ML093360328
| ML093360328 | |
| Person / Time | |
|---|---|
| Site: | Davis Besse  |
| Issue date: | 05/23/2009 |
| From: | Hiremagalur J, Rodamaker S FirstEnergy Nuclear Operating Co, Structural Integrity Associates |
| To: | Office of Nuclear Reactor Regulation |
| References | |
| L-09-268, TAC ME0477, TAC ME0478 0800368.323, Rev. 1 | |
| Download: ML093360328 (31) | |
Text
Structural Integrity Associates, Inc.
File No.: 0800368.323 CALCULATION PACKAGE ProjectNo.: 0800368 Quality Program: N Nuclear E" Commercial PROJECT NAME:
Davis Besse Phase 2 Alloy 600 CONTRACT NO.:
49151 Rev. 1 CLIENT:
PLANT:
Welding Services Inc. (WSI)
Davis-Besse Nuclear Power Station, Unit 1 CALCULATION TITLE:
Thermal and Unit Mechanical Stress Analyses for Reactor Coolant Pump Discharge Nozzle with Weld Overlay Repair Document Affected Project Manager Preparer(s) &
Revision Pages Revision Descriptlon Approval Checker(s)
Signature & Date Signatures & Date 0
1-29 Initial Issue A A-2 Computer Files Z 41 Richard Bax Scott Rodamaker RLB 05/28/09 SCR 05/28/09 Jagannath Hiremagalur JH 05/28/09 Page 1 of 29 F0306-01RO
Structural Integrity Associates, Inc.
Table of Contents 1.0 OBJECTIV E.........................................................................................................
4 2.0 A SSUM PTION S......................................................................................................
4 3.0 DESIGN INPUT......................................................................................................
4 3.1 Finite Elem ent M odels..................................................................................
4 3.2 M aterial Properties.........................................................................................
5 3.3 Therm al Transient D efinitions......................................................................
5 4.0 M ETHODOLOGY....................................................................................................
5 5.0 ANALY SIS....................................................................................................................
6 5.1 Therm al Transient Definitions.......... %
6 5.1.1 Thermal Analyses...........................................................................................
6 5.1.2 Thermal Stress Analyses...............................................................................
6 5.2 M echanical Stress Analyses..........................................................................
6 5.2.1 Internal Pressure...........................................................................................
6 5.2.2 In-Plane M oment...........................................................................................
8 5.2.3 Out-of-Plane M oment....................................................................................
8 5.2.4 Axial Force....................................................................................................
8 6.0 RESULTS......................................................................................................................
9 7.0 CON CLU SION S......................................................................................................
9 8.0 REFEREN CES........................................................................................................
10 APPENDIX A AN ALY SIS COM PUTER FILES..........................................................
A-1 List of Tables Table 1: Bounding Transients for Analysis............................................................................
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List of Figures Figure 1. Finite Element Model of the RCP Discharge Nozzle with Minimum "Optim ized" W eld Overlay Repair....................................................................
12 Figure 2. Finite Element Model of the RCP Discharge Nozzle with Maximum "Full Structural" W eld Overlay Repair......................................................................
13 Figure 3. Applied Boundary Conditions and Pressure Loading for Unit Pressure Analysis.. 14 Figure 4. Applied Boundary Conditions and Loading for Unit In-Plane Moment Analysis.. 15 Figure 5. Applied Boundary Conditions and Loading for Unit Out-of-Plane Moment A n aly sis........ I........................................................................................................
16 Figure 6. Applied Boundary Conditions and Loading for Unit Axial Force Analysis.....
17 Figure 7. Applied Heat Transfer Coefficients for Thermal Transient Analyses (Thermal P a ss).......................................................................................................................
1 8 Figure 8. Applied Boundