design. In the pre-test analysis, the predicted uncertainties are used to determine the range of allowable test results that would validate the design analysis. See Section 4.7 for additional details regarding this aspect of the pre-test analysis. In the post-test analysis, the range is confirmed using final uncertainty values, and the validation uncertainty is compared to the model error as described in Section 4.5.4.1. © Copyright 2018 by NuScale Power, LLC 121

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 4.5.4.2.1 Input Uncertainty The effect of input parameter uncertainty on simulation uncertainty is calculated using the local or global methods that are discussed in Sections 4.3.2.1 and 4.3.2.2, respectively. The sampling methods discussed in Section 4.3.2.2 are used to generate a series of predictions from which an input uncertainty is estimated (Equation 4-15). The input parameters that are considered in the input uncertainty assessment are to be justified in the pre-test analysis. 4.5.4.2.2 Numerical Uncertainty There is no numerical uncertainty in the AR calculation method, so this term is zero for the purpose of the pre-test and post-test analyses. 4.5.4.2.3 Measurement Uncertainty Measurement uncertainty is estimated in the pre-test prediction and a final evaluation is performed in the post-test assessment. Depending on the maturity of the test design at the time of the pre-test prediction, engineering judgment is used to estimate measurement uncertainty values. In this event, appropriate assumptions are made that are reasonable both in terms of the test design and the ability to validate the design analysis. The results of the pre-test prediction are used to identify any changes that need to be incorporated into the detailed test design to accommodate reasonable measurement uncertainty. Open items are established to track the assumption until it has been incorporated. In the post-test analysis, the measurement data uncertainty is used directly as provided by the test and no other action is required. In the pre-test analysis, a propagation calculation is performed to obtain uD (Section 4.1) similar to the approach for estimating input uncertainty. 4.5.4.3 Estimate Uncertainty in Safety Margin Margin to the AR acceptance criterion of Strouhal number is calculated as follows: cdi SFAR = 1 Equation 4-27 (0.62)4(Lv + 0.3di )V The uncertainty in Equation 4-27 is primarily from input parameters and variables that are measured during the startup test at a single location susceptible to AR. Table 4-9 discusses the influential parameters that contribute to the uncertainty in safety margin. The process in Section 4.3.1 is used to determine the analytically predicted allowable range for the safety margin. Hence, Equation 4-27 is re-written as: © Copyright 2018 by NuScale Power, LLC 122

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 X1 X 2 SFAR = 1 Equation 4-28 4( X 3 + 0.3X 2 ) X 4 X 5 Table 4-10 shows the details of performing the calculation on Equation 4-28. Table 4-9 Decay heat removal system steam pipe inputs to acoustic resonance margin calculation Input Parameter Basis Speed of sound In analysis space, the speed of sound is evaluated as a function of steam pressure and temperature in the rigid piping. During NPM steady-state operation and startup testing, the thermodynamic properties of the steam fluctuate about a mean. Accordingly, changes in pressure or temperature are accounted for in the speed of sound. Local flow velocity at tee in This input parameter is evaluated from the total secondary mass flow pipe rate, steam density, and flow area of pipe to obtain an average value. During NPM steady-state operation and startup testing it is probable that the local velocity is slightly different due to thermodynamic fluctuations, turbulence, or geometry effects (e.g., effect of upstream elbow). Length of closed branch pipe This parameter is measured during construction or in the test setup based on the as-built configuration. Inside diameter connected to This parameter is measured during construction or in the test setup tee junction based on the as-built configuration. Strouhal Number Specific geometric considerations are used to determine the best-estimate value and uncertainty range for the Strouhal number. © Copyright 2018 by NuScale Power, LLC 123

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 4-10 Decay heat removal system steam pipe acoustic resonance margin uncertainty method Step Description Procedure 1 Analytic derivative of 0.403 X 2 Equation 4-28 with respect to X1 ( X 3 + 0.3 X 2 ) X 4 X 5 uX1 Uncertainty in X1 Uncertainty in the speed of sound is estimated based on the range of possible pressures, temperature and flow rates in the test. 2 Analytic derivative of 0.403X1 X3 Equation 4-28 with respect to X2 ( X3 + 0.3X 2 )2 X 4 X5 uX2 Uncertainty in X2 Uncertainty in the inner diameter of the cavity piping. 3 Analytic derivative of 0.403X1 X 2 Equation 4-28 with respect to X3 ( X3 + 0.3X 2 )2 X 4 X 5 uX3 Uncertainty in X3 Uncertainty in the length of the cavity. 4 Analytic derivative of 0.403 X1 X 2 Equation 4-28 with respect to X4 ( X 3 + 0.3 X 2 ) X 42 X 5 uX4 Uncertainty in X4 Uncertainty in the steam flow velocity. 5 Analytic derivative of 0.403 X1 X 2 Equation 4-28 with respect to X5 ( X 3 + 0.3 X 2 ) X 4 X 52 uX5 Uncertainty in X5 Uncertainty in the Strouhal number. uR Equation 4-11 (1ux1 ) + (2ux2 ) + (3ux3 ) + (4ux4 ) + (5ux5 ) 2 2 2 2 2 4.6 Experimental Bias Considerations Some of the NuScale CVAP tests are performed on prototypic mockups of the NPM components, as opposed to in-situ with the plant at normal operation. The following tests have reasonable differences from the plant configuration:

Steam generator FIV testing is performed on a full-size subset of the total number of tubes corresponding to the 9th to 13th columns of the actual steam generator. Unheated water flow about the tubes (on the outside) provides the excitation forces, and no fluid is present within the tubes (on the inside).

4.6.1 Steam Generator Testing The geometry of the helical coil tubes used in the FIV testing is identical to the components used in the NPM. The boundary conditions in terms of supports and structural interactions (i.e., interfaces with other components) are also similar. The water flow in the reactor primary side is simulated by water entering the lower part of the inner vessel, rising upwards and turning at the top into the annulus to cross the tube bundle in a downward sense. Nonetheless, there are practical considerations that make the test specimen differ © Copyright 2018 by NuScale Power, LLC 124

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 from the NPM so those differences are considered. The following features introduce bias into the design analysis that relies on test measurements:

The circulating water on the exterior of the tubes is at room temperature
The helical coil tubes are not filled with boiling water, but contain instruments and cables
The test specimen contains five tube columns instead of twenty-one in the full assembly.

The objective of the testing is to collect data and confirm that VS and FEI are not active, that inputs to the analysis of the different FIV mechanisms (e.g., natural frequency, damping ratio, and so on) are justified, and that vibration amplitude predictions for TB are bounding. 4.6.1.1.1 Approach for Testing and Confirmation of Turbulent Buffeting Characteristics The natural frequency in water is a parameter in the calculation of safety margin against fatigue from alternating stress induced by random vibrations on the SG tubes, and its uncertainty is accounted for by comparison of simulations and measurements. The simulation accurately models the empty tube and specify the appropriate water temperature as the test to make the comparison valid. The structural or operating features of the test that deviate from the NPM design result in a different average frequency as determined in the design analysis. Therefore, the modal analysis of the test apparatus is compared to the modal analysis of the NPM to understand any differences. The effective mass of tube is another parameter that is affected by the test vs. NPM differences. Its influence on vibration appears in the measured frequency and mean square displacement amplitude. As discussed earlier, the pre-test prediction determines the modal characteristics and compares to the design analysis. Lastly, the maximum RMS displacement is a parameter in the safety margin calculation for the design analysis. The methodology uses an upper bound PSD approach from literature, so the expectation is that measured RMS responses are less than in the pre-test prediction (i.e., positive bias). To comprehensively consider the uncertainty in RMS displacement, the PSD analysis is validated against the recorded dynamic pressure data in the test to confirm that the literature approach is bounding for the HCSG under prototypical NPM velocities. Numerical evaluation of the differences between the literature PSD and the benchmarked PSD from the test is performed to quantify the uncertainty and incorporate any bias. 4.6.1.1.2 Approach for Testing and Confirmation of Vortex Shedding Characteristics The signature of VS is a periodic oscillation in the pressure field that translates to a distinct frequency in the PSD. If the frequency of the periodic driving force matches the natural frequency of a tube, then resonance occurs and the amplitude of the vibration becomes © Copyright 2018 by NuScale Power, LLC 125

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 significant. Vortex shedding characteristics in terms of the coherent structure of the eddies are strongly dependent on Reynolds number. The SG testing, although on a subset of the total number of tubes, allows detection of this phenomenon if it occurs for a range of velocities that are considered based on flow rate changes with power in the NPM. The differences relative to the NPM design in terms of circulating water temperature and empty tubes, and their potential impact on VS are considered as follows:

The water temperature affects the fluid density and viscosity, which influence the Reynolds number (the tube diameter and flow speed are similar to NPM conditions).

Therefore, the pre-test prediction evaluates those changes in Reynolds number, and ensures that the test specifies sufficient flow rate changes to cover the possible range of Reynolds number at plant conditions.

The vibration mode shape and natural frequency of the tube are important parameters that affect the tubes response to periodic flow excitations and potential for phase synchronization. As discussed earlier, the pre-test prediction determines the modal characteristics of the test apparatus and compares to the design analysis.

4.6.1.1.3 Approach for Testing and Confirmation of Fluid Elastic Instability Characteristics Fluid elastic instability is an intense vibration regime that causes significant motion and tube wear much greater than vibration caused by turbulence. Analytically, the onset of FEI is determined when the pitch velocity is greater than an empirically established critical velocity (evaluated using Connors coefficient). In order to comprehensively consider other parameters that may be affected by experimental biases, the following are evaluated:

The effective pitch velocity is dependent on the vibration mode and natural frequency of the tube. The pre-test prediction determines the modal characteristics of the test apparatus and compares to the design analysis. The comparison ensures that the test specifies sufficient flow rate changes to compensate for any differences that result in a decrease of the reduced pitch velocity in the test relative to the NPM design.
The critical velocity is dependent on the tubes total mass per unit length (including hydrodynamic mass), damping ratio, and density, which may deviate from the normal operating state. The damping ratio is a measured variable, so its value and associated uncertainty will be used directly in the range of safety margin calculation. The empty tubes provide a positive bias because that reduces the critical velocity (mass is in the numerator), and hydrodynamic mass is approximately 1/10 the metal mass. On the other hand, the test temperature provides a negative bias (density is in the denominator) because the test water density is greater than in the NPM. Therefore, the pre-test prediction compares values of the critical velocity calculated for the test apparatus and the NPM design.

4.7 Expected Results and Validation Range of Experimental Results The purpose of the pre-test prediction is to calculate the expected experimental results and determine a range of results that are acceptable to validate the design analysis. If the © Copyright 2018 by NuScale Power, LLC 126

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 experimental design exactly matches the conditions of the design analysis, and if there were no errors in the experimental measurements or modeling, the experimental result would exactly match the design analysis result. Distortions exist for most experiments, and the effect of the positive and negative distortion values on the range of validation safety margins and experimental results is determined. For example, testing at a lower pressure than the pressure associated with the limiting design condition is considered a distortion, if pressure affects the results of the analysis. To quantify the effect of the distortion, the design analysis calculation is re-performed, using the standard design analysis methods, at the test pressure and a new safety margin is determined. The difference between the design analysis safety margin and the safety margin determined at the test pressure is the distortion adjustment. If the testing condition is more limiting than the design analysis condition, the value of the adjustment is positive and increases the validation range. Each distortion is individually calculated and then the safety margins are added together in Equation 4-29. The input, numerical and measurement uncertainties are calculated based on the guidelines in Section 4.5.1. These uncertainties are calculated in terms of the safety margin and are combined in Equation 4-29. The effect of the design analysis safety margin, distortions and uncertainties on the allowable range of the safety margin is described by Equation 4-29. The design analysis safety margin is provided as an upper bound to the range to provide a reasonable cutoff for the validation. For the lower bound of the range, the design analysis safety margin is not considered to ensure that even accounting for uncertainties there is positive margin to the onset of the phenomena at normal operating conditions. The expected results for the critical measured parameter should be documented, and a validation range using the result of Equation 4-29 for that parameter should be specified. The expected results for each measured parameter are documented, and an allowable validation range using the result of Equation 4-29 for that parameter specified. RangeUpper = SMBE +SMd + SMDA +SMu Equation 4-29 RangeLower = SM BE + SMd SMu Where, Range = Range of safety margins for validation (%), SMBE = Best-estimate safety margin (%), SMDA = Safety margin from the design analysis (%), SMd = Safety margin adjustment from distortions (%), and SMu = Safety margin adjustment from total uncertainty (%). © Copyright 2018 by NuScale Power, LLC 127

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Note that it could be possible to justify a higher upper bound for the validation range, since an experimental result that falls above the upper bound indicates that there are un-realized conservatisms in the design analysis. Particularly for design analysis results with small safety margins or known, highly conservative inputs, this approach should be considered to determine an alternate upper bound instead of the approach provided in Equation 4-29. 4.8 Summary The NuScale Power CVAP Measurement Program relies on diverse testing campaigns to verify the structural integrity of NPM components that are evaluated in the Analysis Program to have a margin of safety less than 100 percent. This report provides an approach to validate the analysis methods against the experimental results, and methodologies to quantify bias and uncertainty embodied with the results of the design analyses and the measurement program. Table 4-11 summarizes the components discussed in the body of the report, and their analysis validation approach. When testing is complete, post-test analysis is performed to assess the experimental results and finalize the validation effort. The pre-test prediction provides a level of confidence in the test design and its ability to validate the design analysis. Any differences between the pre-test predictions and experimental results will be adjudicated in the post-test analysis. Table 4-11 Summary of components and flow induced vibration analysis validation methods FIV Validation Variables with Uncertainty Component Margin Relative To Mechanism Test to be Measured Speed of sound DHRS Steam Critical Strouhal AR Initial Startup Flow velocity Pipe Number Cavity diameter and length Tube diameter and mass Mode shapes and natural SG VS Prototypic Reduced Damping frequencies Damping ratio in air Tube diameter and mass Mode shapes and natural Impact Fatigue frequencies SG TB Prototypic Usage Mean square response PSD Damping ratio in water Flow velocity Mode shapes and natural frequencies SG FEI Prototypic Stability Ratio Tube diameter and mass Damping Primary fluid density © Copyright 2018 by NuScale Power, LLC 128

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.0 Validation Tests The following sections provide a summary of the validation testing planned for the steam generator, SG IFR, and DHRS steam tee. The test design, as specified in the testing needs document, is discussed for each test. For the SG and DHRS tests, the results of the pre-test prediction calculations are also provided. 5.1 TF-3 Validation Test 5.1.1 TF-3 Testing Overview The general objective of the TF-3 test is to obtain vibration test data for a prototypical NuScale HCSG for validation of FEI, VS, and TB design analyses. The specific test program objectives are:

1. Determine in-air natural frequencies and mode shapes of the HCSG tubes; this includes ability to characterize modes of the tube bundle assembly (synchronized motion of full tube bundle and supports).

2. Determine in-water natural frequencies and mode shapes of the HCSG tubes and supports; this includes ability to characterize modes of the tube bundle assembly (synchronized motion of full tube bundle and supports).

3. Determine in-air and in-water damping values for a range of representative mode frequencies and vibration amplitudes.

4. Obtain data to characterize primary flow dynamic pressure fluctuations, SG tube and tube support vibration amplitudes for a range of primary flow conditions.

5. Obtain high flow rate vibration amplitudes to demonstrate margins to FEI and VS.

The TF-3 test program consists of modal testing during the fabrication process, modal testing on the completed test assembly, and flow testing as shown in Table 5-1. Table 5-1 Summary of tests Test Type In-air natural frequencies and mode Partial-tube array Shape testing (during fabrication) In-air damping tests (during fabrication) Partial-tube Array In-air natural frequencies and mode Full-tube Array Shape testing In-air damping tests Full-tube array In-water natural frequencies and mode Full-tube array Shape testing In-water damping tests Full-tube array Steady-state flow testing Full-tube array, flow VS flow testing Full-tube array, flow FEI flow testing Full-tube array, flow Individual tube testing is performed during fabrication of the test specimen. Testing is performed following installation of a complete helical column, but before installation of the © Copyright 2018 by NuScale Power, LLC 129

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 next column. Temporary support rings are used during this testing to simulate the restraint provided by the riser in a fully-assembled tube bundle. This testing includes measurements using both permanently-installed and temporarily-mounted accelerometers. Individual tube testing during assembly allows exploration of the various boundary conditions that may exist. Access limitations exist in a fully-assembled tube bundle array test, both for instrumentation placement and for means to perform excitation of tubes. Single-tube tests allow greater ability to examine variability in boundary conditions between tubes, based on the flexibility to use temporary, removable accelerometers that can be iteratively employed. Permanent sensor arrangement in the tube array cannot be altered once the array is constructed. Performing modal measurements during fabrication allows confirmation that sensor function is as expected. Tube array testing is performed using a representative tube bundle array, constructed using prototypic supports. Array testing includes in-air modal and damping tests, performed as part of individual tube testing during fabrication of the test specimen. The array testing also includes in-water modal and damping tests and flow testing over the full range of nominal design operating conditions, as well as at FEI and VS on-set conditions. This testing is a comprehensive performance demonstration of the FIV design of the NuScale SG. A full-array test provides the most prototypic platform to characterize modal frequencies, shapes and damping for the NuScale design. In order to directly evaluate FEI, VS or confirm primary side flow PSDs for the NuScale design, flow testing of a prototypic tube array is necessary. 5.1.1.1 TF-3 Test Specimen The scope of the TF-3 test is the SG (including tubes and tube support structures) both as a fully-assembled tube array and during the fabrication process at points where full-helical columns are installed. This section identifies the design aspects that must be prototypic. Temporary Supports for Individual Tube Testing during Fabrication The in-process tube array is used for testing during fabrication; therefore, requirements for the full tube array (described in the following section) apply. The only physical modification for the tube array for this testing is that a temporary support structure is needed to simulate the constraint provided by the riser in a fully assembled tube bundle. This structure is designed to interface with the innermost installed column of tube supports. This structure is adjustable to allow variation in the applied compression and to allow use at various intermediate steps in the specimen fabrication (i.e., be able to be deployed as each column is installed, and so on). Full-Tube Array Testing Confinement of flow through the SG tube bundle is represented, with a prototypic upper riser (including riser-to-SG-tube-support clearance) and reactor vessel (including vessel-to-SG-tube-support clearances). The full test specimen includes a mechanism to provide © Copyright 2018 by NuScale Power, LLC 130

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 adjustable compression of the tube supports between the riser and the vessel wall. This mechanism is functional (including ability to adjust compression) during testing conditions, including flow testing. Prototypic geometry upstream of the SG is maintained by representing fluid confinement from the outlet of the riser to the inlet of the SG tube bundle. Flow downstream of the SG is maintained as balanced annular flow usinga pressure drop plate or other feature to remove the effect of any constrictions (transition of flow from an annulus to an exit pipe or plenum) at the outlet of the test fixture. The design of the SG tube array itself, including tube geometry and length, design of tube supports and physical interfaces between the tubes and tube supports and the riser and vessel (interfaces), is fully prototypic unless otherwise noted below. The only allowable departure from prototypic design geometry is that only helical Columns 9 through 13 are included. This implicitly requires the diameter of the riser and vessel to be scaled accordingly so that prototypic gaps between the riser and vessel, and between the inner and outer tube columns, are maintained. Other minor allowed deviations are described below. The design of tube array test fixture is in accordance with Table 5-2. Table 5-2 Tube array design geometry Drawing Design Elements

SG tube geometry (including OD and wall thickness)

Steam generator

SG tube arrangement (e.g., pitch)
Feed plenum tube layout Feed plenum access port
Geometry of vessel and tubesheet Steam generator tube supports
SG tube supports
Steam plenum tube sheet layout
Upper and lower SG supports
Upstream SG flow geometry (pressurizer baffle plate)

Upper RPV section

Downstream SG flow geometry (riser)
Interface between outer column tube supports and the vessel; this implicitly includes maintaining prototypic separation between outermost tube column and vessel
Interface between inner column tube supports and riser; this implicitly includes maintaining prototypic separation Reactor vessel internals - upper riser between innermost tube column and riser.
Riser geometry and supports (upstream SG flow geometry)
Downstream SG flow geometry (riser)

The tubes in the test fixture include the entire helix, transition, and straight lengths. A general summary of tube requirements for this test are provided in Table 5-3. Tube lengths upstream of the shell-side face of the feed plenum and downstream of the shell-side face of the steam plenum are reduced because a reduced number of columns are being tested and this affects the interface with the plenums. © Copyright 2018 by NuScale Power, LLC 131

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-3 Helical steam generator tube array details Helical # of Helical Radius NuScale Part # Length (in.) Column Tubes (in.) 9 (( }}2(a),(c) 10 (( }}2(a),(c) 11 (( }}2(a),(c) 12 (( }}2(a),(c) 13 (( }}2(a),(c) (( }}2(a),(c) The SG tubes for this testing use 304 or 316 stainless steel or other materials as proposed by the supplier and approved by NuScale. The SG tubes are 0.625-inchOD with a 0.050-inch wall thickness. Test facility operating conditions are provided in Table 5-4. Table 5-4 TF-3 test facility operating conditions Parameter Maximum Minimum Nominal Primary-side temperature(1) (( }}2(a),(c) Primary-side pressure(2) (( }}2(a),(c) Primary-side flow (( }}2(a),(c) Secondary-side temperature (( }}2(a),(c) Secondary-side pressure (( }}2(a),(c) Secondary-side flow (( }}2(a),(c) Notes: (1) Maximum primary-side temperature is based on accommodating heatup due to flow resistance without the need for dedicated cooling. Maximum design temperature may be reduced provided required flow rates are accommodated. (2) Maximum primary-side pressure is based on providing margin to accommodate required flow. Maximum design pressure for test fixture or system may be reduced, provided required flow rates are accommodated (3) This volumetric flow corresponds to a gap velocity of (( }}2(a),(c). (4) This volumetric flow corresponds to a gap velocity of (( }}2(a),(c). Lower minimum flow capacity is acceptable. The minimum flow requirement is based on allowing flexibility in selecting pump and pump controls. Testing at flows less than minimum flow are not planned 5.1.1.2 TF-3 Test Instrumentation and Data Acquisition The purpose of the TF-3 test is to obtain data on the vibration characteristics of the SG tubes; therefore, most test instrumentation is applied to the SG tubes, with a secondary emphasis on the tube supports and the vessel. Both strain gauges and accelerometers are used to characterize tube vibration amplitudes and associated frequencies: © Copyright 2018 by NuScale Power, LLC 132

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

PCB Piezotronics (Model number W356A03, 10mV/g sensitivity, 2-5000Hz frequency range) tri-axial accelerometers are used for tube accelerometer instrumentation.
Strain gauges (HBM 1-LY65-3/350) are used for tube strain gauge instrumentation.

A total of eight tubes selected from Columns 9, 11 and 12 are instrumented. Two tubes are permanently instrumented with strain gauges and accelerometers, four tubes are instrumented with accelerometers only, and two tubes are instrumented with strain gauges only. Based on the potential for varying boundary conditions (fixed, pivot, hybrid of pivot and fixed) for any given tube or span, the general approach for instrumentation is to provide some instrumentation on as many spans as possible to maximize the capability to capture measurements of the full possible range of tube vibration modes. The total number of instrumented tubes and the distribution of instrumentation among the selected tubes provides a balance between obtaining intensive data for a representative number of tubes (tubes with both strain gauges and accelerometers), having the capability to assess any influence of the types of instrumentation on data obtained (mix of tubes instrumented with only one or both types of instruments), and obtaining data on a broader sample of tubes (spreading total available instrumentation among a greater total number of tubes). There was also a preference to place instrumentation in spans that have an exciter coupling (or are proximate to the coupled spans) and a need to place multiple accelerometers on some spans to better characterize some higher order modes (anti-node(s) occur within the span, not only at supports) that have high relative mass participation factors. Each of the six instrumented tubes have a maximum of 10 accelerometers based on instrument cable constriction limitations. Accelerometers are placed in locations expected to have the largest vibration magnitude for the most dominant (highest mass participation factor) modes. For three accelerometer-instrumented tubes (one in each instrumented column), two accelerometers are designated for placement at a tube support, to ensure capability to detect rigid body motion. There are accelerometers placed on the tube supports that are paired with the tube accelerometers placed at a support. Strain gauges are placed in pairs at a given location, with one strain gauge on the tube extrados (oriented along major axis of the tube, on outside of major curvature) and one strain gauge on the top of the tube (oriented along major axis of the tube, 90 degrees diametrically offset from extrados). These pairs of placements will characterize the maximum strains associated with tube bending deflections perpendicular to the axis of the tube at a given location. Specific placement of strain gauges is based on locations of maximum predicted strain associated with most dominant tube frequencies (maximum mass participation factor). Detailed descriptions of the specific instrument locations on each tube are provided in the following sections. The general basis for the selection of the tubes for instrumentation is as follows:

Column 12. Based on progress of test specimen fabrication, Column 12 and Column 13 have already been fully installed, but no instrumentation was included. It is feasible to remove tube(s) from either end of the row of tubes installed at each of the four plenums in Column 12 to add instrumentation. Instrumentation of any tubes in Column

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 13 requires extensive disassembly of the specimen and is not practical. Because the outermost tube column has the highest susceptibility to FEI, two tubes from Column 12 are to be instrumented to provide the capability to characterize FEI.

Column 11. The center column of the tube bundle is the most removed from the tube bundle interfaces (vessel and riser wall) and should represent the most nominal flow conditions. Design of the test specimen included access ports that allow coupling up to four tubes to harmonic exciters. Therefore, four tubes are selected for instrumentation in this column to provide the greatest amount of instrumentation in the most representative columnand to allow maximum utilization of the harmonic exciter. The harmonic exciter is the only means of performing modal measurements on tubes in the fully-assembled test specimen.
Column 9. This is the innermost tube column in the specimen. In order to fully characterize the vibration response of the tube bundle, any potential variations in vibration response due to flow differences along the perimeter (i.e., riser surface) are assessed. Two tubes are selected for instrumentation in this column. Tubes at the bottom periphery of the tube bundle (including all tubes in innermost column) are potentially susceptible to VS.

A summary of instrumented tubes is provided in the following tables. Figures representing the physical layout of the instruments along each tube are provided in Appendix A. Table 5-5 Instrumented tubes (accelerometers and strain gauges) Test Tube Part Location Description Notes Tube # Number Column 11, tube 1 at steam This corresponds to the position of 1 A014.1101 plenum 4 (305.4°) Instrumented tube N.1. Column 11, tube 16 at steam This corresponds to the position of 2 A014.1116 plenum 2 (144.6°) Instrumented tube N.16. Table 5-6 Instrumented tubes (accelerometers only) Test Tube Part Location Notes Tube # Number Description Column 9 tube 15 at steam 3 A014.0915 To evaluate VS plenum 1 (~45°) Column 9 tube 16 at steam 4 A014.0916 To evaluate VS plenum 1 (~45°) Column 12, tube 1 at steam To evaluation limiting location 5 A014.1201 plenum 3 (~225°) for FEI Column 12, tube 2 at steam To evaluation limiting location 6 A014.1202 plenum 3 (~225°) for FEI © Copyright 2018 by NuScale Power, LLC 134

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-7 Instrumented tubes (strain gauges only) Test Tube Part Location Notes Tube # Number Description This corresponds to the position Column 11, tube 2 at steam 7 A014.1102 of Instrumented tube plenum 4 (307.1°) N.2. This corresponds to the position Column 11, tube 15 at steam 8 A014.1115 of Instrumented tube plenum 2 (144.3°) N.15. At least ten tri-axial accelerometers, including mounts and adapters suitable to support removable placement at various locations on individual tubes, are available for modal testing to be performed during test specimen fabrication. Removable accelerometer specifications are recommended by the supplier and approved by NuScale. Tri-axial accelerometers are used for permanent instrumentation of the tubes. Higher sensitivity (100 mV/g) is desired for the testing using removable accelerometers. Instrumented tubes (Columns 9, 11 and 12) contain 3.75 helical turns, which result in a total of 31 tube spans (length of tubing between two adjacent support) for each tube. Based on the non-symmetric placement of the tube supports, spans are alternatively long (64-degree arc) and short (26-degree arc). The first and subsequent odd-numbered spans are long and even-numbered spans are short. For the purpose of identifying instrument locations for the test specimen, instrument locations are identified to a specific span, based on numbering that originates at the steam plenum. The steam plenum numbering is based on FW plenum 1 being oriented at 45 degrees with the steam plenum numbering proceeding in a clockwise direction (steam plenum 2 is located at 135 degrees, and so on). For example, Span 1 is a long span and represents the tube span from the FW plenum steam tubesheet to the first support (e.g., steam transition bend). Span 31 is also a long span and represents the span of tubing from the last support to the FW tubesheet. Likewise, SG tube support circumferential position #1 is designated as corresponding to the tube support located immediately counter-clockwise from steam plenum 1 and SG tube support numbering proceeds in a clockwise manner, such that positions #1 and #2 are on each side of steam plenum 1. Figure A-1 provides a figure illustrating this numbering scheme. Accelerometer placement is in accordance with the following tables and figures. Figures A-1 through A-6 show physical placements of each accelerometer along the tube length and Figure A-10 provides a composite view of all accelerometer placements. © Copyright 2018 by NuScale Power, LLC 135

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-8 Accelerometers placement for instrumented tube #1 Accelerometer Location Notes Span 1 (steam transition), A1 Fundamental mode (fixed) mid-span A2 Span 11: mid span To detect prevalent fixed and pivot lower order modes To monitor for rigid body motion of the tube, e.g., movement of the tube due to FIV of the tube support A3 Span 14/15 at support (to which the tube is coupled), so that this can be differentiated from FIV of the tube itself. A4 Span 15: 1/3 span Span 15 has harmonic exciter coupling A5 Span 15: 1/2 span (nozzle N3) A6 Span 25: mid span To detect prevalent fixed and pivot lower order modes A7 Span 26/27 at support To monitor for rigid body motion of the tube A8 Span 27: 1/3 span To detect higher order modes, proximate A9 Span 27: 1/2 span to exciter location Span 29 has harmonic exciter coupling (nozzle N1), VS A10 Span 29: mid span susceptible location Table 5-9 Accelerometers placement for instrumented tube #2 Accelerometer Location Notes Span 1 (steam A11 transition): mid-span A12 Span 3: 1/3 span Span 3 has harmonic exciter coupling (nozzle N4) A13 Span 3: 1/2 span A14 Span 13: 1/3 span To detect prevalent fixed and pivot higher order A15 Span 13: 1/2 span modes, proximate to exciter A16 Span 15: mid span Span 15 has harmonic exciter coupling (nozzle N2) To detect prevalent fixed and pivot lower order A17 Span 17: mid span modes, proximate to exciter To detect prevalent fixed and pivot lower order A18 Span 25: mid span modes, proximate to exciter A19 Span 26: mid span To detect response of short spans To detect prevalent fixed and pivot lower order A20 Span 27: mid span modes, proximate to exciter © Copyright 2018 by NuScale Power, LLC 136

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-10 Accelerometers placement for instrumented tube #3 Accelerometer Location Notes Span 1 (steam transition): A21 Fundamental beam mode mid span A22 Span 7: 1/3 span To monitor for prevalent higher order modes A23 Span 7: 1/2 span A24 Span 11: mid span To monitor for prevalent first order modes A25 Span 13: mid span To monitor for prevalent first order modes A26 Span 23: 1/3 span To monitor for prevalent higher order modes A27 Span 23: 1/2 span A28 Span 27: mid span To monitor for prevalent first order modes A29 Span 30: mid span First short span from feed transition, susceptible to VS Span 31 (feed transition): VS shedding susceptible location, fundamental mode A30 mid span response (fixed) Table 5-11 Accelerometers placement for instrumented tube #4 Accelerometer Location Notes A31 Span 7: mid span A32 Span 13: 1/3 span To monitor for prevalent higher order modes A33 Span 13: 1/2 span A34 Span 13/14 at support To monitor for rigid body motion of the tube A35 Span 15: mid span To monitor for prevalent first order modes A36 Span 21: mid span To monitor for prevalent first order modes A37 Span 22/23 at support To monitor for rigid body motion of the tube A38 Span 23: mid span To monitor for prevalent first order modes A39 Span 29: mid span First long span from feed transition, susceptible to VS Span 31 (feed transition): VS shedding susceptible location, fundamental mode A40 mid span response (fixed) © Copyright 2018 by NuScale Power, LLC 137

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-12 Accelerometers placement for instrumented tube #5 Accelerometer Location Notes Span 1 (steam A41 Fundamental mode (pivot) transition): mid span A42 Span 5: mid span A43 Span 7: 1/3 span To monitor for higher order modes A44 Span 7: 1/2 span A45 Span 9: mid span A46 Span 21: mid span A47 Span 22: mid span To monitor for first order response mode of short span A48 Span 23: mid span A49 Span 29: mid-span VS shedding susceptible location Span 31 (feed transition): A50 VS shedding susceptible location mid-span Table 5-13 Accelerometers placement for instrumented tube #6 Accelerometer Location Notes Span 1 (steam transition): A51 Fundamental mode (pivot) mid span A52 Span 13: mid span A53 Span 13/14 at support To monitor for rigid body motion of the tube A54 Span 15: 1/3 span A55 Span 15: 1/2 span A56 Span 21: mid span A57 Span 23; 1/3 span To monitor for higher order modes A58 Span 23: 1/2 span A59 Span 23/24 at support To monitor for rigid body motion of the tube A60 Span 25: mid span A total of 32 uni-axial strain gauges are mounted on SG tubes as shown in Table 5-14. Appendix A Figures A-1, A-2, A-7, and A-8 show physical placements of each strain gauge along the tube length and Figure A-10 provides a composite view of strain gauge placements. Strain gauge placements are based on measuring strains associated with most prevalent vertical modes. Strain gauges are generally placed in spans that do not include accelerometers. This is both to increase the extent of specimen that contains at least some instrumentation and to minimize potential impact of instrumentation on measurements (heavily concentrating instrumentation in a single span further alters vibration response as compared to a span with no added mass due to instrumentation). © Copyright 2018 by NuScale Power, LLC 138

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-14 Tube strain gauge placements Instrumented Strain Gauge Location Notes Tube # Number S1, S2 Span 1, at steam plenum tubesheet face (( }}2(a),(c) S3, S4 S5, Span 15, each end, as close as practical

1, column 11, -

S6 to tube support tube 1 (( S7, S8 Span 31, at feed plenum tubesheet

                                                                                     }}2(a),(c)

S9, S10 Span 16, mid-span (( }}2(a),(c)

2, column 11, S11, S12 Span 17, mid-span (( }}2(a),(c) tube 16 S13, S14 Span 27, each end, as close as practical

(( }}2(a),(c) S15, S16 to tube support S17, S18 Span 11, mid-span - S19, S20 Span 13, each end, as close as practical

7, column 11, (( }}2(a),(c)

S21, S22 to tube support tube 2 (( S23, S24 Span 31, at feed plenum tubesheet

                                                                                     }}2(a),(c)

S25, S26 Span 15, each end, as close as practical ((

8, column 11, S27, S28 to tube support }}2(a),(c) tube 15 S29, S30 Span 31, at tube support (( }}2(a),(c)

S31, S32 Span 31, at tubesheet (( }}2(a),(c) There are six SG tube accelerometers (as shown in Table 5-15) that are coincident with a SG tube support. An accelerometer is placed on the corresponding tube support at a location coincident (to the extent practical) with each of these SG tube accelerometers. Table 5-15 Steam generator tube support accelerometer Column Corresponding SG Tube Radial Tube SG Tube Instrumented Support Position Support Position Accelerometer Tube # (Circumferential) (Radial) SG tube support A3 1 11 Circumferential position #5 between Col 11/12 SG tube support A7 1 11 Circumferential position #1 between Col 11/12 SG tube support A34 4 9 Circumferential position #6 between Col 9/10 SG tube support A37 4 9 Circumferential position #6 between Col 9/10 SG tube support A53 6 12 Circumferential position #1 between Col 12/13 SG tube support A59 6 12 Circumferential position #7 between Col 12/13 Based on Table 5-15, there are a total of four upper and lower SG supports (at circumferential locations #1, #5, #6 and #7) that have corresponding tube accelerometers to monitor for rigid body motions of the SG tube supports. Accelerometers are placed on both the upper and lower SG supports at each of these locations (eight accelerometers). © Copyright 2018 by NuScale Power, LLC 139

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Likewise, a paired accelerometer is placed on the SG tube support along with each of these accelerometers (eight accelerometers). Sixteen accelerometers are placed on the vessels to evaluate potential modal responses of the entire test specimen. Based on pre-test modal analysis, depending on the boundary conditions that exist, the vessel shells respond in beam modes (( }}2(a),(c), shell modes (( }}2(a),(c) or torsional modes (( }}2(a),(c). Eight inside of the inner vessel (i.e., riser), two sets of four accelerometers (at approximately 1/10, 2/5, 3/5 and 9/10 heights, vertically in-line), offset circumferentially by 90 degrees. Eight outside of primary vessel, two sets of four accelerometers (at approximately 1/10, 2/5. 3/5 and 9/10 height vertically in-line), offset circumferentially by 90 degrees. The inner wall of the vessel is instrumented with 14 dynamic pressure transducers to characterize a turbulent pressure force PSD for steady flow conditions. Other sensors included in this test are documented in Table 5-16. Table 5-16 Other pressure and temperature instrumentation Measurement Total Description Number Temperature 2 Primary-side inlet and outlet temperature Pressure 5 Primary-side static pressure spaced over height Primary-side pressure drop spaced over height (pressure drop Differential pressure 4 measurements are developed based on differentials between five pressure instruments) Flow 2 Primary-side flow For the purposes of this testing, frequencies up to 500 Hz are of interest; therefore, DAS sampling rates for modal and damping tests are at least 2000 Hz. Lower DAS operating frequencies are permitted for FEI and VS tests (these phenomena are associated with frequencies (( }}2(a),(c). Damping tests require DAS capabilities to provide near real-time calculated damping measurements. This includes the DAS being pre-programmed to determine transfer function(s) for fixed exciter damping tests. The DAS is capable of measuring both large-amplitude, slow-changing strain (i.e., static strain) and low-amplitude, rapid-cycling strain (i.e., dynamic strain). Evaluation of the FIV phenomena described herein requires only dynamic strains; however, knowledge of static strain changes and variations throughout testing may be of benefit in understanding boundary conditions at the support interface points. Before each dynamic strain measurement (e.g., damping, modal- or flow-test dataset), the static and average strains are measured to establish a baseline. In order to facilitate accurate measurement of both static and dynamic strains, the DAS includes one of the following features or equivalent © Copyright 2018 by NuScale Power, LLC 140

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 measures to address accurate measurement, as recommended by the testing organization and approved by NuScale:

Capability to measure with high-range (low-gain) settings for static strains, output the analog (raw) signals, and use separate hardware to measure with low-range (high-gain) settings for dynamic strains (high-gain measurements is zero-centered for ease of data post-processing).
Capability to auto-balance (null-calibrate) each channel, with procedures or software features to re-zero strain signals before each test series dataset (to avoid signal saturation). The DAS must record all such adjustments such that an accurate static strain representation can be reproduced.

5.1.1.3 Description of TF-3 Tests 5.1.1.3.1 Partial-Tube Array Testing During Fabrication In-air mode testing is performed on individual tubes in fully assembled columns during the fabrication process. Testing is performed after each of the columns containing permanently instrumented tubes (Columns 9, 11 and 12) is fully installed, including associated tube supports. Testing is performed with up to three variable levels of compression applied by temporary tube bundle supports. Testing with variable levels of support compression evaluates potential variations in frequency that could result from differences in the boundary conditions between the SG tubes and supports. Tube excitation using impulse hammer strikes or other means such as a harmonic exciter, is utilized for partial-tube array testing performed during test specimen fabrication. Access to perform impulse tests is precluded once test specimen is fully assembled with the riser installed. Specific requirements for impulse hammer(s) necessary to provide measurable response for the test specimen tubes are provided by the testing services supplier and approved by NuScale. Fixed point excitation capabilities using a harmonic exciter is provided for instrumented tubes #1, #2, #7 and #8 (column 11) through access nozzles N1, N2, N3, and N4. Fixed point excitation is only used for full-tube array tests (in-air and in-water modal and damping tests). The harmonic exciter is capable of providing a range of displacements and operating over a frequency range of at least 5 to 500 Hz. Specific tubes and spans to be evaluated for these tests are in accordance with Table 5-17. © Copyright 2018 by NuScale Power, LLC 141

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-17 Partial-tube array modal tests Tube Column Description Extent Long spans, any short spans with Instrumented Tube #5 12 Permanently instrumented permanent instrumentation 10 long spans (including all long spans with permanent Instrumented Tube #6 12 Permanently instrumented instrumentation), any short spans with permanent instrumentation Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing from near each end (feed and W12 12 based on loosely held tube steam plenum tube sheets), and one group from both ~1/3 and

                                                                         ~2/3 of the full length of the test specimen Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing       from near each end (feed and X12                    12 based on tightly held tube    steam plenum tube sheets), and one group from both ~1/3 and
                                                                         ~2/3 of the full length of the test specimen Span(s) selected during testing, all tube segments in span are evaluated to assess variability in 2 long spans, mode frequencies Multiple                 12      boundary conditions (tubes only exhibit frequencies associated with fixed, pivot or hybrid boundary conditions)

All long spans, any short spans Instrumented Tube #1 11 Permanently instrumented with permanent instrumentation Ten long spans (including any long spans with permanent Instrumented Tube #2 11 Permanently instrumented instrumentation), any short spans with permanent instrumentation © Copyright 2018 by NuScale Power, LLC 142

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Tube Column Description Extent Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing from near each end (feed and W11 11 based on loosely held tube steam plenum tube sheets), and one group from both ~1/3 and

                                                                         ~2/3 of the full length of the test specimen Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing       from near each end (feed and X11                    11 based on tightly held tube    steam plenum tube sheets), and one group from both ~1/3 and
                                                                         ~2/3 of the full length of the test specimen Two long spans, mode Multiple                 11 frequencies only All long spans, any short spans Instrumented Tube #3               9      Permanently instrumented with permanent instrumentation Ten long spans (including any long spans with permanent Instrumented Tube #4               9      Permanently instrumented instrumentation), any short spans with permanent instrumentation Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing       from near each end (feed and W9                     9 based on loosely held tube    steam plenum tube sheets), and one group from both ~1/3 and
                                                                         ~2/3 of the full length of the test specimen Four groups of five spans (long/short/long/short/long) selected to provide one group Selected during testing       from near each end (feed and X9                     9 based on tightly held tube    steam plenum tube sheets), and one group from both ~1/3 and
                                                                         ~2/3 of the full length of the test specimen Two long spans, mode Multiple                  9 frequencies only

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 There are three technical objectives of the modal testing during tube bundle fabrication:

Reproducibly measure mode frequencies and mode shapes (goal of characterization of up to four mode shapes and frequencies per tube) using impulse excitation.
Evaluate range of tube modal responses. Based on preliminary modal measurements, a range of frequencies (representing pivot and fixed boundary conditions) are expected.
Obtain consistent modal measurements for temporary and permanent instrumentation.

Testing is conducted by placing temporary accelerometers, taking measurements and then repeating as necessary to obtain required data. The specific placement of temporary accelerometers to perform this portion of the testing is determined by the test performer as necessary to meet the test objectives. NuScale provides concurrence that necessary modal measurements have been achieved if less than four modes can be measured for a given tube. For testing Columns 9 and 11, extent of modal testing for tubes W and X may be reduced based on demonstrated consistency of results with tests for other columns and locations in the tube array. Three-dimensional mode shape functions are developed for as many modes as possible (up to a goal of four), including at least one first-order beam mode for each tube tested. For each individual mode shape and frequency that can be characterized for each variable level of temporary support compression, at least two sets of duplicate measurements are obtained. If divergent results are observed for the duplicate tests, additional test runs may be requested until consistent results are observed. Accelerometers are not required to be re-positioned to obtain duplicate data sets. Mode shapes are defined in a local coordinate system. Locations of removable accelerometers are recorded to within an accuracy of (( }}2(a),(c) inches. Rotational position (e.g., bottom dead center, top dead center, and so on) of each span tested is also recorded to evaluate the impact of the horizontal orientation of the test fixture. In addition to data from removable accelerometers, data is recorded using permanently installed strain gauges and accelerometers in the tested tubes. 5.1.1.3.2 In-Air Damping Tests Damping tests are performed on the same individual tubes that are characterized as part of partial tube array fabrication modal testing. This includes testing performed with up to three variable levels of compression applied by temporary tube bundle supports. Tests are performed on tubes in Columns 9, 11 and 12. The extent of damping measurements in each column is based on the number of individual modes that are successfully characterized as part of the partial tube array fabrication modal testing. Damping values for a maximum of four modes for each of four tubes in each column (total of sixteen damping values) are measured. Damping values for each tube and mode are developed using both logarithmic decrement and half-power bandwidth methods. Damping testing includes evaluation of amplitude specific damping. © Copyright 2018 by NuScale Power, LLC 144

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The specific placement of temporary accelerometers to perform this portion of the testing is determined based on the test objectives. In addition to data from removable accelerometers, data is recorded using permanently installed strain gauges and accelerometers in the tested tubes. There are two primary objectives of this testing:

Reproducibly measure damping values for modal frequencies characterized during partial tube array fabrication modal testing. Damping values are determined using at least two methods (logarithmic decrement and half-power bandwidth methods)
Determine variability in damping values between different tubes and as a function of modal frequency.

Minimum duration of data files is agreed upon by NuScale and the testing services supplier. Both half power and logarithmic decrement methods are used to determine damping values. For each individual tube and frequency that can be characterized, damping values are obtained using each method. For each damping value measured for each method, a duplicate set of damping values is obtained. If divergent results are observed for the duplicate tests, additional test runs may be requested until consistent results are observed. Logarithmic decrement and half-power bandwidth methods produce different ranges of damping values (results from each method are not expected to show strong agreement). Therefore, testing objectives are satisfied when reproducible results are produced for each method, even if the results obtained for each method are not in agreement. 5.1.1.3.3 Tube Array Testing: In-Air Natural Frequencies and Mode Shapes This testing obtains frequency and mode shape measurements comparable to those observed in the tests during tube bundle fabrication. With the exception of possible limited access for tubes #3 and #4 (Column 9), impulse excitation is not possible for these tests. Therefore, a fixed point exciter is used to measure mode frequencies and mode shapes of only tubes in Column 11 (Instrumented tube #1, #2, #7 and #8). Initial testing is performed by frequency sweep testing for frequencies between 5 and 500 Hz. Frequency sweep rates are recommended by the testing services supplier and approved by NuScale. Following this initial sweep testing, harmonic sweep testing around frequencies characterized during individual tube testing of Column 11 tubes is performed if broad spectrum sweep testing did not adequately characterize these modes. Measurements are obtained for each tube using excitation at each of the fixed points (two to three points per tube, based on access through N1, N2, N3 and N4). At least two duplicate sets of measurements are obtained for each tube at each discernable modal frequency with excitation from each exciter coupling location. In addition, excitation in frequency ranges corresponding to any predicted predominant frequencies not characterized during the individual tube testing is performed. This testing is to confirm the boundary conditions (as indicated by observed modal frequencies) in the © Copyright 2018 by NuScale Power, LLC 145

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 fully-assembled tube array are consistent with those during the testing during the fabrication process. During this testing, it is only necessary to record data for the individual tubes to which excitation is applied. Repetition of some or all tests using altered tube bundle compression forces is performed. Damping values associated with each individual frequency detected are based on determination of the transfer function (i.e., FRF) for each tube. Excitation for damping tests is performed using the fixed-point exciter system and includes determination of amplitude dependency of damping. Results are obtained for permanently instrumented tubes in Column 11 (instrumented tubes #1, #2, #7 and #8). 5.1.1.3.4 Tube Array Testing: In-Water Natural Frequencies and Mode Shapes The objectives, conduct, and necessary data for this testing are identical to the full array in-air natural frequency and mode shape testing, with the exception that the test specimen be maintained full of stagnant water. The objectives, conduct, and necessary data for this testing are identical to the full array in-air natural damping testing, with the exception that the test specimen be maintained full of stagnant water. 5.1.1.4 TF-3 Steady-State Flow Testing These tests are devoted to fully characterizing the vibration amplitudes of the HCSG as function of normal primary flow velocities. Measurements are also performed with no flow conditions to determine background noise levels. When increasing flow velocity, displacement amplitudes are monitored so that the test can be suspended if the onset of instability is observed. Because flows in this phase of testing are limited to 100 percent normal design flow, no unusual vibration is expected. The general requirements of this testing are steady flow runs of a minimum of five minutes at each test run, with recording of a dedicated test point data file for a minimum of two minutes at each test run. Once steady flow conditions have been observed for at least three minutes (based on concurrence with the NuScale test engineer, as supported by relevant instrument readings), a minimum of two minutes of data are recorded to a dedicated file for the test point. Minimum testing points are in accordance with Table 5-18. © Copyright 2018 by NuScale Power, LLC 146

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-18 Steady-state flow flow-induced vibration tests Flow Vgap Test Run Description (gpm) (ft/s) 1 (( Baseline 2 3 25% flow 4 5 50% flow 6 7 75% flow 8 9 100% flow 2(a),(c) 10 }} The PSD functions cover a range of non-dimensional reduced frequencies (frequency*tube diameter/Vgap) up to 10. The flow test points in Table 5-20 provide data to validate the design PSD over the prescribed range of reduced frequencies. Each steady-state flow test run is repeated on a different day from the first test run. If divergent results are observed for the duplicate tests, additional test runs may be requested until consistent results are observed. 5.1.1.5 TF-3 Vortex Shedding Flow Testing This test is to demonstrate that the SG design is not susceptible to VS phenomena. The VS can cause excessive vibration when alternating vortices are induced at a frequency that is at or near a modal frequency of the structure. The purpose of these tests is to evaluate flow rates which could induce VS at frequencies coincident with modal frequencies of individual tubes at the bottom periphery of the tube bundle by measuring vibration amplitudes that result during these flowrates. Flow rates necessary to cover the range of VS frequencies are provided in Table 5-19. Vortex shedding may occur when the Vgap is in proximity to a structural frequency (perfect coincidence is not necessary); therefore, testing at only specific points is not sufficient to characterize this phenomena. As there are many closely-spaced modal frequencies of the tubes within part of the range where tube natural frequencies and VS frequencies coincide, the testing approach requires taking sufficient data at flowrates throughout this range to fully demonstrate VS is precluded. It is understood there may be practical limitations with respect to fine adjustment of flow velocities using high-capacity pumps; therefore, the proposed test sequence may be adjusted to facilitate available control capability. © Copyright 2018 by NuScale Power, LLC 147

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-19 Vortex shedding test points1, 2 Bulk flow Vgap fs Basis (gal/min) (ft/s) (Hz) (( }}2(a),(c) Approximate frequency of fundamental tube mode (( }}2(a),(c) Approximate frequency of second tube mode (( }}2(a),(c) Approximate frequency of third tube mode (( }}2(a),(c) (( }}2(a),(c) Approximate frequency of fourth tube mode (( }}2(a),(c) Closely-spaced modes in this frequency range (( }}2(a),(c) Closely-spaced modes in this frequency range Testing at this level bounds all design conditions with (( }}2(a),(c) sufficient margin Note 1: there is some overlap of the VS test conditions, steady-state flow test, and FEI test conditions. A consolidated test matrix that includes common flow conditions that satisfy evaluation of all phenomena may be developed. Note 2: test points may be adjusted based on results of modal testing to ensure test runs most closely correspond with actual measured structural frequencies of the test array. The VS tests include a minimum of five minutes of steady-state flow with recording of a dedicated test point data file for a minimum of two minutes at each test point. Once steady flow conditions have been observed for at least three minutes, a minimum of two minutes of data are recorded to a dedicated file for the test point. If large tube displacements (characteristic of VS) are observed, duration of data files may be reduced to prevent possible damage to the test specimen. The VS is associated with the fundamental or other lower frequency modes (less than (( }}2(a),(c)), therefore data acquisition rate may be reduced for this testing. Flowrate changes between test points are controlled such that changes in flowrate do not exceed 10 percent per minute. Each VS flow test run is repeated on a different day from the first test run. If divergent results are observed for the duplicate tests, additional test runs may be requested until consistent results are observed. Likewise, if any indication of VS occurs during transitions, additional test points are added to examine flow rates intermediate to the test points specified in Table 5-19. 5.1.1.6 TF-3 Fluid Elastic Instability Flow Testing This test is to demonstrate the onset (or lack of) of FEI in the NuScale HCSG to demonstrate design margin. However, the ability to demonstrate the onset of FEI in this test may be impossible for two reasons, 1) it is possible that a helical tube design is immune to FEI phenomena based on unique design features (de-tuning based on array including tubes of various frequencies, cannot be synchronously excited in a single mode), and 2) if margin to FEI is significantly larger than predicted, test facility flow rates are inadequate to reach FEI. Based on achieving maximum possible test flow rates without onset of FEI, adequate design margin is demonstrated. © Copyright 2018 by NuScale Power, LLC 148

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The general requirements of this testing are that steady-state flow runs of five minutes with recording of a dedicated test point data file for a minimum of two minutes at each test point. Once steady flow conditions have been observed for at least three minutes, a minimum of two minutes of data are recorded to a dedicated file for the test point. If large tube displacements are observed, duration of data files may be reduced to prevent possible damage to the test specimen. Fluid elastic instability is associated with the fundamental or other lower frequency modes (less than (( }}2(a),(c) for the NuScale design); therefore, data acquisition rate may be reduced for this testing. Flowrate changes between test points are controlled such changes in flowrate do not exceed 10 percent per minute. Fluid elastic instability is characterized by synchronized vibration of the tube array at a common frequency (predicted to be between (( }}2(a),(c) for this test specimen). Continuous monitoring of vibration amplitude frequency of available strain gauges and accelerometers is necessary during FEI testing to accurately identify the onset of FEI, if it occurs. If the onset of FEI is observed, flow rates are immediately reduced and concurrence from NuScale obtained before subsequent increases in flow rates. Minimum testing is in accordance with Table 5-20. Table 5-20 Fluid elastic instability flow tests Vgap Test Run Flow (gpm) Description (ft/s) 1 (( 2 Predicted onset of FEI (conservative Connors 3 constants) 4 Predicted onset of FEI (best estimate Connors 5 constants) 6 7 Additional test points up to maximum flow or onset of FEI, as directed by NuScale Max flow test, with concurrence of NuScale if no 8 }}2(a),(c) indication of FEI is observed at all previous test points. Each FEI flow test run is repeated on a different day from the first test run. If divergent results are observed for the duplicate tests, additional test runs may be requested until consistent results are observed. 5.1.1.7 TF-3 Results Scope The Summary Test Report includes the following:

test description

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

list and discussion of test anomalies and test procedure changes
assessment of test data acceptability
any relevant data plots or tables The Final Test Report includes the following:
raw data
calculations, including methodology and results summaries
checksums for the non-encrypted reduced and calculated data sets
reduced and calculated data in an encrypted file
instrument calibration certificates
test readiness inspection report
completed, filled out, and signed test procedures
test logs 5.1.2 TF-3 Modal Analysis Pre-Test Prediction This calculation is to predict the modal response of the steam generator TF-3 test specimen. The TF-3 test specimen is a full-scale representation of Columns 9 through 13 of the NuScale power module SG. This calculation supports the TF-3 test program.

This calculation applies only to the TF-3 test specimen design. Individual tube models as well as a TF-3 full-bundle model are used in the analysis. The type of results generated in this calculation are:

Modal frequencies, mass participations, and mode shapes for individual tube models of Columns 9, 11, and 13
Sensitivity studies to determine the effect of different boundary conditions, mesh sizes, and the influence of primary-side water (dry vs wet conditions)
Recommended strain gauge placement to capture dominant modes of Column 11 tubes
Mode frequencies and mass participations of the TF-3 full-bundle model compared to the individual tube models Three different coordinate systems types are used in this calculation for the models. They are described below and pictured in Figure 5-1. Note that all coordinate systems are located at global zero, but are shown at different locations in the figure for clarity. The figure also shows images of the TF-3 full-bundle model, but the coordinate systems apply to the individual models as well.
Global Cartesian coordinate system: X and Z are horizontal directions, and Y points vertically upward. This is ANSYS coordinate system 0 (CSYS 0).
Global cylindrical coordinate system: X is the radial direction, Y is the circumferential direction, and Z points vertically upward. This is ANSYS coordinate system 5 (CSYS 5).

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

Local coordinate systems: Forty unique local Cartesian coordinate systems are used for coupling tubes to tube supports, one assigned to each of the forty tube supports.

From the perspective of the interface, the local X is along the tube axis and Z points radially inward toward the center of the bundle. The local Y axis is perpendicular to these two, and is angled away from the global vertical direction by the tube inclination angle (approximately13° to 14°). The ANSYS coordinate system number is the column number followed by the tube support number. For example, Column 13, tube support 7 is coordinate system 137 (CSYS 137). ((

                                                                                                          }}2(a),(c)

Figure 5-1 Coordinate systems shown from global isometric view The numbering system for identifying the circumferential positions of the tube supports (as used above in defining CSYS 137), tubesheets, and tube ends is shown in Figure 5-2. This applies to both individual tube models and the full-bundle model. This numbering system is for bookkeeping within the ANSYS models only and does not represent any numbering system used in the TF-3 or SG drawings. © Copyright 2018 by NuScale Power, LLC 151

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Figure 5-2 Numbering system for circumferential positions (CSYS 0 shown) 5.1.2.1 Single-Tube Models This calculation includes individual tube models for Columns 9, 11, and 13. The model for each column contains the two bounding tubes, one at each end of a row of tubes in the tubesheet. Columns 9, 11 and 13 are shown in Figure 5-3. The tube geometry of the TF-3 test specimen is the same as the tube geometry for the NuScale Power Module SG. © Copyright 2018 by NuScale Power, LLC 152

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Figure 5-3 Representative tubes for individual tube models The individual tube models are meshed with 1-inch BEAM188 elements, which do not have midside nodes. The exception to this is in the mesh sensitivity analysis, which uses 12-inch BEAM189 elements with midside nodes (see Section 5.1.2.6). The tubes are assigned Type 304 stainless steel material properties at 70 degrees Fahrenheit. For analyzing the test conditions with water on the primary side, the material density is adjusted to account for the displaced water mass of the tube (added mass effect). The effect of the added mass is analyzed in Section 5.1.2.5. Boundary conditions are applied to the tubes to simulate the connections to the tubesheets and tube supports, which are not explicitly modeled. The edges at the ends of the tubes have all degrees of freedom constrained to simulate the connection where the tubes are inserted and welded to the tubesheets (the inserted length is fixed). The tube vertices at the tube support interface locations are constrained using the local coordinate system directions. Two combinations of constraints are analyzed: pivot and fixed. For the pivot case, only the local UY and UZ are constrained, which allows for a © Copyright 2018 by NuScale Power, LLC 153

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 tube to pivot about any direction, as well as slide along its axis. For the fixed case, the local displacements (UX, UY, UZ), rotation in Y direction (ROTY), and rotation in Z direction (ROTZ) are constrained, but twisting about the tube axis is still free. The additional constraints simulate a condition where the tube supports are pressed together and provide more clamping on the tube. This condition occurs in the NuScale Power Module SG due to thermal expansion differences and/or tolerance stack-up. These two boundary condition combinations should bound any possible modal behavior. A depiction of the boundary condition locations is shown in Figure 5-4. ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.2.2 TF-3 Full Bundle Model This section describes the TF-3 full bundle model, which explicitly models all tubes, tube supports, and vessels in a single ANSYS model. Details of the vessels have been simplified to reduce mesh complexity. The top head, bolts, vessel penetrations, cover plates, and small features have been removed. These components have negligible stiffness compared to the major components of the specimen that are modeled. For example, although the top head is stiff, it is negligible compared to the 5-inch thick steam tubesheet to which it attaches. The mass of these components is added back into the model in order to maintain the correct overall mass-to-stiffness ratio. The TF-3 vessels and tubesheets are modeled using surface bodies at the nominal mid-surface of the thickness. One exception to this is the steam tubesheet, which uses an offset in order to properly interface with the surfaces beneath it, while still maintaining the stiffness at the correct elevation. Also, some stiffener ring elevations were adjusted slightly (less than 0.65 inch) in order to line up with elevations of other components. This avoids skinny elements with poor aspect ratios without affecting overall specimen behavior. The tubes are made of line bodies with a circular tube cross-section. The inner radius is (( }}2(a),(c) inch and the outer radius is (( }}2(a),(c) inch. The tube supports are made of line bodies with rectangular cross-sections. The cross-section of the main tube support body is (( }}2(a),(c) inch wide and (( }}2(a),(c) inch thick. This gives equivalent bending stiffness as the detailed geometry design. The rectangular cross-section of the tube support tabs has the nominal dimensions of (( }}2(a),(c) thick. The geometry of the TF-3 full bundle model is shown in Figure 5-5. The tubes are meshed with BEAM189 elements, which include midside nodes. The element length is set to 12 inches, which was determined to be adequate as described in Section 5.1.2.6. The tube mesh is shown in Figure 5-6 and Figure 5-7. The tube supports are meshed with BEAM188 elements that do not include midside nodes. Midside nodes are not necessary due to the small element size of less than 1 inch. The small elements are necessary to characterize the correct spacing between adjacent tabs and between adjacent tube supports. The tube support mesh is shown in Figure 5-6 and Figure 5-7. The vessels and tubesheets are meshed with SHELL281 elements that include midside nodes. The element size varies between 13 inches for the general shell regions, down to 1 inch at the tubesheet interface with the tubes. The vessels and tubesheet mesh are shown in Figure 5-6. © Copyright 2018 by NuScale Power, LLC 155

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 5-7 Tube and tube support mesh Bodies are assigned material properties for Type 304 stainless steel at 70 degrees Fahrenheit. This is the correct material for most components in the test specimen. It is a simplification of the tubesheet material, any differences in density are compensated by the mass corrections. The tube support tab material uses a stiffer elastic modulus. This arbitrarily stiff value is used to properly couple the moments between the center of the tab and the base of the tab where it connects with the main tube support body. In the true design, the moments are coupled by multiple tabs with significant horizontal spacing, which is not easily achievable in the simplified beam model representation. This simplification only impacts the TF-3 full bundle model where moments are coupled between the tubes and supports (fixed boundary condition). © Copyright 2018 by NuScale Power, LLC 158

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Because many features of the TF-3 specimen have been removed from the model geometry, their masses must be added back to maintain the overall mass of the specimen. This is done by applying distributed masses in ANSYS Workbench Mechanical. The mass correction is split into two sections: the top head and the shells. The top head mass is calculated by multiplying the detailed head geometry volume by the density for Type 304 stainless steel. The remaining mass that is applied to the shells is the difference between the vessel target mass, and the modeled vessel mass and head mass. This is summarized in Figure 5-8 and Table 5-21. The top head distributed mass is applied to the steam tubesheet surface and the shell mass is applied to the outer vessel surface. © Copyright 2018 by NuScale Power, LLC 159

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                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-21 Mass correction for vessels Item Description Value Reference Top head volume (in^3) (( }}2(a),(c) Figure 5-8 Top head density (lbm/in^3) (( }}2(a),(c) Type 304 SS at 70°F Top head mass to add (lbm) (( }}2(a),(c) = top head volume

density Total target mass for vessels (lbm) (( }}2(a),(c)

Modeled vessel mass (lbm) (( }}2(a),(c) Added top head mass (lbm) (( }}2(a),(c) calculated top head mass above

                                                                   = target mass - modeled vessel mass -

Shell mass to add (lbm) (( }}2(a),(c) top head mass The mass of the tubes and tube supports do not need correction. The tubes are modeled with their true geometry and the tube supports end up at nearly the correct mass despite having a simplified geometry. The modeled tube support volume is only 1 percent different than the actual volume. 5.1.2.3 Boundary Conditions This section explains the various boundary conditions and constraint equations used in the TF-3 full bundle model to couple the components together. The shell bodies do not require additional coupling to each other, as they all share a conformal mesh as a single part. In the following figures, shell thicknesses and beam cross-sections are turned on or off depending on which provides the greatest clarity. The bottom edge of the TF-3 full bundle model has a fixed boundary condition applied. This simulates the entire specimen bolted to the foundation. Nodes near the top of each tube are coupled to corresponding nodes on the steam tubesheet. Nodes near the bottom of each tube are coupled to corresponding nodes on the feed tubesheets. All degrees of freedom are coupled at each connection. This simulates the inserted and welded tube in the tubesheet. The coupling is performed using constraint equations written in an ANSYS parametric design language (APDL) command object named Commands (APDL) - tubes to sheets - tube sups to SG sups. A visualization of the constraint equation coupling is shown in Figure 5-10. © Copyright 2018 by NuScale Power, LLC 161

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                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 5-10 Tube to tubesheet coupling: steam tubesheet (top), feedwater tubesheet (bottom) Nodes near the top of each tube support are coupled to corresponding nodes on the upper SG supports. Nodes near the bottom of each tube support are coupled to corresponding nodes on the lower SG supports. For the upper connection, the UX, UY, and UZ of the global cylindrical coordinate system (CSYS 5) are coupled. For the lower connection, the UX and UY of the global cylindrical coordinate system (CSYS 5) are coupled. The coupling is performed using constraint equations written in an APDL command object named Commands (APDL) - tubes to sheets - tube sups to SG sups. A visualization of the constraint equation coupling is shown in Figure 5-11. © Copyright 2018 by NuScale Power, LLC 163

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                                                                                                          }}2(a),(c)

Figure 5-11 Tube support to steam generator support coupling: upper connection (top), lower connection (bottom) Tube nodes are coupled to tube support tab nodes at each interface. For the pivot case, the local UY and UZ are coupled. For the fixed case, the local UX, UY, UZ, ROTY, and ROTZ are coupled. The coupling is performed using constraint equations written in an APDL command object named Commands (APDL) - tubes to tube sups. A visualization of the constraint equation coupling is shown in Figure 5-12. © Copyright 2018 by NuScale Power, LLC 164

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                                                                                                          }}2(a),(c)

Figure 5-12 Tube to tube support coupling. The tube support tab tip nodes are coupled to the adjacent tube support back nodes. A given tip node is coupled to two back nodes using a weighted average. For the nominal case, the UX, UY, and ROTZ of the global cylindrical coordinate system (CSYS 5) are coupled. The coupling is performed using constraint equations written in an APDL command object named Commands (APDL) - tubes sups to tube sups and vessels. The supports are only coupled together at certain elevation intervals, approximately every 9 inches. Because the tube support design has pockets machined out of the back, tabs from the adjacent support may protrude into the pocket and not interface with the support. Because of this, the tube support design uses spacers every 18 inches to fill in the pockets and guarantee contact with an adjacent tab. It is also likely that contact will still be made at non-spacer locations, so 9 inches was selected as the interval between sets of constraint equations. A visualization of the constraint equation coupling is shown in Figure 5-13. © Copyright 2018 by NuScale Power, LLC 165

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                                                                                                          }}2(a),(c)

Figure 5-13 Various views of tube support to tube support coupling Using a similar methodology to the section above, the Column 9 tube support tips are coupled to the inner vessel (i.e., riser) and the Column 13 tube support backs are coupled to the outer vessel. Because the mesh of the vessels is much coarser than the tube supports, each vessel node within the region of interest is coupled to the two closest tube support nodes using a weighted average. The same degrees of freedom are coupled as the above section, except for the interface between Column 13 tube supports and the outer vessel, where the moment about the vertical axis is not coupled. This is because the back face of the support does not fully engage with the vessel and the support is free to pivot around the vertical alignment strip welded to the vessel. The coupling is performed using constraint equations written in an APDL command object named Commands (APDL) - tubes sups to tube sups and vessels. A visualization of the constraint equation coupling is shown in Figure 5-14 and Figure 5-15. © Copyright 2018 by NuScale Power, LLC 166

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 5-15 Column 13 tube support to outer vessel coupling 5.1.2.4 Modal Analysis - Individual Tube Models Modal analysis is performed for the individual tube models. These include sensitivity analyses for different boundary conditions, dry vs. wet conditions, and different mesh sizes. It also includes strain gauge placement recommendations based on modal analysis of Column 11. Modal analysis was performed up to 1000 Hz using the individual tube models to determine the sensitivity to the two sets of boundary conditions, pivot and fixed. The pivot condition has the local UY and UZ constrained at each tube support interface location. The fixed condition has the local UX, UY, UZ, ROTY, and ROTZ constrained. © Copyright 2018 by NuScale Power, LLC 168

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The analyses were performed for Column 9 and Column 13 individual tube dry models. The tabulated results of the 20 modes with highest mass participation plus the fundamental mode are shown in Table 5-22 through Table 5-24. Results are shown in the global Cartesian coordinate system (CSYS, 0). The mode shapes of the fundamental mode and highest y-direction mass participation mode are shown in Figure 5-16 and Figure 5-17 for the pivot case, and in Figure 5-18 and Figure 5-19 for the fixed case. Column 13 dry model is used as the example. The mode shapes for all modes below 300 Hz are written to text files. The fixed results show significant increase in the modal frequencies. The fixed results also have the majority of the mass participation above 1000 Hz for the horizontal directions. Column 13 shows similar trends as Column 9, but with reduced frequency. © Copyright 2018 by NuScale Power, LLC 169

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-22 Pivot vs. fixed dry modal results for Columns 9 and 13 in x-direction (horizontal) Column 9 Pivot, X (horiz) Column 13 Pivot, X (horiz) Column 9 Fixed, X (horiz) Column 13 Fixed, X (horiz) MASS MASS MASS MASS FREQ. FREQ. FREQ. FREQ. MODE PARTIC. MODE PARTIC. MODE PARTIC. MODE PARTIC. (HZ) (HZ) (HZ) (HZ) RATIO, X RATIO, X RATIO, X RATIO, X 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 11 (( }}2(a),(c) 7 (( }}2(a),(c) 17 (( }}2(a),(c) 15 (( }}2(a),(c) 14 (( }}2(a),(c) 11 (( }}2(a),(c) 18 (( }}2(a),(c) 16 (( }}2(a),(c) 15 (( }}2(a),(c) 12 (( }}2(a),(c) 50 (( }}2(a),(c) 44 (( }}2(a),(c) 16 (( }}2(a),(c) 13 (( }}2(a),(c) 51 (( }}2(a),(c) 47 (( }}2(a),(c) 17 (( }}2(a),(c) 14 (( }}2(a),(c) 208 (( }}2(a),(c) 229 (( }}2(a),(c) 18 (( }}2(a),(c) 15 (( }}2(a),(c) 209 (( }}2(a),(c) 230 (( }}2(a),(c) 19 (( }}2(a),(c) 18 (( }}2(a),(c) 263 (( }}2(a),(c) 238 (( }}2(a),(c) 33 (( }}2(a),(c) 19 (( }}2(a),(c) 264 (( }}2(a),(c) 239 (( }}2(a),(c) 61 (( }}2(a),(c) 21 (( }}2(a),(c) 266 (( }}2(a),(c) 248 (( }}2(a),(c) 144 (( }}2(a),(c) 43 (( }}2(a),(c) 265 (( }}2(a),(c) 249 (( }}2(a),(c) 145 (( }}2(a),(c) 52 (( }}2(a),(c) 278 (( }}2(a),(c) 250 (( }}2(a),(c) 147 (( }}2(a),(c) 122 (( }}2(a),(c) 277 (( }}2(a),(c) 253 (( }}2(a),(c) 149 (( }}2(a),(c) 124 (( }}2(a),(c) 279 (( }}2(a),(c) 254 (( }}2(a),(c) 150 (( }}2(a),(c) 127 (( }}2(a),(c) 280 (( }}2(a),(c) 255 (( }}2(a),(c) 213 (( }}2(a),(c) 130 (( }}2(a),(c) 289 (( }}2(a),(c) 320 (( }}2(a),(c) 215 (( }}2(a),(c) 185 (( }}2(a),(c) 290 (( }}2(a),(c) 331 (( }}2(a),(c) 216 (( }}2(a),(c) 186 (( }}2(a),(c) 322 (( }}2(a),(c) 333 (( }}2(a),(c) 231 (( }}2(a),(c) 189 (( }}2(a),(c) 325 (( }}2(a),(c) 334 (( }}2(a),(c) 232 (( }}2(a),(c) 198 (( }}2(a),(c) 326 (( }}2(a),(c) 337 (( }}2(a),(c) 277 (( }}2(a),(c) 199 (( }}2(a),(c) (( : }}2(a),(c) (( }}2(a),(c) (( }}2(a),(c) © Copyright 2018 by NuScale Power, LLC 170

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-23 Pivot vs. fixed dry modal results for Columns 9 and 13 in y-direction (vertical) Column 9 Pivot, Y (vert) Column 13 Pivot, Y (vert) Column 9 Fixed, Y (vert) Column 13 Fixed, Y (vert) MASS MASS MASS MASS FREQ. FREQ. FREQ. FREQ. MODE PARTIC. MODE PARTIC. MODE PARTIC. MODE PARTIC. (HZ) (HZ) (HZ) (HZ) RATIO, Y RATIO, Y RATIO, Y RATIO, Y 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c) 3 (( }}2(a),(c) 3 (( }}2(a),(c) 9 (( }}2(a),(c) 16 (( }}2(a),(c) 4 (( }}2(a),(c) 4 (( }}2(a),(c) 20 (( }}2(a),(c) 17 (( }}2(a),(c) 7 (( }}2(a),(c) 7 (( }}2(a),(c) 21 (( }}2(a),(c) 22 (( }}2(a),(c) 8 (( }}2(a),(c) 8 (( }}2(a),(c) 24 (( }}2(a),(c) 23 (( }}2(a),(c) 11 (( }}2(a),(c) 11 (( }}2(a),(c) 25 (( }}2(a),(c) 29 (( }}2(a),(c) 12 (( }}2(a),(c) 12 (( }}2(a),(c) 26 (( }}2(a),(c) 53 (( }}2(a),(c) 31 (( }}2(a),(c) 27 (( }}2(a),(c) 31 (( }}2(a),(c) 119 (( }}2(a),(c) 32 (( }}2(a),(c) 29 (( }}2(a),(c) 60 (( }}2(a),(c) 120 (( }}2(a),(c) 33 (( }}2(a),(c) 31 (( }}2(a),(c) 137 (( }}2(a),(c) 206 (( }}2(a),(c) 35 (( }}2(a),(c) 110 (( }}2(a),(c) 138 (( }}2(a),(c) 207 (( }}2(a),(c) 129 (( }}2(a),(c) 112 (( }}2(a),(c) 139 (( }}2(a),(c) 211 (( }}2(a),(c) 130 (( }}2(a),(c) 136 (( }}2(a),(c) 140 (( }}2(a),(c) 212 (( }}2(a),(c) 134 (( }}2(a),(c) 137 (( }}2(a),(c) 241 (( }}2(a),(c) 213 (( }}2(a),(c) 157 (( }}2(a),(c) 140 (( }}2(a),(c) 242 (( }}2(a),(c) 214 (( }}2(a),(c) 158 (( }}2(a),(c) 141 (( }}2(a),(c) 245 (( }}2(a),(c) 215 (( }}2(a),(c) 161 (( }}2(a),(c) 148 (( }}2(a),(c) 246 (( }}2(a),(c) 334 (( }}2(a),(c) 162 (( }}2(a),(c) 161 (( }}2(a),(c) 389 (( }}2(a),(c) 335 (( }}2(a),(c) 343 (( }}2(a),(c) 300 (( }}2(a),(c) 390 (( }}2(a),(c) 336 (( }}2(a),(c) 344 (( }}2(a),(c) 342 (( }}2(a),(c) (( }}2(a),(c) © Copyright 2018 by NuScale Power, LLC 171

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-24 Pivot vs. fixed dry modal results for Columns 9 and 13 in z-direction (horizontal) Column 9 Pivot, Z (horiz) Column 13 Pivot, Z (horiz) Column 9 Fixed, Z (horiz) Column 13 Fixed, Z (horiz) MASS MASS MASS FREQ. FREQ. FREQ. FREQ. MASS PARTIC. MODE PARTIC. MODE PARTIC. MODE PARTIC. MODE (HZ) (HZ) (HZ) (HZ) RATIO, Z RATIO, Z RATIO, Z RATIO, Z 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 1 (( }}2(a),(c) 10 (( }}2(a),(c) 12 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c) 14 (( }}2(a),(c) 13 (( }}2(a),(c) 15 (( }}2(a),(c) 13 (( }}2(a),(c) 15 (( }}2(a),(c) 14 (( }}2(a),(c) 16 (( }}2(a),(c) 14 (( }}2(a),(c) 16 (( }}2(a),(c) 15 (( }}2(a),(c) 31 (( }}2(a),(c) 38 (( }}2(a),(c) 17 (( }}2(a),(c) 18 (( }}2(a),(c) 48 (( }}2(a),(c) 42 (( }}2(a),(c) 18 (( }}2(a),(c) 126 (( }}2(a),(c) 49 (( }}2(a),(c) 43 (( }}2(a),(c) 30 (( }}2(a),(c) 128 (( }}2(a),(c) 94 (( }}2(a),(c) 80 (( }}2(a),(c) 146 (( }}2(a),(c) 129 (( }}2(a),(c) 95 (( }}2(a),(c) 227 (( }}2(a),(c) 148 (( }}2(a),(c) 131 (( }}2(a),(c) 206 (( }}2(a),(c) 228 (( }}2(a),(c) 149 (( }}2(a),(c) 139 (( }}2(a),(c) 207 (( }}2(a),(c) 231 (( }}2(a),(c) 213 (( }}2(a),(c) 184 (( }}2(a),(c) 234 (( }}2(a),(c) 238 (( }}2(a),(c) 214 (( }}2(a),(c) 186 (( }}2(a),(c) 235 (( }}2(a),(c) 267 (( }}2(a),(c) 215 (( }}2(a),(c) 187 (( }}2(a),(c) 263 (( }}2(a),(c) 271 (( }}2(a),(c) 217 (( }}2(a),(c) 188 (( }}2(a),(c) 264 (( }}2(a),(c) 277 (( }}2(a),(c) 218 (( }}2(a),(c) 191 (( }}2(a),(c) 267 (( }}2(a),(c) 278 (( }}2(a),(c) 221 (( }}2(a),(c) 200 (( }}2(a),(c) 268 (( }}2(a),(c) 320 (( }}2(a),(c) 222 (( }}2(a),(c) 201 (( }}2(a),(c) 277 (( }}2(a),(c) 326 (( }}2(a),(c) 230 (( }}2(a),(c) 208 (( }}2(a),(c) 278 (( }}2(a),(c) 330 (( }}2(a),(c) 233 (( }}2(a),(c) 235 (( }}2(a),(c) 323 (( }}2(a),(c) 333 (( }}2(a),(c) 234 (( }}2(a),(c) 236 (( }}2(a),(c) 324 (( }}2(a),(c) (( }}2(a),(c) (( }}2(a),(c) © Copyright 2018 by NuScale Power, LLC 172

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                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.2.5 Dry-Wet Sensitivity Analysis Modal analysis was performed for the tube models in the wet configuration, meaning added mass was included to account for the displaced water on the primary side of the test specimen. No fluid is modeled inside the tubes. The added mass was included by increasing the density of the tube material. The added mass contributes to a (( }}2(a),(c) reduction in modal frequencies. Because the added mass is a linear change, the (( }}2(a),(c) shift applies equally to any frequency of any configuration. The results for the y-direction of Column 13 are presented in Table 5-25 and Table 5-26. Table 5-25 Dry vs. wet modal results for pivot boundary conditions in y-direction Dry - Col 13 Pivot, Y (vert) Wet - Col 13 Pivot, Y (vert) MASS FREQ. MASS PARTIC. % CHANGE MODE MODE FREQ. (HZ) PARTIC. (HZ) RATIO, Y FREQ. RATIO, Y 1 (( }}2(a),(c) 1 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c) 16 (( }}2(a),(c) 16 (( }}2(a),(c) 17 (( }}2(a),(c) 17 (( }}2(a),(c) 22 (( }}2(a),(c) 22 (( }}2(a),(c) 23 (( }}2(a),(c) 23 (( }}2(a),(c) 29 (( }}2(a),(c) 29 (( }}2(a),(c) 53 (( }}2(a),(c) 53 (( }}2(a),(c) 119 (( }}2(a),(c) 119 (( }}2(a),(c) 120 (( }}2(a),(c) 120 (( }}2(a),(c) 206 (( }}2(a),(c) 206 (( }}2(a),(c) 207 (( }}2(a),(c) 207 (( }}2(a),(c) 211 (( }}2(a),(c) 211 (( }}2(a),(c) 212 (( }}2(a),(c) 212 (( }}2(a),(c) 213 (( }}2(a),(c) 213 (( }}2(a),(c) 214 (( }}2(a),(c) 214 (( }}2(a),(c) 215 (( }}2(a),(c) 215 (( }}2(a),(c) 334 (( }}2(a),(c) 334 (( }}2(a),(c) 335 (( }}2(a),(c) 335 (( }}2(a),(c) 336 (( }}2(a),(c) 336 (( }}2(a),(c) (( }}2(a),(c) © Copyright 2018 by NuScale Power, LLC 177

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-26 Dry vs. wet modal results for fixed boundary conditions in y-direction Dry - Col 13 Fixed, Y (vert) Wet - Col 13 Fixed, Y (vert) MASS FREQ. MASS PARTIC. % CHANGE MODE MODE FREQ. (HZ) PARTIC. (HZ) RATIO, Y FREQ. RATIO, Y 1 (( }}2(a),(c) 1 (( }}2(a),(c) 3 (( }}2(a),(c) 3 (( }}2(a),(c) 4 (( }}2(a),(c) 4 (( }}2(a),(c) 7 (( }}2(a),(c) 7 (( }}2(a),(c) 8 (( }}2(a),(c) 8 (( }}2(a),(c) 11 (( }}2(a),(c) 11 (( }}2(a),(c) 12 (( }}2(a),(c) 12 (( }}2(a),(c) 27 (( }}2(a),(c) 27 (( }}2(a),(c) 29 (( }}2(a),(c) 29 (( }}2(a),(c) 31 (( }}2(a),(c) 31 (( }}2(a),(c) 110 (( }}2(a),(c) 110 (( }}2(a),(c) 112 (( }}2(a),(c) 112 (( }}2(a),(c) 136 (( }}2(a),(c) 136 (( }}2(a),(c) 137 (( }}2(a),(c) 137 (( }}2(a),(c) 140 (( }}2(a),(c) 140 (( }}2(a),(c) 141 (( }}2(a),(c) 141 (( }}2(a),(c) 148 (( }}2(a),(c) 148 (( }}2(a),(c) 161 (( }}2(a),(c) 161 (( }}2(a),(c) 300 (( }}2(a),(c) 300 (( }}2(a),(c) 342 (( }}2(a),(c) 342 (( }}2(a),(c) (( }}2(a),(c) 5.1.2.6 Mesh Sensitivity Analysis Modal analysis was performed with the Column 13 individual tube dry model to determine the effect of element type and size on modal results. The fine mesh uses 1-inch BEAM 188 elements, and the coarse mesh uses 12-inch BEAM189 elements. The purpose of this sensitivity analysis is to ensure the coarse mesh properly characterizes the modal response of the tubes, as this coarse mesh is used in the TF-3 full bundle model to reduce computation time. The mesh sensitivity results for the top 20 participating modes are presented in Table 5-27 through Table 5-29 for the pivot boundary conditions, and in Table 5-30 through Table 5-32 for the fixed boundary conditions. For the fixed condition, only modes under 400 Hz are shown. Results are shown in the global Cartesian coordinate system (CSYS, 0). Agreement is shown between the two mesh sizes, validating the use of the coarse mesh in the full bundle model. For modes below 200 Hz, the frequency shift is less than ((

                    }}2(a),(c). The frequency shift increases with higher frequencies, but stays under

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 complexity of the mode shapes at higher frequencies, which become harder to represent with the coarse mesh that cannot fully resolve the complex shape. The difference is acceptable for the frequencies of interest. Some modes show large changes in mass participation between the fine and coarse meshes, but this is typically a case of mass participation shifting from one mode to an adjacent closely spaced mode of a similar mode shape. When looking at comparable sets of modes between the fine and coarse meshes, the sums of the mass participations are similar between the two meshes, validating this explanation. See the mass participation sums at the end of each table. Additionally, the modes with large percent changes between mesh sizes tend to be the modes with low mass participation, so the magnitude of the mass participation change is small. © Copyright 2018 by NuScale Power, LLC 179

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-27 Fine vs. coarse mesh modal results for pivot boundary conditions in x-direction Fine Mesh - Col 13 Pivot, X (horiz) Coarse Mesh - Col 13 Pivot, X (horiz) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, X (HZ) FREQ. RATIO, X 7 (( }}2(a),(c) 7 (( }}2(a),(c) 11 (( }}2(a),(c) 11 (( }}2(a),(c) 12 (( }}2(a),(c) 12 (( }}2(a),(c) 13 (( }}2(a),(c) 13 (( }}2(a),(c) 14 (( }}2(a),(c) 14 (( }}2(a),(c) 15 (( }}2(a),(c) 15 (( }}2(a),(c) 18 (( }}2(a),(c) 18 (( }}2(a),(c) 19 (( }}2(a),(c) 19 (( }}2(a),(c) 21 (( }}2(a),(c) 21 (( }}2(a),(c) 43 (( }}2(a),(c) - (( }}2(a),(c) 52 (( }}2(a),(c) 52 (( }}2(a),(c) 122 (( }}2(a),(c) 122 (( }}2(a),(c) 124 (( }}2(a),(c) 124 (( }}2(a),(c) 127 (( }}2(a),(c) 127 (( }}2(a),(c) 130 (( }}2(a),(c) 130 (( }}2(a),(c) 185 (( }}2(a),(c) 185 (( }}2(a),(c) 186 (( }}2(a),(c) 186 (( }}2(a),(c)

     -            ((               }}2(a),(c)      187        ((                                   }}2(a),(c)
     -            ((               }}2(a),(c)      188        ((                                   }}2(a),(c) 189        ((                      }}2(a),(c)     -            ((                               }}2(a),(c) 198        ((                      }}2(a),(c)   198        ((                                       }}2(a),(c) 199        ((                      }}2(a),(c)   199        ((                                       }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-28 Fine vs. coarse mesh modal results for pivot boundary conditions in y-direction Fine Mesh - Col 13 Pivot, Y (vert) Coarse Mesh - Col 13 Pivot, Y (vert) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, Y (HZ) FREQ. RATIO, Y 1 (( }}2(a),(c) 1 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c)

    -             ((               }}2(a),(c)       13         ((                                   }}2(a),(c) 16          ((                     }}2(a),(c)    16         ((                                       }}2(a),(c) 17          ((                     }}2(a),(c)    17         ((                                       }}2(a),(c) 22          ((                     }}2(a),(c)    22         ((                                       }}2(a),(c) 23          ((                     }}2(a),(c)    23         ((                                       }}2(a),(c)
    -             ((               }}2(a),(c)       28         ((                                   }}2(a),(c) 29          ((                     }}2(a),(c)    29         ((                                       }}2(a),(c) 53          ((                     }}2(a),(c)    53         ((                                       }}2(a),(c) 119        ((                      }}2(a),(c)   119        ((                                        }}2(a),(c) 120        ((                      }}2(a),(c)   120        ((                                        }}2(a),(c) 206        ((                      }}2(a),(c)   206        ((                                        }}2(a),(c) 207        ((                      }}2(a),(c)   207        ((                                        }}2(a),(c)
    -             ((               }}2(a),(c)      210        ((                                    }}2(a),(c) 211        ((                      }}2(a),(c)   211        ((                                        }}2(a),(c) 212        ((                      }}2(a),(c)     -            ((                                }}2(a),(c) 213        ((                      }}2(a),(c)   213        ((                                        }}2(a),(c) 214        ((                      }}2(a),(c)     -            ((                                }}2(a),(c) 215        ((                      }}2(a),(c)   215        ((                                        }}2(a),(c) 334        ((                      }}2(a),(c)     -            ((                                }}2(a),(c) 335        ((                      }}2(a),(c)     -            ((                                }}2(a),(c) 336        ((                      }}2(a),(c)     -            ((                                }}2(a),(c)
    -             ((               }}2(a),(c)      337        ((                                    }}2(a),(c)
    -             ((               }}2(a),(c)      338        ((                                    }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-29 Fine vs. coarse mesh modal results for pivot boundary conditions in z-direction Fine Mesh - Col 13 Pivot, Z (horiz) Coarse Mesh - Col 13 Pivot, Z (horiz) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, Z (HZ) FREQ. RATIO, Z 12 (( }}2(a),(c) 12 (( }}2(a),(c) 13 (( }}2(a),(c) 13 (( }}2(a),(c) 14 (( }}2(a),(c) 14 (( }}2(a),(c) 15 (( }}2(a),(c) 15 (( }}2(a),(c) 18 (( }}2(a),(c) 18 (( }}2(a),(c) 126 (( }}2(a),(c) 126 (( }}2(a),(c) 128 (( }}2(a),(c) 128 (( }}2(a),(c) 129 (( }}2(a),(c) 129 (( }}2(a),(c) 131 (( }}2(a),(c) 131 (( }}2(a),(c) 139 (( }}2(a),(c) 139 (( }}2(a),(c) 184 (( }}2(a),(c) 184 (( }}2(a),(c)

    -             ((               }}2(a),(c)      185         ((                                  }}2(a),(c) 186        ((                      }}2(a),(c)   186         ((                                      }}2(a),(c) 187        ((                      }}2(a),(c)   187         ((                                      }}2(a),(c) 188        ((                      }}2(a),(c)   188         ((                                      }}2(a),(c) 191        ((                      }}2(a),(c)   191         ((                                      }}2(a),(c) 200        ((                      }}2(a),(c)   200         ((                                      }}2(a),(c) 201        ((                      }}2(a),(c)   201         ((                                      }}2(a),(c) 208        ((                      }}2(a),(c)     -             ((                              }}2(a),(c) 235        ((                      }}2(a),(c)     -             ((                              }}2(a),(c) 236        ((                      }}2(a),(c)     -             ((                              }}2(a),(c)
    -             ((               }}2(a),(c)      237         ((                                  }}2(a),(c)
    -             ((               }}2(a),(c)      238         ((                                  }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-30 Fine vs. coarse mesh modal results for fixed boundary conditions in x-direction Fine Mesh - Col 13 Fixed, X (horiz) Coarse Mesh - Col 13 Fixed, X (horiz) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, X (HZ) FREQ. RATIO, X 1 (( }}2(a),(c) 1 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c) 15 (( }}2(a),(c) 15 (( }}2(a),(c) 16 (( }}2(a),(c) 16 (( }}2(a),(c) 28 (( }}2(a),(c) 28 (( }}2(a),(c) 29 (( }}2(a),(c) 29 (( }}2(a),(c) 30 (( }}2(a),(c) 30 (( }}2(a),(c) 32 (( }}2(a),(c) 32 (( }}2(a),(c)

     -           ((               }}2(a),(c)       33         ((                                   }}2(a),(c) 41       ((                      }}2(a),(c)    41         ((                                       }}2(a),(c) 44       ((                      }}2(a),(c)    44         ((                                       }}2(a),(c) 47       ((                      }}2(a),(c)    47         ((                                       }}2(a),(c)
     -           ((               }}2(a),(c)       48         ((                                   }}2(a),(c) 49       ((                      }}2(a),(c)    49         ((                                       }}2(a),(c) 52       ((                      }}2(a),(c)    52         ((                                       }}2(a),(c) 53       ((                      }}2(a),(c)     -             ((                               }}2(a),(c)
     -           ((               }}2(a),(c)       54         ((                                   }}2(a),(c) 80       ((                      }}2(a),(c)    80         ((                                       }}2(a),(c) 122       ((                      }}2(a),(c)    122        ((                                       }}2(a),(c) 123       ((                      }}2(a),(c)     -             ((                               }}2(a),(c) 134       ((                      }}2(a),(c)    134        ((                                        }}2(a),(c) 148       ((                      }}2(a),(c)     -             ((                               }}2(a),(c) 149       ((                      }}2(a),(c)     -             ((                               }}2(a),(c)
     -           ((               }}2(a),(c)       150        ((                                   }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-31 Fine vs. coarse mesh modal results for fixed boundary conditions in y-direction Fine Mesh - Col 13 Fixed, Y (vert) Coarse Mesh - Col 13 Fixed, Y (vert) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, Y (HZ) FREQ. RATIO, Y 1 (( }}2(a),(c) 1 (( }}2(a),(c) 3 (( }}2(a),(c) 3 (( }}2(a),(c) 4 (( }}2(a),(c) 4 (( }}2(a),(c) 7 (( }}2(a),(c) 7 (( }}2(a),(c) 8 (( }}2(a),(c) 8 (( }}2(a),(c) 11 (( }}2(a),(c) 11 (( }}2(a),(c) 12 (( }}2(a),(c) 12 (( }}2(a),(c) 27 (( }}2(a),(c) 27 (( }}2(a),(c) 29 (( }}2(a),(c) 29 (( }}2(a),(c) 31 (( }}2(a),(c) 31 (( }}2(a),(c) 110 (( }}2(a),(c) 110 (( }}2(a),(c) 112 (( }}2(a),(c) - (( }}2(a),(c)

     -           ((               }}2(a),(c)       113        ((                                   }}2(a),(c) 115       ((                      }}2(a),(c)      -            ((                               }}2(a),(c)
     -           ((               }}2(a),(c)       135        ((                                   }}2(a),(c) 136       ((                      }}2(a),(c)      -            ((                               }}2(a),(c) 137       ((                      }}2(a),(c)      -            ((                               }}2(a),(c)
     -           ((               }}2(a),(c)       138        ((                                   }}2(a),(c) 140       ((                      }}2(a),(c)    140        ((                                       }}2(a),(c)
     -           ((               }}2(a),(c)       143        ((                                   }}2(a),(c) 141       ((                      }}2(a),(c)      -            ((                               }}2(a),(c) 144       ((                      }}2(a),(c)    144        ((                                       }}2(a),(c)
     -           ((               }}2(a),(c)       147        ((                                   }}2(a),(c) 148       ((                      }}2(a),(c)      -            ((                               }}2(a),(c)
     -           ((               }}2(a),(c)       156        ((                                   }}2(a),(c)
     -           ((               }}2(a),(c)       160        ((                                   }}2(a),(c) 161       ((                      }}2(a),(c)      -            ((                               }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-32 Fine vs. coarse mesh modal results for fixed boundary conditions in z-direction Fine Mesh - Col 13 Fixed, Z (horiz) Coarse Mesh - Col 13 Fixed, Z (horiz) MASS FREQ. MASS PARTIC. FREQ. % CHANGE MODE MODE PARTIC. (HZ) RATIO, Z (HZ) FREQ. RATIO, Z 1 (( }}2(a),(c) 1 (( }}2(a),(c) 2 (( }}2(a),(c) 2 (( }}2(a),(c) 13 (( }}2(a),(c) 13 (( }}2(a),(c) 14 (( }}2(a),(c) 14 (( }}2(a),(c) 27 (( }}2(a),(c) 27 (( }}2(a),(c) 28 (( }}2(a),(c) 28 (( }}2(a),(c) 29 (( }}2(a),(c) - (( }}2(a),(c) 38 (( }}2(a),(c) 38 (( }}2(a),(c)

     -            ((              }}2(a),(c)       40         ((                                   }}2(a),(c)
     -            ((              }}2(a),(c)       41         ((                                   }}2(a),(c) 42       ((                      }}2(a),(c)    42         ((                                       }}2(a),(c) 43       ((                      }}2(a),(c)    43         ((                                       }}2(a),(c) 45       ((                      }}2(a),(c)     -             ((                               }}2(a),(c)
     -            ((              }}2(a),(c)       53         ((                                   }}2(a),(c) 54       ((                      }}2(a),(c)     -             ((                               }}2(a),(c) 55       ((                      }}2(a),(c)    55         ((                                       }}2(a),(c) 80       ((                      }}2(a),(c)    80         ((                                       }}2(a),(c) 84       ((                      }}2(a),(c)    84         ((                                       }}2(a),(c) 109       ((                      }}2(a),(c)    109        ((                                        }}2(a),(c) 121       ((                      }}2(a),(c)    121        ((                                       }}2(a),(c) 135       ((                      }}2(a),(c)     -             ((                               }}2(a),(c) 146       ((                      }}2(a),(c)    146        ((                                       }}2(a),(c) 147       ((                      }}2(a),(c)     -             ((                               }}2(a),(c)
     -            ((              }}2(a),(c)       149        ((                                   }}2(a),(c)
     -            ((              }}2(a),(c)       161        ((                                   }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.2.7 Strain Gauge Placement Recommendations Modal analysis was performed on the two bounding tubes of the Column 11 individual tube model for the pivot and fixed boundary conditions. Strain gauge placement recommendations are provided for the top five mass participating modes in the vertical y-direction. These maximum strain locations are determined using the EPELINT (elastic strain intensity) user defined result in ANSYS Workbench Mechanical. Analysis was performed for the tubes in the dry condition. Table 5-33 provides the top five mass participating modes in the y-directions for each of the two tubes for each of the boundary conditions. The strain gauge placement recommendations are shown in Figure 5-20 through Figure 5-23. The maximum strain for each mode occurs at the mid-span between boundary conditions, or at the boundary condition. Table 5-33 Top 5 participating modes in y-direction for Column 11 tubes Col 11 Tube 1 Pivot Col 11 Tube 1 Fixed MASS PARTIC. MASS PARTIC. MODE FREQ. (HZ) MODE FREQ. (HZ) RATIO, Y RATIO, Y 1 (( }}2(a),(c) 2 (( }}2(a),(c) 10 (( }}2(a),(c) 4 (( }}2(a),(c) 12 (( }}2(a),(c) 16 (( }}2(a),(c) 68 (( }}2(a),(c) 65 (( }}2(a),(c) 123 (( }}2(a),(c) 79 (( }}2(a),(c) Col 11 Tube 16 Pivot Col 11 Tube 16 Fixed MASS PARTIC. MASS PARTIC. MODE FREQ. (HZ) MODE FREQ. (HZ) RATIO, Y RATIO, Y 1 (( }}2(a),(c) 2 (( }}2(a),(c) 10 (( }}2(a),(c) 4 (( }}2(a),(c) 69 (( }}2(a),(c) 16 (( }}2(a),(c) 122 (( }}2(a),(c) 63 (( }}2(a),(c) 194 (( }}2(a),(c) 79 (( }}2(a),(c) © Copyright 2018 by NuScale Power, LLC 186

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                       }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.2.8 Modal Analysis - TF-3 Full Bundle Model Modal analysis is performed for the TF-3 full bundle model. The purpose of the full bundle analysis is to determine the full bundle modes, and also determine if the tube modes within the full bundle match those of the individual tube models. If the tube modes are similar, it validates the assumption of rigid supports in the individual tube models. The full bundle model is run in both the pivot and fixed conditions for the tube-to-tube support connections. These are the same boundary condition cases used in the individual tube models. An additional case is run with the fixed condition where the circumferential coupling between the tube supports and the inner and outer vessels is removed. This is done to determine a possible twisting mode of the tube bundle in case the circumferential restraints were removed. This third case is called fixed, no circ. The full bundle analyses are run from 0 Hz to 55 Hz for the pivot case, and 0 Hz, to 80 Hz for the fixed case. These upper bounds were selected to capture the modes with highest vertical mass participation as seen in the individual tube models. The fixed, no circ case is run for the first 1,000 modes, which terminated at (( }}2(a),(c). This was done to capture the twisting mode, but not repeat all other modes that are similar to the normal fixed case. The modes of interest that are discussed in the in the following sections are summarized in Table 5-34. © Copyright 2018 by NuScale Power, LLC 191

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-34 Summary of full bundle model results Boundary Condition Mode Freq. (Hz) Mode Type Notes Case Similar frequency as breathing mode in column (( }}2(a),(c) tube breathing 13 individual tube model ((( }}2(a),(c) Hz) full specimen Full specimen rocking mode. Not seen in (( }}2(a),(c) rocking individual tube models tube beam Highest y-mass participation. Matches Pivot (( }}2(a),(c) (long span between frequencies for high y-mass participation modes supports) in individual tube models (see below) Top 38 y-mass participating modes. Matches tube beam (( frequencies for highest y-mass participating (long span between

                          }}2(a),(c)                           modes in individual tube models (((

supports)

                                                                                 }}2(a),(c) Hz) full specimen          Full specimen rocking mode, similar to pivot

(( }}2(a),(c) rocking case. Not seen in individual tube models Full specimen squeezing mode. Likely exists in full specimen pivot case, but difficult to discern due to (( }}2(a),(c) squeezing overlapping tube modes. Not seen in individual tube models Fixed Beam mode of tube transition bend. Similar to tube beam (( }}2(a),(c) transition bend beam mode of Column 13 (transition bend) individual tube model ((( }}2(a),(c) Hz) Highest y-mass participation. Matches tube beam frequency for highest y-mass participation mode (( }}2(a),(c) (long span between in Column 13 individual tube model supports) ((( }}2(a),(c) Hz) Twisting of the tube and tube support bundle relative to the vessels. Low mass participation Fixed, tube bundle No Circ (( }}2(a),(c) twisting (outside of top 240 participating modes in any direction). Not seen in individual tube models. Other modes similar to fixed case The following sections contain several figures of mode shapes. In some figures, the cross-section shapes are shown, and some figures they are not. The option that showed the mode shape best was chosen. © Copyright 2018 by NuScale Power, LLC 192

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The fundamental mode of the full bundle pivot case is at (( }}2(a),(c). This is about 5 percent lower than the fundamental mode of the Column 13 individual tube model of (( }}2(a),(c). Both modes correspond to breathing of the tubes. This tube breathing mode shape is shown in Figure 5-24. ((

                                                                                                            }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The mode with highest x-direction mass participation is at (( }}2(a),(c). This mode is the entire specimen rocking back and forth, and thus there is no corresponding mode in the individual tube models. This mode shape is shown in Figure 5-25. ((

                                                                                                           }}2(a),(c)

Figure 5-25 Mode with highest x-direction mass participation for full bundle pivot case (rocking mode) The mode with highest y-direction mass participation is at (( }}2(a),(c). This is a tube beam mode and is shown in Figure 5-26. The vessels do not respond to this mode. © Copyright 2018 by NuScale Power, LLC 194

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The top 38 y-participating modes are between (( }}2(a),(c). These are similar frequencies as seen in the individual tube models, which have dominant y-direction modes of (( }}2(a),(c) for Column 13 and Column 9, respectively. ((

                                                                                                            }}2(a),(c)

Figure 5-26 Mode with highest y-direction mass participation for full bundle pivot case (tube beam mode) The fundamental mode of the full bundle fixed model is an (( }}2(a),(c) rocking mode, similar to the one shown in Figure 5-25 for the pivot case. An additional entire specimen mode becomes apparent in the fixed case, which is a squeezing mode at (( }}2(a),(c). It is less apparent in the pivot case because it © Copyright 2018 by NuScale Power, LLC 195

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 overlaps the lower frequency tube modes of that case. This mode shape is shown in Figure 5-27. Despite this being a full specimen mode, it has relatively low mass participation, with similar participation values to the closely spaced tube modes. ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The tube fundamental mode within the full bundle model is at (( }}2(a),(c) and is a beam mode of the tube transition bend region. This is a similar mode shape as the individual tube model shown in Figure 5-18, which also has a similar frequency of (( }}2(a),(c). The full bundle mode is shown in Figure 5-28. ((

                                                                                                               }}2(a),(c)

Figure 5-28 Tube fundamental mode for full bundle fixed case (beam mode of transition bend) The overall mode with highest y-direction mass participation is at (( }}2(a),(c). It makes up (( }}2(a),(c) of the vertical mass, indicating it is a vessel axial mode. It © Copyright 2018 by NuScale Power, LLC 197

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 is difficult to visualize the axial motion of the specimen because the axial displacement is very small compared to the tube displacements that also occur in this mode. The mode with highest y-direction mass participation that is dominated by tube movement is at (( }}2(a),(c). This mode exhibits beam mode behavior for the long spans of many tubes, similar to that shown in the Column 13 individual tube model in Figure 5-19. It is also similar in frequency to the individual tube model (( }}2(a),(c). This full bundle mode is shown in Figure 5-29. ((

                                                                                                           }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The fixed case model was repeated but the circumferential coupling between the tube supports and the inner and outer vessels was removed. This simulates a condition where the circumferential restraints welded to the inner and outer vessels are removed. This model was only analyzed for the first 1,000 modes. This case introduces a tube bundle twisting mode at (( }}2(a),(c). This mode shape is shown in Figure 5-30. Cross-section shapes are turned on to highlight the tube supports. The mode has low mass participation. It has the 798th highest x-mass participation, 248th highest y-mass participation, and 978th highest z-mass participation. ((

                                                                                                           }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.2.9 Conclusions This calculation provides modal analysis of the TF-3 test specimen through the use of individual tube models and the full bundle model. The modal analysis results show agreement between the full bundle model and the single tube models for modes involving the tubes (see Table 5-34). This validates the use of the rigid boundary conditions in the single tube models, because the inclusion of the explicitly modeled tube supports and vessels in the full bundle model did not significantly alter the tube modes. The full bundle analysis also provides the additional full bundle modes not captured in the individual tube models. The individual tube models provide frequencies and mass participations for the bounding tubes in the bounding columns (Columns 9 and 13). The effects of different boundary conditions, added mass, and mesh size are evaluated. Mode shapes for all modes below 300 Hz are written to text files for downstream analysis of Columns 9, 11, and 13. Maximum strain intensity locations are provided for the Column 11 dominant vertical modes, as a recommendation for strain gauge placement. © Copyright 2018 by NuScale Power, LLC 200

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.1.3 TF-3 FEI Pre-Test Prediction This information will be provided at the next scheduled revision of the technical report. 5.1.4 TF-3 VS Pre-Test Prediction This information will be provided at the next scheduled revision of the technical report. 5.1.5 TF-3 TB Pre-Test Prediction This information will be provided at the next scheduled revision of the technical report. © Copyright 2018 by NuScale Power, LLC 201

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.2 Decay Heat Removal System Steam Tee Validation Testing Initial startup testing is performed on the first NPM after the first fuel load. Due to the natural circulation design of the NPM, it is not possible to obtain the limiting thermal hydraulic conditions that are necessary to verify the FIV inputs and results until the NPM is operating near full power conditions. Initial startup testing is performed for a sufficient duration to ensure one million vibration cycles for the component with the lowest structural natural frequency. It takes less than 2.5 days of operation to obtain one million cycles of vibration. This is a conservative estimate because the lowest natural frequency of any component evaluated in the CVAP is (( }}2(a),(c) (outer column of the SG, conservatively assuming it is filled with subcooled liquid, which it will not be during full power conditions). The initial startup test is performed with online vibration monitoring of the DHRS steam piping. In the event that an unacceptable vibration response develops any time during initial startup testing, the test conditions are adjusted to stop the vibration and the reason for the vibration anomaly investigated before continuing with the planned testing. Vibration amplitudes in the DHRS steam lines are measured to confirm the acoustic resonance (AR) analysis results. 5.2.1 Decay Heat Removal System Test Design The DHRS steam piping was determined to be a component susceptible to acoustic excitation with a margin of less than 100 percent to the critical Strouhal number. The DHRS steam lines are branch lines where there is normally no flow during operation. This report develops an approach and testing requirements to perform in-situ measurements in the piping outside the containment vessel head. Flow-excited ARs, where instabilities in the fluid flow excite acoustic modes within valves, stand pipes, or branch lines can play a significant role in producing mid- to high-frequency pressure amplification and vibration. Flow separation and generation of unstable shear layers at closed branch lines can sometimes lead to AR. To determine if there is a concern for AR in the NuScale design, the piping locations where this source of flow excitation is possible were identified and the Strouhal number was calculated for each location. To determine the margin to AR, the calculated Strouhal number was compared to the empirically established range of critical Strouhal numbers (0.35 - 0.62) that could lead to the onset of AR. This analysis was applied to the DHRS steam piping, as described below, for full-power normal operating conditions when the secondary flow rate and steam velocity in the pipe is maximum. Full-power normal operating conditions produce the Strouhal numbers closest to the upper range value of 0.62. At lower reactor power levels, velocities are reduced. This results in Strouhal numbers that are higher and therefore further from the critical range. Figure 5-31 shows the containment system (CNTS) MS line 2 from the CNTS main steam tees to the disconnect flange downstream of the main steam isolation valve (MSIV) and a portion of the DHRS steam lines up to the first bend after the DHRS actuation valves. It is this junction where the secondary flow is moving vertically upward and encountering the discontinuity of horizontal branch openings to the closed DHRS actuation valves that are susceptible to acoustic excitation. The CNTS main steam line 1 is not shown. It has a very © Copyright 2018 by NuScale Power, LLC 202

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 similar layout, but with different circumferential orientations of the tees around the steam piping. Each of the four side branches and two MS lines need instrumentation to measure flow parameters and pipe vibration during the initial start-up testing. Acoustic resonance is considered a strongly coupled FIV mechanism that results in large vibration amplitudes. The design analysis approach is to preclude the onset of this mechanism. The main objective of the test is to verify that AR is not active or causing detrimental vibration in the CNTS main steam lines, decay heat removal steam lines, and connected valves during tests that represent the full range of operating conditions. This includes testing for the detection of any acoustic excitation by a higher order shear layer mode during partial power operation. Another objective of the test is to validate the calculated AR safety margin. The test quantifies the measurement uncertainties of analysis input parameters such as the speed of sound in the fluid and the steam velocity in the CNTS main steam piping. The as-built component measurements are used to validate uncertainties on other analysis inputs, such as the DHRS side branch entrance diameter and side branch length. Unlike monitoring mechanical vibration of a particular component, ARs are also detectable by monitoring the magnitude and frequencies of dynamic pressure pulsations in the fluid, which help identify the presence and excitation of a standing wave in a flow occluded region. Such measurements serve as additional evidence beyond the vibration data that are collected on the exterior of the pressure boundary. © Copyright 2018 by NuScale Power, LLC 203

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Figure 5-31 Containment system steam line 2 and decay heat removal system actuation valves 5.2.1.1 Vibration Testing Guidelines The ASME Standard for Operation and Maintenance (OM) of Nuclear Power Plants (Reference 9.1.1) Part 3: Vibration Testing of Piping Systems, provides test methods and acceptance criteria for assessing the severity of piping vibration. Steady-state and transient vibration testing are addressed along with applicable instrumentation and measurement techniques, recommendations for corrective action, and discussions of potential vibration sources. The test specification developed for the AR initial startup testing shall comply with the ASME Operations and Maintenance code requirements as follows:

Reference 9.1.1 under General Requirements, stipulates that a test specification be prepared to ensure that the objectives of the tests are satisfied and that results obtained are accurate or conservative.
The test specification shall include the minimum list of items in Reference 9.1.1 Section

3. Namely, (a) test objectives, (b) systems to be tested (including boundaries), (c) pretest requirements or conditions, (d) governing documents and drawings, (e) precautions, (f) quality control and assurance, (g) acceptance criteria, (h) test conditions and hold points, (i) measurements to be made and acceptable limits

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 (including visual observations), (j) instrumentation to be used, (k) data handling and storage, and (l) system restoration.

Classification of the piping is in accordance with the requirements and guidance of Reference 9.1.1, Section 3.1.1 (steady-state vibration) because transient operations such as pump actuation or rapid valve motion are not relevant for acoustic resonance.

Due to operating experience and design analysis, the NuScale DHRS connection piping is classified as Vibration Monitoring Group 2.

The test specification shall include deflection measurement of the branch DHRS piping as described in Reference 9.1.1, Section 5.1.1.4.
The determination of an allowable deflection limit is to be developed based on the methodology defined in Reference 9.1.1, Section 5.1.1.5 and NuScale design inputs.

The measurement technique and deflection limits are specific to the validation of the NuScale DHRS steam pipe and AR phenomena.

Instrumentation and the Vibration Monitoring System specifications comply with the requirements discussed in Section 7 of Reference 9.1.1.

5.2.1.2 Instrumentation and Data Acquisition Requirements A general description of the minimum measurements and sensors proposed to perform the testing is provided in Table 5-35. Sensor specifications, signal conditioning equipment, data conversion and storage procedures, and calibration procedures are to be accepted by NuScale. © Copyright 2018 by NuScale Power, LLC 205

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-35 Measurements and sensors Minimum Measurement Number of Description Sensors The accelerometers are mounted on the two MSIVs, two MS Vibration amplitude 12 piping lines, four DHRS actuation valves and four DHRS branch piping legs in order to record their vibration response. The high frequency(b) dynamic pressure sensors probe the four branch lines to the DHRS actuation valves, and measure Dynamic pressure 6 pressure fluctuations in the branch lines, and MS lines. Strain gauges may be substituted if dynamic pressure sensors cannot be accommodated(c). These sensors are used to determine the superheated steam Temperature 2 temperature inside the pipes. The main steam system (MSS) has these as part of its control and monitoring function. The mass flow rate sensor in the MSS is used, along with pressure and temperature sensors in the MS line, to calculate the free stream flow velocity in the MS pipes at the DHRS branch lines. The uncertainties involved in this calculation are Flow rate 2(a) considered in the pre-test prediction. A velocity reading at the DHRS branch line location is not required because the analysis margin calculation is based on a free stream velocity upstream of the leading edge of the cavity. (a) Quantity indicates a final datum of average velocity in each MS line. The velocity is calculated from the mass flow rate measurement in the downstream MSS line (b) The frequency should be greater than the reciprocal of transit time for a fluid particle across the branch cavity, and the transit time of a sound wave traversing the length of the cavity and back to the MS pipe. (c) If strain gauges are used, they would be installed in the DHRS branch lines to transform strain oscillation readings into pressure amplitudes. Two sets of four symmetrically circumferential strain gauges placed at two axial locations in each branch pipe cancel out the shell modes of vibration such that the frequency range is well below the breathing shell mode of the pipe. Any deformation of the pipe as measured by strain gauges is caused by an acoustic pressure wave inside the pipe. The axial distance between the two measuring locations will be less than half the wavelength of the upper limit frequency. Acceleration, velocity, and displacement are measured with the use of accelerometers. The accelerometer also provides the frequency signature of a vibration such that the vibration response can be correlated to a vibration source, i.e., from turbulence or from AR. Velocity and displacement readings are obtained through single and double integration, respectively. The advantage of accelerometers is they measure absolute acceleration and do not need to be referenced to a structure position. Each of the MSIVs and DHRS actuation valves are to be monitored with accelerometers mounted to the valve body to ensure that vibration amplitudes are acceptable. If AR is taking place in the DHRS cavity piping, high oscillating pressures develop and propagate through the entire piping system causing a vibration response in other nearby components. Also, if the instabilities in the stub piping resonate with the structural natural frequencies of the MS piping and MSIVs, dynamic loads cause high cycle fatigue. Thus, it is important to also instrument nearby components such as the MSIVs. The MS lines are not fully symmetric and a slight disparity in steam velocity between each line results from minor differences in flow resistance through the FW and MS piping. © Copyright 2018 by NuScale Power, LLC 206

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Although unlikely, with one MS line at a slightly higher velocity, resonance could occur in one MS line and not the other. Also, if resonance in the DHRS stub piping were to propagate into the MS piping, there may be small differences in vibration response due to geometry, support locations, and damping, thus accelerometers are placed on both MS lines for this testing. The branch piping exterior walls are also instrumented with accelerometers to ensure deflection is below the limits for the piping, as calculated using ASME OM Part 3 Section 5.1.1.5 (Reference 9.1.1). The amplitude measured on the branch pipe is expected to be larger than the process piping. As discussed in Section H-3.1.3 of Reference 9.1.1, measurement of true peak-to-peak displacement is preferred over RMS displacement because the displacement is proportional to the pipe mode shape and vibrational stress. RMS measurements cannot be readily converted to peak-to-peak measurements except for pure sinusoidal signals, so RMS displacements can only indicate averaged stress. The count of two MSIVs, two MS line piping legs, four DHRS actuation valves, and four DHRS branch piping legs requires 12 sensors, which is the minimum for accelerometers if tri-axial accelerometers are used. If biaxial accelerometers are used, then two offset by 90 degrees are needed at each location. Consideration of additional sensors for redundancy in case some fail is assessed in the test plan based on review of vendor data, instrument specifications, and ease of installation. Pressure data is best obtained through the use of dynamic pressure transducers directly in contact with the fluid, which requires tapping into the piping. This is feasible in the DHRS branches as indicated by the small-bore taps shown in Figure 5-31. These particular penetrations are used for sensors related to the nuclear steam supply system control, so additional ports are needed for the first prototype to accommodate using dynamic pressure transducers for this test. Each of the four closed-end legs has dynamic pressure measurement in order to detect the presence of a standing wave in the branch piping and allow for the investigation of resonance. Because the acoustic transmission of pressure waves propagates in the MS lines, the remaining pressure sensors are installed in the flow path of the MS piping in order to compare to the branch measurements, and determine the strength of the reflected pulsation if it is active. Alternatively, two sets of four strain gauges may be placed at two axial locations along a run of straight pipe to measure hoop strain in the pipe. This non-intrusive technique may be used to measure dynamic changes in pressure inside the pipe. At a given axial location, the four strain gauges will need to be placed around the circumference of the pipe every 90°. The axial distance between the measuring locations will be designed to avoid half-wavelengths of the acoustic pressure waves. The half-wavelength would be calculated as L = c/2f. The spacing therefore should be less than 19.5 inches in order to detect an excitation of a first or second order acoustic mode. Strain gauges will be sensitive to changes in hoop stress due to local pressure changes. A final method is selected in the test specification based on the accuracy and reliability of measurement (from field experience) with consideration of installation options. © Copyright 2018 by NuScale Power, LLC 207

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Thermocouples are needed to measure the fluid temperature exiting the steam generators and flowing through the MS lines. Measurement uncertainties are quantified and provided. The plant has permanent instrumentation in the MS line for this purpose located upstream of the MSIV. The total loop uncertainty of the superheated steam measurement is ((

                                     }}2(a),(c). The two MS flow venturies will have dual transmitters with dual temperature transmitters to support the flow measurement. These temperature sensors will also be used to allow for an assessment of the heat losses through the MS line, and the impact to the calculated velocity at the DHRS side branch entrance. The test plan will specify monitoring steam temperature at these locations and save their data during the test interval.

The pre-test prediction evaluates the uncertainty in the MS flow measurement, but the need to perform velocity measurement for this test is optional because the plant has permanent instrumentation to measure the mass flow rate in the downstream MSS piping outside of the NPM. The free stream velocity in the vicinity of the DHRS steam line tees can be back-calculated from the downstream steam flow rate measurement. Although the velocity profile at the DHRS steam line entrance may exhibit turbulence and swirl from the upstream pipe bends and tee junction (see Figure 5-31), this does not need to be measured explicitly because the AR analysis method is based on the free-stream velocity in the MS pipe upstream of the cavity, and not a local velocity at the cavity entrance. In addition, the back-to-back side openings to the DHRS lines may perturb the velocity profile at the downstream DHRS line tee and this would be seen as slight differences in the dynamic pressure transducer readings between the upstream and downstream DHRS cavities. Design of the DAS is documented in test facility design documents submitted to NuScale for acceptance. The fundamental acoustic frequency of the pipe cavity is less than (( }}2(a),(c). A time signal with a sampling rate five times the highest frequency of interest is sufficient to accurately record the expected pressure pulsations. Therefore, a DAS with a sampling rate of 1000 Hz or higher is used. 5.2.1.3 Description of Required Tests This test includes gathering vibration, flow, and acoustic measurements at various power levels during the initial startup testing. The test should gradually increase the FW pump flow rate such that the DHRS side branch is exposed to a range of partial-power steam flow rates to detect any acoustic excitation by a higher order shear layer mode. When the flow velocity is ramped up from a low value a given resonance mode can be excited by a higher-order shear mode before it is excited by the first order shear mode. The shear-layer excitation is the strongest at the first shear layer mode, where the most severe pressure pulsations are developed. The test procedure specifies a range for the partial power flow rates and a time to hold at each flow rate for sufficient data collection. The partial power testing exercises the test procedures and ensures that vibration levels are acceptable before increasing to the full 100 percent power conditions. The test procedure also specifies a time to hold at full power for sufficient vibration and flow/acoustic measurement data collection. The plant performance parameters in terms of © Copyright 2018 by NuScale Power, LLC 208

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 steam pressure, steam temperature, and flow rate are documented in the final test plan. The test procedure specifies a range for those values in order for data collection to be performed. Variations in these secondary flow conditions affect steam velocity at the DHRS branch lines, but the reactor power level must remain at or below the maximum licensed power level during initial startup testing. The accelerometers measure the acceleration on the MSIVs, MS piping, DHRS actuation valves, and DHRS branch pipes while the plant is operating at each tested condition, which can be converted to a RMS velocity, or a peak displacement. Typically, vibration levels above a certain RMS velocity or displacement limit warrant corrective actions to reduce the vibrations. The test plan will need to establish these thresholds based on ASME OM Part 3 guidelines, and reviewing the vendor design limits for the valves. Stress limits on the piping/welds due to fatigue may also inform the point at which to stop testing and take corrective actions. Vibration responses are manifested differently depending in their source, i.e., responses due to turbulence are typically random, low level spectral amplitudes along the same order of magnitude, whereas an AR source vibration is distinguished as large amplitude responses at distinct frequencies. Vibration signals usually consist of very many frequencies occurring simultaneously, such that a resonant frequency cannot immediately be seen by looking at the time history response. Therefore, a frequency analysis must be performed to break down the vibration time signals into individual frequency components such that a spectrogram is generated and analyzed to verify the presence or absence of AR. Online and offline frequency analysis are performed to determine the amplitude and frequency content of the vibration signals. The dynamic pressure transducers are used for continuous monitoring of the pressure fluctuations in the DHRS branch lines and the MS lines. These measurements can be used to determine if resonance exists at acoustic source frequencies, and to understand the characteristics of the excitations if the piping or valve vibration amplitudes are excessive. Having pressure sensors in each MS line and each DHRS branch line helps determine if local velocity differences have an effect on the pressure fluctuations. The pressure measurements, along with temperature data, determine the uncertainty and bias in the design values for the speed of sound and velocity used in the AR calculation. The inside diameter of the DHRS pipe at the tee connection and length of DHRS piping from CNTS steam tee to DHRS actuation valve seat are key inputs to the analysis. The fillet radius of the tee is currently not defined at the branch/run pipe tee location, but it can be evaluated in the post-test analysis to determine the effective value for the branch opening diameter. The test procedure shall specify that as-built measurements of these variables are recorded to ensure that uncertainty in design inputs have been adequately accounted for in the analysis. Measurements need to be obtained for the inside diameter of both MS lines at the flow sensor location and at the DHRS steam tee, as well as the inside diameter and length of all DHRS branch lines. These measurements can be performed in the factory upon receipt inspection of the fitting or when it is welded as a piping assembly. © Copyright 2018 by NuScale Power, LLC 209

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.2.1.4 Testing Activities Requirements The testing to be performed follows at a minimum the sequence of activities specified in this section. Additional steps are included by the test supplier as needed to effectively and safely conduct the test. For each test period, the vibration monitoring from the accelerometers and dynamic pressure transducers are recorded simultaneously to allow for data interpretation and decision making about test continuation. In the event that an unacceptable vibration response develops any time during initial startup testing, the test conditions are adjusted to stop the vibration and the reason for the vibration anomaly investigated before continuing with the planned testing. Online and offline spectral analysis and time-history analysis are performed to determine the amplitude and frequency content of the vibration signals. Spectral analysis is used to detect large amplitude responses at distinct frequencies, which is indication of the acoustic frequency modes of the DHRS branch line resonating with the MS line VS frequencies. The resulting vibration of the piping systems and DHRS or MSIV valve bodies could cause dynamic loads and fatigue on the locations where maximum stress is expected. The measurements are compared to the established acceptance criteria for each location. The acceptance criteria are based on the allowable vibratory stress limits for the instrumented components. Depending on the practical limitations of sensors placement, cable routing and DAS channels, the in-situ flow measurements (pressure, temperature, and flow rate) do not have to be performed at the same time as the accelerometer measurements, although the impact to overall test duration of sequential measurements should be considered in the test plan. The dynamic pressure transducers or accelerometers can independently indicate if there is an AR condition during operation. The duration for data collection will need to be determined in the test specification and should be sufficiently long enough to allow for stabilized statistical averages in the data. If vibration levels are below the acceptance limit and the test is not stopped due to detection of resonance, a reasonable period for data collection is 1.5 hours for the full power test in order to achieve 1 million cycles of the DHRS side branch natural frequency, which is less than (( }}2(a)(c). For the second order shear layer test, it is not required to achieve 1 million cycles at each flow rate hold point, but the total test duration will depend on the heatup and power ascension rate limits. A final test report is developed to summarize the testing activities and results. The content includes the following, at a minimum.

description of the testing infrastructure, such as drawings, descriptions, and photographs of the NuScale NPM and instrumentation mounting instrumentation diagrams details of the DAS and instrumentation

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 dates of the testing identification of tester or data recorder

discussion of testing methodology
actions taken as a result of any deviations
types of observations collected, for example vibration amplitude dynamic pressure or strain temperature mass flow rate/calculated velocity
test results and results evaluations data files data post processing (extent to be determined in the test specification) identification of personnel evaluating test results documentation of critical instrument channel total uncertainty in an official TEEAR instrument calibration certificates test readiness inspection report completed and signed test procedures

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.2.2 Decay Heat Removal System Acoustic Resonance Pre-Test Prediction Under normal power operating conditions of the NuScale plant, the steam generated in the SG tubes flows from the SG plenums to the CNTS main steam piping. The CNTS main steam piping contains tees that connect to the DHRS steam piping. The piping from the tee to the DHRS actuation valves normally does not have flow because the DHRS is isolated except when it is needed for decay heat removal. This cavity is potentially susceptible to AR (see Figure 5-32). At a critical Strouhal number, the shear layer departing the leading edge of the bifurcation becomes unstable and has the potential to excite acoustic standing waves. These acoustic waves are reflected in the cavity, and the oscillations of the shear layer become enhanced, which results in large fluctuating pressure in the cavity. Figure 5-32 Drawing of decay heat removal system junctions to containment system main steam pipe The design analysis demonstrates margin to the onset of an AR condition due to the first order shear layer associated with a Strouhal number range of 0.35 to 0.62 under all operating conditions. The most limiting operating condition occurs at full power conditions. © Copyright 2018 by NuScale Power, LLC 212

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 During the initial startup test, reactor power is increased to check for fluctuating pressure and vibration due to possible second order shear layers at lower flow rate conditions. Measurements are taken at the limiting full power conditions obtainable within the licensing basis to observe for an AR condition. This calculation assesses input and numerical and measurement uncertainty to inform the range of possible test conditions at which an AR condition occurs. Because the test is performed during initial startup rather than in a test facility, it is not possible to increase flow until a resonance is observed. Further, because positive margin to the resonant condition is demonstrated in the design analysis, it is unlikely that a resonant condition is observed during the testing. This calculation quantifies the expected secondary flow velocity when the onset of AR is expected, and the effect of various uncertainties on the testing and validation of the predicted safety margin. The flow rate where a lower response due to possible second order shear layers is also calculated to inform the range of flow rates during the test when a smaller acoustic response might be observed. 5.2.2.1 Uncertainty Evaluation Uncertainty evaluation is performed to determine the expected flow rate that AR is observed during testing, and the range of possible flow rates based on uncertainties. These parameters are also used to calculate a range of allowable flow rates that validate the design analysis results. The length of the acoustic cavity and diameter of the tee are subject to variation due to manufacturing tolerances. The steam velocity in the CNTS steam piping and the speed of sound in the cavity are subject to uncertainty based on the operating conditions of steam pressure, temperature and flow rate obtained during the test and their associated measured uncertainties. Based on Section 6 of Reference 9.1.9, the Strouhal number at the onset of resonance varies as a function of the tee diameters and the distance from the nearest upstream elbow to the tee. These experimental results are used to inform the uncertainty in the Strouhal number. The effect of each of these uncertainty parameters on the safety margin and the predicted velocity for the onset of a resonant condition is determined using the sensitivity coefficient method. Two input uncertainties that are not analyzed in this calculation are the potential for differences in flow between the two CNTS MS lines, and the effect of the fillet radius on the Strouhal number. The design analysis estimates the effect of differences in flow losses on the safety margin for the two CNTS MS lines. The effect of this difference is (( }}2(a),(c) in terms of the predicted safety margin. Since both CNTS MS lines will be instrumented in this test, any effect of the flow loss differences to the onset of AR will be quantified in the testing and addressed in the post-test analysis. Similarly, the transition to the DHRS branch in CNTS MS tee is specified with a fillet radius rather than a sharp corner that would create a discontinuity equal to the inner diameter of the DHRS steam piping. Use of a fillet radius in the design generates a larger effective diameter at the location where vortices are generated due to the discontinuity. This produces a higher Strouhal number and greater margin to the critical Strouhal number. © Copyright 2018 by NuScale Power, LLC 213

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The dimension of the fillet radius has not yet been specified in the design, so the inner diameter of the DHRS branch piping is used in the Strouhal number calculation since it is bounding. The difference between the as-built fillet radius and tee branch inner diameter and its effect on the Strouhal number can be evaluated in the post-test analysis. The acoustic frequency and the velocity design analysis values are calculated using methods that are not subject to numerical uncertainty. Therefore, the numerical uncertainty in these parameters is zero. Uncertainty in the design analysis predicted safety margin and velocity for the onset of a resonant condition is calculated to inform the expected velocity that an AR condition could be reached during initial startup testing. The uncertainty analysis for the DHRS steam tee is carried out in accordance with Section 4.5.4. Because the testing has not been performed and experimental results are not available, a uniform distribution of uncertainties is estimated for the measurement and input terms to support the sensitivity coefficient method discussed above. The global uncertainty method of Equation 4-14 and Equation 4-15 are applied to the individual parameters relevant to AR. The equations provide the square root of the sample variance, also referred to as the standard deviation. This provides a method to estimate the interval or range of uncertainty in a parameter (i.e., x +/- u). 5.2.2.2 Bias Considerations in the Test This test is performed during initial startup testing on the first NPM at full power and flow conditions. Therefore, there are no experimental distortions between the design analyses and the test condition that affect the expected or allowable range for validating the design analysis. There is analytical bias between the best-estimate and conservative design analysis results. Because the best-estimate predictions are used to define the expected results in Section 5.2.2.3, this result quantifies the value of the analytical bias. 5.2.2.3 Expected and Validation Range of Experimental Results The predicted, or expected, experimental result consists of the best-estimate safety margin, plus any test distortion adjustments. The range of experimental results is based on adding and subtracting the design analysis safety margin and the total uncertainty. The total uncertainty consists of both the design analysis input uncertainty and the measurement uncertainty. As discussed in Section 5.2.2.2, the experimental bias for this test is zero, so only the design analysis uncertainties and the test uncertainties need to be considered, as shown in Equation 5-1 and Equation 5-2. © Copyright 2018 by NuScale Power, LLC 214

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 RangeAR.High = SMBE + SMDA + SMu,meas + SMu,inp Equation 5-1 RangeAR.Low = SMBE SMu.meas SMu.inp Equation 5-2 Where, R a n g e AR = Range of safety margins for validation (%), SMBE = Best-estimate safety margin (%), SMDA = Safety margin from the design analysis (%), SMu,inp = Safety margin adjustment from input uncertainty (%), and SMu,meas = Safety margin adjustment from measurement uncertainty (%). As this testing is performed during initial startup testing with the reactor critical in order to achieve full power secondary side flow rate conditions, flow rate cannot be increased any higher than the licensing design basis allows. Because the design analysis predicts a sufficiently positive safety margin to the onset of the phenomena, the expected onset of an AR condition and the allowable range are above the licensing design basis of the NuScale design. The allowable range of flow rates cannot be fully exercised in the test program. If an AR condition is not achieved during the testing, this impacts the ability to explicitly quantify the conservatisms in the design analysis. The lack of AR onset during flow testing, covering the full range of operating conditions up to the limiting full power flow rates, confirms that the DHRS steam tee will not experience AR under any licensing basis operating condition for the NuScale design. The safety margin range is calculated and then it is converted to the main parameter that will be monitored during the testing, which is the flow velocity. This provides the expected flow rate for an AR condition to occur corresponding to each calculated safety margin value. vmeasure = vassume (1+ SM) Equation 5-3 Where, vmeasure = Velocity to be measured, corresponding to a safety margin (%), vassume = Velocity assumed in safety margin calculation (%), and Safety margin (design analysis, best estimate, upper or lower validation SM = range) (%). © Copyright 2018 by NuScale Power, LLC 215

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.2.2.4 Second Order Shear Layer To investigate second order shear layers, testing occurs from ascending partial power flow rate to measure excitation of higher order shear layer modes. Acoustic pressures are lower for a second order shear layer mode compared to a first order shear layer mode (referred to herein as the AR condition). The second order shear layer is expected to occur at twice the Strouhal number range of the AR condition: 0.70 - 1.24. The flow rate range that corresponds to the Strouhal number range is calculated and the associated reactor power levels are specified. Equation 5-4 solves for the flow velocity as a function of the Strouhal number. The velocity range for the second order shear layer is determined based on the Strouhal number range of 0.70 - 1.24. Due to the larger Strouhal number, most of the flow rates associated with this range are within the licensing design basis and can be achieved during initial startup testing operation. cdc v= Equation 5-4 4S(L + 0.3d ) Where, v = Flow velocity (ft/s), S = Strouhal number (-), L = Length of acoustic cavity (ft), d = Inner diameter of piping (ft), c = Speed of sound (ft/s), and dc = Characteristic length of the discontinuity (ft). 5.2.2.5 Expected Ranges for Test Variables Section 5.2.1 discusses the scope of testing needs for the AR startup test. The permanently installed steam pressure and temperature sensors are used to record the pressure and temperatures during the flow test. Permanently installed steam flow rate measurement is also used. Temporary instrumentation consists of dynamic pressure sensors and accelerometers. Signals from the dynamic pressure sensors and accelerometers are the primary means of identifying an AR condition during the test. If a resonant condition occurs, higher vibration amplitudes and dynamic pressures are measured. From these signals, the acoustic frequency can be identified. The presence of an acoustic frequency signature in the signals distinguishes a resonant condition compared to noise due to turbulence. First- and second-order shear layers both excite the same acoustic mode. The magnitude of the dynamic pressure fluctuations and accelerations is the primary difference between whether a first or second order shear layer is excited. A second-order shear layer produces © Copyright 2018 by NuScale Power, LLC 216

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 a response that is not significantly higher than from turbulence. Whereas if an AR condition occurs, the accelerations and dynamic pressure fluctuations are significantly higher than from turbulence. Pressure is a controlled process variable in the NuScale design, so significant variations in this parameter at the full power test condition is not expected. The actual pressure is subject to variability of (( }}2(a),(c) psi. The effect of this variation on the safety margin and velocity where a resonance is expected has been accounted for in the measurement uncertainty assessment. There should be no observed difference between the expected (500 psia) and measured pressure during this test. If this occurs it requires assessment in the post-test analysis. Steam temperature is subject to measurement uncertainty and design analysis uncertainty, based on limitations to accurately predict SG performance and natural circulation flow. Input uncertainty in the steam temperature is approximately ((

                                                                             }}2(a),(c). Temperature measurement uncertainty is ((                                          }} 2(a),(c). These uncertainties have been accounted for in the input and measurement uncertainty assessments. During this test, the observed steam temperature should be within about ((                                        }}2(a),(c) degrees Fahrenheit of the expected value (584.4 degrees Fahrenheit). Larger differences require assessment in the post-test analysis.

The flowmeter is located outside of the reactor building, so a small reduction in steam superheat temperature due to heat loss in the piping and a reduction in steam pressure due to flow losses are expected. This may produce a smaller velocity at the measured location compared to the location of interest for this test (the CNTS main steam piping at the DHRS steam tee). This difference is small and is not accounted for in the pre-test prediction but can be assessed in the post-test analysis. The assumed velocity measurement uncertainty based on the uncertainty of the venturi flowmeter, is ((

                    }}2(a),(c). Additionally, because the flow rate measurement occurs in different size piping (NPS12 SCH160 versus NPS12 SCH80), the ratio of the measured versus the test location area uncertainty is accounted for in the velocity measurement uncertainty determination.

Based on the range of possible thermal hydraulic parameters, variations in the volumetric flow rate are quantified and combined with the uncertainties in the piping inner diameter at the measurement and test locations to determine the total input uncertainty for velocity. Measurement and input uncertainties are (( }}2(a),(c), respectively. 5.2.2.6 Results and Conclusions This calculation provides the pre-test prediction results for AR testing of the DHRS steam line tee locations. The primary goal of the testing is to validate that AR does not occur at this location during limiting operating conditions. Additionally, the presence of second-order shear layers is investigated at lower flow rate conditions. The results of this calculation show the effects of various input and measurement uncertainties on both the predicted safety margin and the velocity where an AR onset is possible. Table 5-36 summarizes the values of input and measurement uncertainty and © Copyright 2018 by NuScale Power, LLC 217

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 the u terms identify their magnitude. The results show that the cavity length has the largest input uncertainty, and the flow measurement has the highest measurement uncertainty. Per the analysis methodology, the u terms are combinedby square root sum of squares to produce the total input and measurement uncertainty. Input uncertainty is (( }}2(a),(c) and measurement uncertainty is (( }}2(a),(c). Table 5-36 Input and measurement uncertainties Input Measurement Parameter Uxii Input Uxii Measurement Uncertainty Uncertainty Speed of Sound (( }}2(a),(c) Cavity Diameter (( }}2(a),(c) Cavity Length (( }}2(a),(c) Flow Velocity (( }}2(a),(c) Strouhal Number (( }}2(a),(c) Total (( }}2(a),(c) The best-estimate safety margin for the onset of AR is (( }}2(a),(c) and considering the input uncertainty only, the safety margin range is ((

                     }}2(a),(c). The design analysis safety margin is ((                          }}2(a),(c), below the input uncertainty range based on the overall conservatisms in the design analysis inputs and the use of square root sum of squares to calculate the total input uncertainty.

The test is performed on the NPM during initial startup testing so there are no distortions in the test. Therefore, the best-estimate safety margin of (( }}2(a),(c) represents the expected test results, and the validation range is ((

                     }}2(a),(c). This range corresponds to flow velocities of ((
              }}2(a),(c) with an expected flow velocity for the onset of a resonant condition at ((
              }}2(a),(c). The nominal, full power flow velocity is ((                      }}2(a),(c) including the 5 percent transient margin, and ((                     }}2(a),(c) at steady-state conditions. This pre-test prediction quantifies the margin to the onset of the AR phenomenon, accounting for possible input and measurement uncertainties. These results are summarized in Table 5-37.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 5-37 Expected and allowable results for acoustic resonance and second order shear layers Validation Safety Expected Expected Validation Velocity Parameter Margin Range for Safety Margin Velocity Range for Test Test Design Analysis (( }}2(a),(c) Best-Estimate ((

                                                                                                    }}2(a),(c)

Initial Startup Test Nominal Flow Velocity (( }}2(a),(c) 2nd Order Shear Layer ((

                                                                                                    }}2(a),(c)

Second-order shear layers occur at lower flow velocities. If this phenomenon occurs at the DHRS steam line tee locations, it is expected to be observed between ((

                 }}2(a),(c) ft/s.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.3 Steam Generator Inlet Flow Restrictor Validation Testing Each individual SG tube of the HCSG tube bundle requires an inlet flow restriction device to maintain stability of the secondary side flow conditions. The flow restrictor fits into the tube inlet. Due to the design of the device, a small annular flow channel exists between the device and inner diameter of the tube. This narrow flow annulus and the flexibility of the IFR are design attributes that could make this device susceptible to LFI. The IFR also experiences vibration due to random turbulence but that response is much smaller than any potential excitation produced by LFI. Leakage flow instability is a complex phenomenon and previous research has demonstrated that this source of flow excitation is sensitive to the flow and the structural details. As such, the industry has not developed general acceptance criteria to avoid LFI and there are no commonly used equations that predict the critical velocity associated with LFI. Therefore, an analysis of LFI of the SG tube IFR is not performed; instead, prototypical FIV tests are performed to fulfill the requirements of Regulatory Guide 1.20 To validate the final design of the SG IFR, follow-up testing supplements the benchmark testing discussed in Section 3.1. The purpose of this test is to demonstrate that the final design of the SG IFR does not experience unacceptable vibration. Due to the ability to gather higher quality and quantity test data, testing of the component is performed in advance of the startup test program, at a test facility. The specific objectives of this test are:

Perform modal testing of the IFR to obtain the first two modal frequencies, both with the device in air and with the device submerged in water.
Demonstrate that the design of the IFR does not experience unacceptable flow excitation due to LFI for the full range of operating conditions and expected manufacturing and installation tolerances. Showing 100 percent safety margin (i.e., no LFI at twice the full-power FW flow rate) is desirable.
Acquire 106 cycles of vibration for IFR test specimens according to the recommendation of Regulatory Guide 1.20 (Reference 9.1.5), and examine wear resulting from vibration of the IFR during testing. This includes both wear on the IFR as well as wear on the model SG tube.

5.3.1 Test Facility General Arrangement, Accessibility, and Special Features Due to the small size of the IFR, the design of the test facility allows multiple specimens to be tested concurrently and/or without draining the test loop between each test, if it is cost-effective to do so (i.e., if the savings in reducing the overall number of tests can offset the complexity and additional testing hardware and instrumentation required to run multiple simultaneous test cases). Testing more than one flow restrictor in a single plenum is acceptable because the effects of any geometrical differences between the test plenum and a prototypic one are negligible. In order to test different IFR alignment and bolt compression conditions, the test facility either provides access to tighten the IFR bolt after installation in the tube or it allows the IFR to be placed in the tube after being aligned and bolted to a mounting fixture. © Copyright 2018 by NuScale Power, LLC 220

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 If concurrent testing is performed, the test specimen design ensures that any noise and structural vibration transmitted between specimens is consistent with (not exceeding) what would be expected from a fully prototypic operating environment. 5.3.2 Test Facility Fabrication Requirements The SG IFR drawing specifies the dimensions and materials for the IFR and its mounting plate. The dimensions and materials of the flow restrictor, flow restrictor bolt, washer, and locknut are reproduced without modification. Figure 5-33, shows the configuration and flow path for the flow restrictor as installed in the reactor module (this figure is not intended to control the design of the test fixture). Figure 5-34 gives dimensions of the two main IFR components: the flow restrictor and bolt. The test specimens are fabricated within specified tolerances to ensure the test specimens are geometrically prototypic. Additionally, different test restrictors are fabricated with steps at the nominal and maximum step diameters. Leakage flow instability is a self-perpetuating phenomenon driven by fluctuating pressure differentials across constrictions. A variation in step diameter by the allowed tolerance has a higher relative effect on the constriction gap width, and thus constriction pressure drop, than a variation in step length or overall IFR length. Therefore, step diameter tolerance is specifically included as a test parameter. ((

                                                                                                          }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 ((

                                                                                                          }}2(a),(c)

Figure 5-34 Dimensions of inlet flow restrictor and flow restrictor bolt In the installed configuration, the IFR is contained within the portion of the SG tube that penetrates the FW plenum tubesheet. This length of tube is rigid compared to the IFR, which is replicated during testing to minimize experimental bias that could be introduced © Copyright 2018 by NuScale Power, LLC 222

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 by flexibility in this flow boundary. The method of providing stiffness is left to the testing services supplier and includes (but is not limited to) addition of supports along the length of tube inside the tubesheet or added tube wall thickness. The minimum length of the rigid section is equal to the depth of the tubesheet holes. For the in-water modal test, the wall stiffness design solution allows sufficient access to the flow restrictor to permit excitation while it is installed in the tube. Instrument penetrations in the portion of the tube surrounding the flow restrictor are not permitted unless flush with the inside diameter of the tube such that no flow disturbance is generated. The IFR mounting plate is altered because the full quantity of IFRs is not being tested. Modifications to the mounting plate maintain prototypic mechanical restraint without loss of rigidity. The system for mounting the IFR allows some test specimens to be aligned eccentrically, that is, offset radially from the centerline of the tube. Eccentricities of 0 percent, 50 percent, and 100 percent shall be tested, where 0 percent is a centered IFR and 100 percent means the IFR is contacting the tube wall with negligible force. In addition, a method to install the test IFR with a specified contact load between it and the tube wall is provided. Stack-up of tube geometric tolerances has the potential to result in a wide range of diametrical clearances between the IFR and tube wall (Table 5-38). A tube and IFR set for each of these three clearance conditions are created for the test, in order to gauge the effect of the relevant tolerances on the performance of the IFR. In the minimum clearance model, an IFR with the maximum allowed step diameter is used. The other two clearance conditions use a nominal-diameter IFR. Table 5-38 Range of possible radial clearances between inlet flow restrictor and tube wall Maximum clearance (( }}2(a),(c) Nominal clearance (( }}2(a),(c) Minimum clearance (( }}2(a),(c) Material of construction for the tube(s) in the test facility is 304 or 316 stainless steel. Tubing for the test is acquired from NuScales existing stock of Alloy 690 SG tubes. Another tube material may be proposed by the supplier and approved by NuScale; for instance, a nonmetallic tube that permits optical measurement of flow restrictor vibration. In general, the tube material is not a controlling parameter for this test and is selected for compatibility with test conditions and proposed measurement methods. Unless specified above, other materials selected are at the discretion of the testing services supplier, subject to approval by NuScale design engineering. Materials selected should be of sufficient quality to meet any applicable facility design code requirements and to prevent the generation or accumulation of significant amounts of corrosion or wear products in the test fixture. © Copyright 2018 by NuScale Power, LLC 223

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 The test fixture design is in conformance with applicable pressure vessel and structural codes and standards in effect where pressurization and operation of the test specimen occurs. Construction and fabrication of the test fixture are in accordance with applicable design codes. Information concerning applicable codes and information demonstrating conformance of the test fixtures is to be provided to NuScale for information upon request. 5.3.3 Test Facility Operating Requirements Table 5-39 provides the minimum and maximum pressures, temperatures, and flow rates required of the test facility. The values are given in ranges rather than as individual test conditions. The pressure and temperature for each volumetric flow rate are specified in Section 5.3.7.3. Table 5-39 Range of flow conditions for steam generator inlet flow restrictor tests Pressure (psia) (( }}2(a),(c) Temperature (°F) (( }}2(a),(c) Flow Rate (gpm) (( }}2(a),(c) (1) Flow rate is on a per-IFR basis. Multiply by number of IFRs tested simultaneously to determine the total facility flow rate. This flow rate range represents conditions from zero reactor power to greater than three times the FW flow rate necessary to demonstrate 100% margin to LFI. The test facility pump is selected so that the frequencies of pressure waves arising from pump operation do not coincide with major structural frequencies of the IFR or of the text fixture over the range of flowrates required to perform testing. Blade passing frequency is considered if a centrifugal pump is selected. If a positive displacement pump is used, the flow pulsation frequency is compared to the structural frequencies. Reciprocating positive displacement pumps are not be used. 5.3.4 Test Facility Control Requirements The test facility shall have the ability to smoothly increase the flow rate between the minimum and maximum per-tube flow rates in Table 5-39, and to hold a steady-state flow at any point between the minimum and maximum. Controls on test facility flow rate shall maintain the flow rate within (( }}2(a),(c) of the setpoint (considering uncertainty in the flow meter used for input to the control system) for steady-state flow test data collection when the total facility flow rate is (( }}2(a),(c) or less, and within ((

                     }} 2(a),(c) of the setpoint for total flow rates above ((                      }}2(a),(c). This provides reasonable control bands for facility designs where few IFR specimens are tested simultaneously and designs where several are tested simultaneously. If multiple IFR specimens are tested simultaneously, it is recommended that a separate flow instrument is used for flow control, rather than a summation of the individual IFR flow instruments.

Temperature shall be maintained (( }}2(a),(c) degrees F from the nominal test case temperature (in addition to any relaxation in the temperature setpoint range). Considering the instrument uncertainty specified in Section 5.3.5, this keeps the temperature within (( }}2(a),(c) degrees F of the target value. In turn, fluid properties of viscosity and density do not vary by more than (( }}2(a),(c). © Copyright 2018 by NuScale Power, LLC 224

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Pressure variations do not exceed (( }}2(a),(c). Slow changes in pressure during a test are acceptable because properties of liquid water are not highly dependent on pressure. Fast pressure fluctuations (e.g., several times over a ten second span) are not acceptable. Test facility water quality controls are proposed by the supplier and approved by NuScale. Water quality is adequate to prevent introduction of gross impurities and/or detrimental corrosion of the test facility. Four parameters are of primary importance to measure in this test: modal frequencies, vibration amplitude, flow temperature, and flow rate. Additionally, plenum static pressure, dynamic pressure downstream of the IFR, and differential pressure across the IFR are recorded. The type and specifications of the instrumentation used to acquire the measurements are proposed by the testing services supplier and must be approved by NuScale before commencement of test facility construction or procurement of the instrumentation and DAS. The following subsections present needed attributes of the instrumentation for each measured parameter but do not select the type of instrumentation to be used to record the primary parameters. All instrumentation discussed below, except for two, are considered critical instrumentation - the proper operation of which is necessary to accomplish the testing objectives. The two noncritical instruments are (1) the plenum static pressure instrument, because static pressure is not a controlling parameter for leakage flow instability. (2) the instrumentation used to measure differential pressure across the IFR, since validation of thermal-hydraulic analyses related to IFR pressure drop is not an objective of this test. For the in-air and in-water frequency tests, the first two modal frequencies of the IFR shall be measured. This requires an instrumentation frequency range of at least ((

                 }}2(a),(c) Hz.

5.3.5 Flow Test Instrumentation During the FIV testing, the IFR is mounted in a representation of the SG tube. IFR vibration amplitudes are measured during the FIV tests; however, the confined space presents a challenge for mounting instrumentation and routing cables. The method proposed by the testing services supplier may include (but is not limited to) directly-mounted accelerometers, strain gauges, or optical measurement. The vibration instrumentation has a frequency range of at least (( }}2(a),(c) Hz in order to measure vibration at the first two modal frequencies of the flow restrictor. It is capable of measuring a minimum displacement of (( }}2(a),(c) inch, which is a quarter of the minimum IFR-tube radial clerance (Table 5-38). Total measurement uncertainty for the vibration instrumentation shall be (( }}2(a),(c) percent of the minimum detectable displacement. © Copyright 2018 by NuScale Power, LLC 225

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 If practical, it is also desirable to obtain maximum IFR stress and strain data in both translational directions. This data is intended to verify that the IFR does not experience high cycle fatigue failure created by TB or LFI. The strain data is also processed to search for indication of LFI vibration. Vibration measurements are taken at the outside of the tube downstream of the IFR as another method of monitoring for IFR vibration, and at the mounting plate in order to provide a reference signal for noise reduction in the IFR vibration data. Pressure transducers are installed in the test apparatus for the FIV testing. One is located in the FW plenum to measure the static pressure upstream of the IFR. Two dynamic pressure transducers are installed on the tube immediately downstream of the IFR, within approximately an inch of the IFR tip. These sensors are installed opposing one another so that both can tap into the tube at the same axial location. This provides sensor redundancy while avoiding a situation where additional flow turbulence created by an upstream pressure tap affects data collected downstream. Finally, a differential pressure instrument is supplied to measure the pressure drop across the IFR. Its upstream tap is placed in the plenum and the downstream tap located to minimize measurement fluctuations due to flow disturbances created by the IFR. The dynamic pressure transducers are used to monitor and record the pressure fluctuations associated with turbulence for the spectrum of frequencies that are measured. They provide an alternate method of monitoring for LFI through the ability to view pressure fluctuations at the discrete frequencies associated with the phenomenon. The dynamic pressure transducers have an amplitude range of (( }}2(a),(c) psi and a minimum frequency range of (( }} 2(a),(c) Hz. The sensor used to measure static pressure has a range of (( }}2(a),(c) psia. The differential pressure instrumentation has a range of (( }}2(a),(c) psid. At 100 percent power, the flow restrictor generates a pressure drop of about (( }}2(a),(c) psi. (( }} 2(a),(c) psid is specified in order to provide differential pressure measurement capability when testing at (( }}2(a),(c), because pressure drop increases by the square of the flow rate. Total measurement uncertainty for pressure instrumentation shall be as follows: dynamic pressure instruments: (( }}2(a),(c) percent of full scale, static pressure instrument: (( }}2(a),(c) percent of full scale, differential pressure instrument: (( }}2(a),(c) percent of range. Instrumentation is provided to record the fluid temperature in the FW plenum. The instrument range shall be capable of measuring liquid water temperatures up to (( }}2(a),(c) degrees F. In combination with the temperature control tolerance in Section 5.3.4, this keeps the recorded temperature variation to within (( }}2(a),(c) degrees F of the true value. In turn, fluid properties of viscosity and density do not vary by more than (( }}2(a),(c). The flow rate in the test facility shall be recorded individually for each flow restrictor undergoing testing. The flow instrumentation shall have a range of (( }}2(a),(c) gpm to © Copyright 2018 by NuScale Power, LLC 226

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 encompass the range of test flow rates. If a separate flow instrument is used to control the overall test loop flow rate, its range shall be 3 gpm multiplied by the maximum number of simultaneously-tested IFR specimens. Flow rate measurement total uncertainty shall be (( }}2(a),(c) gpm for each tubes flow instrument. This is better than (( }}2(a),(c) percent of the full power FW flow on a per-tube basis. If a separate flow instrument is used to control the overall flow rate to multiple IFR specimens, its total uncertainty shall be (( }}2(a),(c) of its range. Critical instruments are within their manufacturers recommended test service supplier calibration periodicity through the end of the testing period. Calibration and verification conform to the test service suppliers program requirements. For any instrumentation that is permanently installed, to the extent practical, calibration is performed just before installation. Records of the results of calibration and verification are maintained. 5.3.6 Data Acquisition System Performance Requirements Design of the DAS is documented and submitted to NuScale for acceptance. The specification for the transducers, the signal conditioning equipment, data conversion and storage procedures and the calibration procedures are accepted by NuScale before fabrication of the test facility. The DAS for modal testing provides real-time frequency response display and recording. Real-time displays of frequency response are calculated using data from the beginning of the test run until the current display time. During the modal testing, the sampling rate is 3,000 Hz. An aliasing filter is provided to prevent frequencies above half the sampling frequency from appearing when the data is represented in the frequency domain. Real-time frequency response is displayed during the FIV tests. The sampling rate for the FIV tests is 3,000 Hz; an aliasing filter again is used. Data is collected continuously for each FIV test beginning at the initiation of flow through the test loop and persisting until the upper limit of the flow rate ramp-up is reached. At each planned hold point, or unplanned hold for abnormal vibration, data shall be collected for 10 minutes after reaching steady-state conditions. Applicable guidelines from Reference 9.1.1 are also considered. Critical instrument channel total uncertainty is documented in an official TEEAR. During testing, plots of various instrument values vs. time are displayed to assist in verifying the FIV performance of the IFR. Displacement, acceleration, and dynamic pressure time history plots of the IFR are included, as well as real-time display of frequency response. © Copyright 2018 by NuScale Power, LLC 227

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.3.7 Description of Required Tests An overview of the required flow restrictor tests is provided in this section. These include in-air and in-water modal tests to obtain the first two IFR modal frequencies, and tests to evaluate FIV. The test program is divided into three steps:

In-air modal test: the first two modal frequencies are measured
In-water (still) modal test: the first two modal frequencies are measured with the IFR submerged
FIV testing: vibratory response is recorded while the IFR is subjected to various flow conditions.

5.3.7.1 In-Air Modal Test The in-air modal test determines the first two modal frequencies of the IFR without the hydrodynamic mass effects of the fluid that would be present during operation. For this test, the IFR is not tested inside the SG tube. However, the prototypical restraint of the IFR with its mounting plate is preserved with this test. This test is performed at room temperature for each of the two IFR compression (bolt tension) conditions described for the FIV testing. An IFR manufactured to nominal dimensions (including step diameter) shall be used. Excitation is imparted to the IFR using a method proposed by the testing services supplier and accepted by NuScale that is compatible with the chosen instrumentation scheme and that is capable of exciting the first two modes of the IFR. In addition to the primary instrumentation used to record vibration results during the modal testing, data is collected from any additional instrumentation preinstalled for the FIV testing that can provide vibration data. The excitation input to the IFR is also recorded. For each modal frequency determined, a duplicate value is obtained. If divergent results are observed for the duplicate tests, additional test runs may be requested consistent results are observed. 5.3.7.2 Static In-Water Modal Test The in-water modal test determines the first two modal frequencies of the IFR while accounting for the damping effects of the fluid that would be present during operation. This test is performed two ways: with the IFR outside the SG tube and with the IFR installed centered in the tube. The prototypical restraint of the IFR with its mounting plate is preserved with this test and the test shall be performed for each of the three radial clearance conditions. The results are compared to gauge the hydrodynamic mass effects upon the fundamental frequency of the IFR resulting from the thin fluid-filled annulus. This test is performed at room temperature and without flow. All other requirement for the in-water modal testing are the same as for the in-air test. © Copyright 2018 by NuScale Power, LLC 228

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.3.7.3 In-Water Flow Induced Vibration Test The FIV test is to assess if LFI of the IFR occurs at any normally expected operating flow rate. The IFR is installed in the SG tube and mounted to preserve both the structural and thermal hydraulic boundary conditions. Numerous test cases are required to cover the range of expected operating flow rates and temperatures and the various aspects of IFR installation. Four general parameters are varied to execute the IFR FIV testing: flow conditions, and the compression, radial clearance, and alignment of the flow restrictor. Flow Rate, Temperature, and Pressure Flow rate testing of the IFR is by means of a flow ramp-up from no flow to an elevated flow rate much higher than expected for any operational mode, high enough to show 100 percent safety margin against LFI. After each IFR test specimen is installed, FW flow is initiated and ramped from (( }}2(a),(c) gpm per tube at a maximum of (( }}2(a),(c) gpm per minute, per tube. At discrete points during testing, the ramp is paused to allow steady-state data collection. These points are 33 percent, 66 percent, 99 percent, and 133 percent of the full power FW flow: (( }}2(a),(c) gpm/tube, (( }}2(a),(c) gpm/tube, (( }}2(a),(c) gpm/tube, and (( }} 2(a),(c) gpm/tube. The flow ramp shall also be paused for steady-state data collection any time that abnormal vibration response is indicated by real-time monitoring. Data shall be collected for ten minutes following the establishment of steady-state conditions at each hold point, then the flow ramp shall resume. If more than one IFR specimen is tested concurrently, a separate flow instrument is used to control the overall test loop flow rate. The measurements from this instrument should be used to determine when the steady-flow hold points and upper end of the flow ramp have been reached because individual tube flow rates are expected to be slightly dissimilar due to differing IFR installation conditions. The IFR is tested at three different flow temperature-pressure combinations.

T1 represents low reactor power FW conditions: (( }}2(a),(c) psia and

(( }}2(a),(c) degrees F. The test case pressure is lower, corresponding to a room temperature flow. Leakage flow instability is not expected to occur at or below the normal full-power FW flow rate; therefore, the low temperature test conditions are more approximate.

T2 simulates full-temperature FW flow: (( }}2(a),(c) degrees F. Static pressure has a negligible influence on LFI; therefore, (( }}2(a),(c) psia is chosen to ensure the flow remains subcooled and not require excessive design pressures for the test facility.
T3 tests above full-temperature FW flow: (( }}2(a),(c) degrees F and (( }}2(a),(c) psia. The pressure for this test case is selected identically to T2 above because pressure is not a controlling hydraulic variable for LFI. Condition T3 provides 10%

margin above the full-power feedwater temperature. This is conservative, as demonstrated by testing of boiling water reactor jet pumps that showed that increasing © Copyright 2018 by NuScale Power, LLC 229

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 fluid temperature decreased the differential pressure at which leakage flow instability developed (Reference 9.1.10, p. 4-2). In application to the IFR, this is equivalent to reducing the critical flow rate for onset of LFI. Compression In its installed configuration, the IFR is compressed by the through-bolt that fastens it to the mounting plate. Varying amounts of compression affect the stiffness of the restrictor, so two different fastener conditions are investigated during testing. The test matrix abbreviations for the two states are defined below:

C1: standard installation with all parts shown on the drawing.
C2: IFR is installed with a second flat washer underneath the locknut and the locknut is tightened to the over-torque specification to place excess compression on the IFR.

The torque specifications for the IFR are provided in the test specification. Radial Clearance Per Table 5-38, the range of radial clearances to be used in the test are as follows.

Minimum (min.): ((

                                                    }}2(a),(c)

Only the nominal radial clearance is tested for off-normal compression condition C2. The as-designed configuration of the IFR is of primary interest in the testing, so fewer test cases are acceptable for scenarios that do not fully represent a design configuration installation. Eccentricity and Preload Eccentricity is the radial distance off-center that the IFR is installed, given in the test matrix as a percentage of the width of the gap between the IFR and the tube wall. Three eccentricities are specified: (( }}2(a),(c), where (( }}2(a),(c) percent represents the IFR touching the tube wall with insignificant contact force. The eccentricity tolerance is (( }}2(a),(c) percentage points, except at the 100 percent eccentricity condition which is (( }}2(a),(c) percentage points. The methods of setting and verifying eccentricity are sensitive enough to meet these requirements. The actual eccentricity for each test case, measured both before and after the test run, is recorded and included in the final test report (see Section 5.3.8). It is possible that some flow restrictors are in contact with the SG tube wall after installation and that this will apply a load to the IFR. This is not the design configuration for the IFR, so it is not examined in every test case, but it is of interest because imperfections in installation or bowing of the tubesheet due to thermal and pressure effects could create the situation. Two preloads are tested by positioning the IFR in the tube such that a load is applied from pressing against the tube wall. These preloads are described below and depicted in Figure 5-35. © Copyright 2018 by NuScale Power, LLC 230

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0

P1: lower preload force applied to one side of the IFR that may deflect the IFR, but not to the extent that part of the IFR touches the SG tube wall opposite the location of the applied force
P2: a higher preload force displaces the IFR enough that the base and tip are contacting opposite faces of the tube wall. The IFR vibrates similar to a fixed-pinned beam in this situation, if any LFI occurs. If IFR vibration is customarily measured at the tip, the location needs to be changed to a higher-displacement location on the IFR for P2 test cases. Note that if it is determined that preload P2 causes yielding of the flow restrictor material, the force is reduced to some multiple of the P1 force that does not cause the material to yield.

The two preload force values are determined before the test. ((

                                                                                                        }}2(a),(c)

Figure 5-35 Preload conditions (not to scale) To optimize the test matrix, and because installation with a preload is not the design of the IFR, preload conditions are tested for a subset of flow and clearance states. Table 5-40 provides the test matrix. It is recommended that the FIV tests are performed at temperatures in order from T1 to T3. Starting with the lowest temperature is more conducive to troubleshooting, if issues arise early during testing. As used in the matrix, the term test specimen is defined as a unique combination of installation parameters, thus a single physical IFR could fill the role of more than one test specimen upon removal and reinstallation in a different configuration. In general, the test matrix is ordered so that conditions that are closer to the nominal design configuration are listed earlier. Aside from test temperature, the order of testing compression, radial clearance, and eccentricity or preload is of low importance. Four preload tests are included in the matrix, two each at compression states C1 and C2. Because the IFR is not intended to be installed with a contact force between itself and the tube wall, the preload conditions are not studied as extensively. The test matrix has not been screened from a design-of-experiments perspective, so the testing services supplier is encouraged to provide input on potential streamlining of the matrix. © Copyright 2018 by NuScale Power, LLC 231

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 If leakage FIV is encountered during the flow ramp, below the full-power flow rate ((( }}2(a),(c) gpm/tube), for any test specimen at compression C1 or C2, then the remainder of the testing may be postponed at the direction of the NuScale test engineer until a solution is produced. During FIV testing of the IFR, test specimens (( }}2(a),(c) (listed in Table 5-40 shall be retested at the flow temperatures given in the right-hand column of Table 5-40 on a different day than the original tests to show consistency. More test cases may be specified for repeat if it is warranted based on the results of the first repeatability study. The test cases selected for the repeatability assessment are a sample of about 15 percent of the test matrix and cover the flow rates and include at least one example of each clearance and alignment condition for fastener conditions C1 and C2. These choices are open to modification if statistical analysis or experience of the testing services supplier indicate that it would be advisable. The total duration of FIV testing for each IFR used in the test shall be enough to capture 106 cycles of vibration assuming the IFR is vibrating at the in-water fundamental frequency determined in the modal testing. At the predicted fundamental frequency of (( }}2(a),(c) Hz, this requires a total of at least (( }}2(a),(c) minutes of FIV testing for each restrictor. The 10 cycles are not required to be consecutive; they may be 6 collected over the course of multiple test runs. Table 5-40 SG IFR flow test matrix Test Specimen IFR Radial Eccentricity/Pre Repeat at Flow

                #                 Compression               Clearance              load              Temperature Ramp flow from ((                          }}2(a),(c) for flow temperature cases T1, T2, and T3 1                      ((                                                                  }}2(a),(c) 2                      ((                                                                 }}2(a),(c) 3                      ((                                                                 }}2(a),(c) 4                      ((                                                                 }}2(a),(c) 5                      ((                                                                  }}2(a),(c) 6                      ((                                                                 }}2(a),(c) 7                      ((                                                                  }}2(a),(c) 8                      ((                                                                 }}2(a),(c) 9                      ((                                                                  }}2(a),(c) 10                     ((                                                                 }}2(a),(c) 11                     ((                                                                  }}2(a),(c) 12                     ((                                                                 }}2(a),(c) 13                     ((                                                                  }}2(a),(c) 14                     ((                                                                  }}2(a),(c) 15                     ((                                                                 }}2(a),(c) 16                     ((                                                                  }}2(a),(c)

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 After all FIV test cases are completed, the test specimens and SG tubes are visually inspected for wear caused by impact between the IFR and the tube wall and the results documented in the final test report. A unique identifier is created for each flow restrictor and tied to the corresponding data files in the DAS output to allow easier correlation of IFR wear to overall time in the flow. The same restrictor specimen is used for the preload test cases, if possible, because this may affect the wear on the device. As part of the initial startup testing performed after NuScale power plant construction, the IFR is subject to a Section XI VT-3 visual examination (Reference 9.1.8, IWB-3520.2). It is therefore recommended that the wear examination conducted after the FIV testing outlined in this report inspects the test specimens and tubes for the applicable VT-3 relevant conditions listed in Section XI, IWB-3520.2. Alternatively, the testing services supplier may propose other inspection methods and criteria, to be agreed upon with NuScale before testing commences. Note that if a nonmetallic material is used to model the SG tubes (for instance, to allow optical measurement of IFR vibration amplitude), the ensuing wear will not be prototypic. However, the wear data is still collected for informational purposes. The objective of the FIV tests is to demonstrate that leakage FIV does not occur for test cases that bound the expected operating conditions for the NPM. Individual test points have been established to provide for discrete periods of steady-state data to support sufficient evaluations. Because this test sweeps a range of flow rates, it is necessary to maintain continuous data recording, including during transitions that take place between identified discrete data collection periods. It is possible that abnormal vibration could occur during these transitions or at flow rates encompassed by these transition flows. Therefore, for FIV testing there are three types of testing data required:

continuous data files for each time period the test facility is in operation, including all test runs for that time period and all recorded data during transitions between test runs
discrete data files for each flow rate ramp test that can be referenced to the continuous data file
discrete data files for each steady-flow hold point during a test run that can be referenced to the continuous data file Data files include the record of vibration, dynamic pressure, flow rate, temperature, plenum static pressure, and differential pressure across the flow restrictor. A high resolution in temperature data is not required so the temperature data recording frequency may be decreased from the DAS sampling rate, though not below (( }}2(a),(c) Hz.

Pump operating speed is recorded for the tests to allow for determination of blade passing frequency (for a centrifugal pump) or pulsation frequency (positive displacement pump). Pump operating speed is recorded as a parameter at the same data acquisition frequency as flow restrictor vibration. This data is necessary to allow determination of any correlation between observed FIV and pump-generated pressure waves. © Copyright 2018 by NuScale Power, LLC 233

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 5.3.8 Test Acceptance Criteria Test steps from the test plan and procedures are performed as written; any deviations from test plan and procedures are reviewed and entered into the test log. A final test report is developed to summarize the testing activities and results. The content includes the following, at a minimum.

description of the testing infrastructure, such as drawings, descriptions, and photographs of the test specimens and method of mounting schematics and photographs of the test facility instrumentation diagrams details of the DAS and instrumentation dates of the testing identification of tester or data recorder
discussion of testing methodology
actions taken in connection with any deviations
types of observations collected, for example strain displacement pressure drop wear inspection results
test results and results evaluations data files data postprocessing (extent to be determined in the test specification) identification of personnel evaluating test results

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 6.0 Initial Startup Measurement Testing Design work is underway to identify the optimal measurement plan to detect unexpected, large amplitude FIV during the initial startup test phase of the NPM. These measurements supplement the scope of the detailed validation measurement program, discussed in other sections of this technical report, by confirming the lack of large amplitude vibration in the prototype NPM. During initial startup testing, the nuclear reactor is critical and the primary and secondary fluid systems in the NPM are at normal operating pressure, temperature and flow conditions. There are three specific areas of interest in the NPM for detecting vibration during initial startup testing: the connection between the upper and lower riser assemblies, the ICIGTs and CRD shafts, and the SG assembly. Instrumentation that would be capable of detecting and identifying vibration in adjacent components is also desirable. If any sensors are recommended to be located inside a pressure boundary, they are inaccessible during operation and must be designed to function reliably throughout the entirety of the initial startup testing program. The temporary sensors must have an operational design life no less than one refueling cycle, at which time they may be removed. Minimizing major modifications to the NPM design to accommodate temporary sensors is desirable. Maximizing the components and FIV phenomena that each sensor can detect is desirable. Future revision to this technical report will include

optimal sensor type and installation details for each NPM component to be measured.
testing plans and considerations, including instrument calibration and on-line signal processing capabilities with suggested sensors.
recommended instrumentation installation and removal plan, detailing any required NPM modifications.
discussion of similar uses in industry or the need for evaluation and testing to confirm adequacy of measurement system design before deployment in the NPM.

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 7.0 Inspection Program This section identifies the prototype components that require inspection before and after the CVAP measurement program. because the measurement program focuses on the limiting components, inspection is used to confirm the assumptions regarding which components are limiting. For the components that are instrumented to support the measurement program, inspection provides a secondary confirmation of the FIV performance and integrity of these structures. Before and after initial startup testing, components are inspected for mechanical wear and signs of vibration induced damage. Initial startup testing provides a sufficient duration for the limiting NPM component to experience a minimum of one million cycles of vibration. Components that are evaluated in the analysis program undergo inspection. For the components validated in the measurement program via testing, the inspection provides a secondary confirmation of the FIV integrity of the NPM components. For components that do not require testing due to large safety margins, the inspection confirms that the testing performed on more limiting components sufficiently bounds the performance of the non-tested components. 7.1 Inspection Methodology The components most susceptible to FIV are examined in limiting and representative locations to demonstrate acceptable performance. Inspection areas include: a) Major load-bearing elements of the reactor vessel internals that position the core support structure b) Lateral, vertical, and torsional restraints inside the RPV c) Locking and bolting components whose failure could impact reactor vessel internals integrity d) Contact surfaces and potential contact surfaces e) Critical locations identified by the analysis program f) RPV interior for loose parts or foreign material Components may be removed and inspected outside of the pressure vessel, but many NPM components cannot be removed from their installed locations. For those components, or when practical, an in-situ inspection is performed. Components like the SG tubes and SG tube supports that are too long to examine their entire surface and have inaccessible areas are inspected at least at the accessible ends of their length. Initial startup testing provides for 1 million cycles of the most limiting (lowest fundamental frequency) component. This testing duration provides a reasonable number of cycles so that if rapid degradation is occurring due to FIV, there is evidence detectable by inspection. © Copyright 2018 by NuScale Power, LLC 236

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 7.2 Inspection Procedure The NPM components are inspected following the guidelines and requirements provided in ASME Section III (Reference 9.1.6), Paragraph NG-5111, Paragraph NB-5111 and using the methods defined in the ASME Section V (Reference 9.1.7), Article 9. The visual inspections are performed using VT-1 and VT-3, as defined by ASME Section XI, Subarticle IWB-2500, Tables IWB-2500-1 B-N-1, B-N-2, and B-N-3 (Reference 9.1.8). These nondestructive surface examinations are used to inspect the surfaces and welds of the components identified for inspection. Visual examinations are performed on the NPM components to satisfy the following objectives:

On critical surfaces to see if there are any cracks, defects, or abnormal distortion
On welds to see evidence of cracks
On interface surfaces to see evidence of wear, distress, or abnormal corrosion
On fittings to see if they are tight
At reasonable locations to see if loose parts or debris have collected The inspection results are documented in the CVAP Measurement and Inspection Program Results report. Any inspection findings and repairs/modifications are documented along with a complete record of the pre- and post- initial startup testing inspections including notes, photographs, and video.

7.3 Pre- and Post-Initial Startup Testing Inspection The inspection and documentation for the NPM components are completed in two stages. The baseline inspection stage (pre-initial startup testing) takes place as the NPM components are assembled. The post-initial startup testing inspection stage takes place after the completion of the initial startup testing. During post-initial startup testing inspection, the core support structure and lower riser assembly are examined in the pool while other internals are examined in the dry dock. The post-initial startup testing inspection results are compared with the baseline inspection data. The comparison provides an independent method of corroborating the conclusions of the CVAP analysis program, that no severe FIV related degradation is occurring. The CVAP inspection locations are listed in Table 7-1 and depicted in Figure 7-1, Figure 7-2, Figure 7-3, and Figure 7-4. These locations include all inspection elements required to cover the six inspection areas listed in Section 7.1. The inspection examination methods defined in Table 7-1 are based on and consistent with the methods specified for in-service inspections of the NPM to meet ASME Code Section XI requirements. VT-1 inspections are specified for welded core support structures, attachments to the RPV, or identified areas of low margin. VT-3 inspections are specified for the majority of the remaining features except for locations that are mainly inspected for loose parts using a general visual exam. © Copyright 2018 by NuScale Power, LLC 237

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Table 7-1 Pre- and post-initial startup testing inspection locations Exam. Inspection Location Feature to be Inspected Method Req. Category ID with Notes 4 (Section 7.1) 8 Core Supports and Flow Diverter Core Support Block Gussets to RPV Bottom Head 1 VT-1 1 a, b Welds 2 Core Support Block Exterior Surfaces VT-3 1, 2 a, b, c 3 Lower Core Plate Surfaces VT-3 a, b, c, d 4 Lower Core Plate to Core Barrel Weld VT-1 1 a, b General 5 Reflector Blocks f Visual 5 6 Core Barrel Exterior Surface VT-3 6 a 7 Upper Support Block Weld and Fittings VT-1 1, 2 a, b, c, d 8 Core Barrel to Upper Core Plate Interface VT-3 a, b, d 9 Shared Fuel Pins VT-3 3 d General 10 Flow Diverter f Visual Lower Riser 11 Upper Core Plate to Lower Riser Section Weld VT-3 1 a, b 12 Upper Core Plate Surfaces VT-3 2, 5 a, b, c, d, f 13 Lower Riser Section Surfaces VT-3 5, 6 a, b 14 Lower Riser Spacer Surfaces VT-3 a, b 15 Lower Riser Transition Surfaces VT-3 a, b 16 ICIGT Flag to Upper Core Plate Welds VT-1 1 f 17 Fuel Pin VT-1 3 d 18 CRA Lower Flange Surfaces VT-3 b, c 19 CRAGT Interior and Exterior Surfaces VT-3 b 20 CRA Card to CRA Rodlet Interface VT-3 3 d 21 CRD shaft Alignment Cone to CRD shaft Interface VT-3 3 d CRD shaft Alignment Cone to CRAGT Support Plate 22 VT-3 b, d Interface Upper Riser and Pressurizer Spray Nozzle 23 Upper Riser Transition Surfaces VT-3 6 b, d 24 Upper Riser Bellows VT-3 b 25 Upper Riser Section Surfaces VT-3 6 b 26 Injection Line Pipe VT-3 - 27 CRD shaft Support Surfaces VT-3 b 28 CRD shaft Supports to CRDS Interface VT-3 3 d 29 CRD shaft Supports to ICIGT Interface VT-3 3 d 30 Upper Riser Hanger Brace Surfaces VT-3 b 31 CRD shaft Sleeve Surfaces VT-3 - 32 Upper Riser Hanger Ring Surfaces VT-3 2 b, c 33 Hot Temperature Thermowell External Surfaces VT-3 - 34 Pressurizer Spray Nozzle Surfaces VT-3 1 - SG and Downcomer 35 SG Inlet Flow Restrictors VT-3 3, 7 c, e, f 36 SG Inlet Flow Restrictor to SG Tube Interface VT-3 3, 7 d, e 37 SG Flow Restrictor Mounting Plate VT-3 2 f 38 SG Lower Tube Support Cantilever Surfaces VT-3 b, d © Copyright 2018 by NuScale Power, LLC 238

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Exam. Inspection Location Feature to be Inspected Method Req. Category ID with Notes 4 (Section 7.1) 8 39 SG Tube to Tube Support Interface VT-3 3, 6 b, d, e 40 Tube Support to Upper Riser Section Interface VT-3 6 b, d 41 Injection Line Pipe Surfaces VT-3 - 42 Cold Temperature Thermowells External Surfaces VT-3 - 43 RRV Nozzles VT-3 - Secondary Side Components 44 Steam Plenum VT-3 - 45 Steam Plenum Nozzle VT-3 - 46 SGS Piping VT-3 6 - 47 Steam Temperature Thermowells, External Surface VT-3 - 48 MSIVs, Interior Surfaces VT-3 5 e 49 DHRS Steam Piping, Actuation Valve to Steam Line Tee VT-1 3 e 50 DHRS Condensate Piping Inside Containment VT-1 - Notes:

1) Visually examine welds

2) Verify that fittings are tight

3) Visually examine for evidence of vibration wear

4) Visual examinations include checking for loose parts

5) Inspection limited to accessible surfaces exposed while assembled

6) Inspection limited to the accessible ends of the feature due to the large surface area

7) Inspection limited to a sampling of components due to the large quantity

8) Rows with a - indicate that the feature to be inspected does not fall within one of the six categories identified in Section 3.0

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 8.0 Summary and Conclusions This report provides the details of the NuScale CVAP measurement and inspection program. This program consists of benchmark testing and analysis, validation analysis and testing, an instrumentation plan to detect large amplitude vibration during initial startup testing, and inspection of components screened as susceptible to FIV before and after initial startup testing. Following the completion of each test, post-test analysis is performed to complete the validation effort. Assessments are also performed based on the initial startup testing and inspection observations. Combined with the benchmarking efforts, the measurement and inspection work scope validate the FIV screening and predictive analyses in Reference 9.1.4. © Copyright 2018 by NuScale Power, LLC 244

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 9.0 References 9.1 Referenced Documents 9.1.1 American Society of Mechanical Engineers, Operation and Maintenance of Nuclear Power Plants, Division 3: OM Guides, ASME OM-2012, Part 11, Vibration Testing and Assessment of Heat Exchangers, New York, NY. 9.1.2 American Society of Mechanical Engineers, Standard for Verification and Validation in Computational Fluid Dynamics and Heat Transfer, ASME V&V 20-2009, New York, NY. 9.1.3 Au-Yang, M.K., Flow-Induced Vibration of Power and Process Plant Components, A Practical Workbook, ASME Press, New York, NY, 2001. 9.1.4 NuScale Comprehensive Vibration Assessment Program Technical Report, TR-0716-50439, Rev. 1. 9.1.5 U.S. Nuclear Regulatory Commission, Comprehensive Vibration Assessment Program for Reactor Internals during Preoperational and Initial Startup Testing, Regulatory Guide 1.20, Revision 3, March 2007. 9.1.6 American Society of Mechanical Engineers, Boiler and Pressure Vessel Code, 2013 Edition, Section III, Rules for Construction of Nuclear Facility Components, New York, NY. 9.1.7 American Society of Mechanical Engineers, Boiler and Pressure Vessel Code, 2013 Edition, Section V, Nondestructive Examination, New York, NY. 9.1.8 American Society of Mechanical Engineers, Boiler and Pressure Vessel Code, 2013 Edition, Rules for Inservice Inspection of Nuclear Power Plant Components, New York, NY. 9.1.9 Ziada, S. and Shine, S., Shrouhal Number of Flow-Excited Acoustic Resonance of Closed Side Branches, Journal of Fluids and Structures, Volume 13 (1999), pg. 127-142. 9.1.10 Schardt, J.F., Flow-Induced Vibration Characteristics of BWR/6-238 Jet Pumps, GEAP-22201, UC-78, General Electric Company, September 1982. © Copyright 2018 by NuScale Power, LLC 245

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Steam Plenum <<< ---------------------------------------- <<< ---------------------------------------- <<< Span IDs <<< ---------------------------------------- <<< ---------------------------------------- <<< Feed Plenum 01 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Accelerometer IDs 01 02 03 04 05 06 07 08 09 10 Accelerometer IDs Inst-#1: Col-11, Inst-#1: Col-11, Plenum-4, Tube-1 Plenum-4, Tube-1 02 04 N3 06 N1 08 Strain Gage IDs Strain Gage IDs 01 03 05 07 Accelerometer IDs 11 12 13 14 15 16 17 18 19 20 Accelerometer IDs Inst-#2: Col-11, Inst-#1: Col-11, Plenum-2, Tube-16 Plenum-4, Tube-1 N4 N2 10 11 13 15 Strain Gage IDs Strain Gage IDs 09 12 14 16 Accelerometer IDs 21 22 23 24 25 26 27 28 29 30 Accelerometer IDs Inst-#3: Col-9, Inst-#3: Col-9, Plenum-1, Tube-15 Plenum-1, Tube-15 Strain Gage IDs Strain Gage IDs Accelerometer IDs 31 32 33 34 35 36 37 38 39 40 Accelerometer IDs Inst-#4: Col-9, Inst-#4: Col-9, Plenum-1, Tube-16 Plenum-1, Tube-16 Strain Gage IDs Strain Gage IDs Accelerometer IDs 41 42 43 44 45 46 47 48 49 50 Accelerometer IDs Inst-#5: Col-12, Inst-#5: Col-12, Plenum-3, Tube-1 Plenum-3, Tube-1 Strain Gage IDs Strain Gage IDs Accelerometer IDs 51 52 53 54 55 56 57 58 59 60 Accelerometer IDs Inst-#6: Col-12, Inst-#6: Col-12, Plenum-3, Tube-2 Plenum-3, Tube-2 Strain Gage IDs Strain Gage IDs Accelerometer IDs Accelerometer IDs Inst-#7: Col-11, Inst-#7: Col-11, Plenum-4, Tube-2 Plenum-4, Tube-2 18 20 22 24 Strain Gage IDs Strain Gage IDs 17 19 21 23 Accelerometer IDs Accelerometer IDs Inst-#8: Col-11, Inst-#8: Col-11, Plenum-2, Tube-15 Plenum-2, Tube-15 26 28 30 32 Strain Gage IDs Strain Gage IDs 25 27 29 31 01 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Steam Plenum <<< ---------------------------------------- <<< ---------------------------------------- <<< Span IDs <<< ---------------------------------------- <<< ---------------------------------------- <<< Feed Plenum Figure A-9 Instrumentation summary © Copyright 2018 by NuScale Power, LLC 254

Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix B. TF-2 FEI Spectral Plots by Test Series (0 - 300 Hz) © Copyright 2018 by NuScale Power, LLC 255

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix C. TF-2 FEI Spectral Plots by Flow Rate (0 - 300 Hz) © Copyright 2018 by NuScale Power, LLC 266

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix D. TF-2 FEI Spectral Plots by Test Series (0 - 1000 Hz) © Copyright 2018 by NuScale Power, LLC 279

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix E. TF-2 FEI Spectral Plots by Flow Rate (0 - 1000 Hz) © Copyright 2018 by NuScale Power, LLC 290

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix F. TF-2 FEI Content within Frequency Ranges of Interest © Copyright 2018 by NuScale Power, LLC 303

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix G. TF-2 FEI Frequency-Specific Amplitudes versus Flow Rate © Copyright 2018 by NuScale Power, LLC 311

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Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report TR-0918-60894-NP Rev. 0 Appendix H. TF-3 Build-out Testing Frequency Response Function Calculations © Copyright 2018 by NuScale Power, LLC 318

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LO-1218-63700 : Affidavit of Thomas A. Bergman, AF-1218-60894 NuScale Power, LLC 1100 NE Circle Blvd., Suite 200 Corvallis, Oregon 97330 Office 541.360-0500 Fax 541.207.3928 www.nuscalepower.com

NuScale Power, LLC AFFIDAVIT of Thomas A. Bergman I, Thomas A. Bergman, state as follows: (1) I am the Vice President of Regulatory Affairs of NuScale Power, LLC (NuScale), and as such, I have been specifically delegated the function of reviewing the information described in this Affidavit that NuScale seeks to have withheld from public disclosure, and am authorized to apply for its withholding on behalf of NuScale (2) I am knowledgeable of the criteria and procedures used by NuScale in designating information as a trade secret, privileged, or as confidential commercial or financial information. This request to withhold information from public disclosure is driven by one or more of the following: (a) The information requested to be withheld reveals distinguishing aspects of a process (or component, structure, tool, method, etc.) whose use by NuScale competitors, without a license from NuScale, would constitute a competitive economic disadvantage to NuScale. (b) The information requested to be withheld consists of supporting data, including test data, relative to a process (or component, structure, tool, method, etc.), and the application of the data secures a competitive economic advantage, as described more fully in paragraph 3 of this Affidavit. (c) Use by a competitor of the information requested to be withheld would reduce the competitors expenditure of resources, or improve its competitive position, in the design, manufacture, shipment, installation, assurance of quality, or licensing of a similar product. (d) The information requested to be withheld reveals cost or price information, production capabilities, budget levels, or commercial strategies of NuScale. (e) The information requested to be withheld consists of patentable ideas. (3) Public disclosure of the information sought to be withheld is likely to cause substantial harm to NuScales competitive position and foreclose or reduce the availability of profit-making opportunities. The accompanying report reveals distinguishing aspects about the methodology by which NuScale develops its CVAP Measurement and Inspection Plans. NuScale has performed significant research and evaluation to develop a basis for this CVAP Measurement and Inspection Plans technical report and has invested significant resources, including the expenditure of a considerable sum of money. The precise financial value of the information is difficult to quantify, but it is a key element of the design basis for a NuScale plant and, therefore, has substantial value to NuScale. If the information were disclosed to the public, NuScale's competitors would have access to the information without purchasing the right to use it or having been required to undertake a similar expenditure of resources. Such disclosure would constitute a misappropriation of NuScale's intellectual property, and would deprive NuScale of the opportunity to exercise its competitive advantage to seek an adequate return on its investment. (4) The information sought to be withheld is in the enclosed report entitled NuScale Comprehensive Vibration Assessment Program Measurement and Inspection Plan Technical Report. The enclosure contains the designation Proprietary" at the top of each page containing proprietary information. The information considered by NuScale to be proprietary is identified within double braces, "(( }}" in the document. AF-1218-63701 Page 1 of 2

(5) The basis for proposing that the information be withheld is that NuScale treats the information as a trade secret, privileged , or as confidential commercial or financial information. NuScale relies upon the exemption from disclosure set forth in the Freedom of Information Act ("FOIA"), 5 USC § 552(b)(4), as well as exemptions applicable to the NRC under 10 CFR §§ 2.390(a)(4) and 9.17(a)(4 ). (6) Pursuant to the provIsIons set forth in 10 CFR § 2.390(b)(4), the following is provided for consideration by the Commission in determining whether the information sought to be withheld from public disclosure should be withheld: (a) The information sought to be withheld is owned and has been held in confidence by NuScale. (b) The information is of a sort customarily held in confidence by NuScale and , to the best of my knowledge and belief, consistently has been held in confidence by NuScale. The procedure for approval of external release of such information typically requires review by the staff manager, project manager, chief technology officer or other equivalent authority, or the manager of the cognizant marketing function (or his delegate), for technical content, competitive effect, and determination of the accuracy of the proprietary designation. Disclosures outside NuScale are limited to regulatory bodies, customers and potential customers and their agents, suppliers, licensees, and others with a legitimate need for the information, and then only in accordance with appropriate regulatory provisions or contractual agreements to maintain confidentiality. (c) The information is being transmitted to and received by the NRC in confidence. (d) No public disclosure of the information has been made, and it is not available in public sources. All disclosures to third parties, including any required transmittals to NRC, have been made, or must be made, pursuant to regulatory provisions or contractual agreements that provide for maintenance of the information in confidence. (e) Public disclosure of the information is likely to cause substantial harm to the competitive position of NuScale, taking into account the value of the information to NuScale, the amount of effort and money expended by NuScale in developing the information, and the difficulty others would have in acquiring or duplicating the information. The information sought to be withheld is part of NuScale's technology that provides NuScale with a competitive advantage over other firms in the industry. NuScale has invested significant human and financial capital in developing this technology and NuScale believes it would be difficult for others to duplicate the technology without access to the information sought to be withheld. I declare under penalty of perjury that the foregoing is true and correct. Executed on December 7, 2018. AF-1218-63701 Page 2 of 2}}

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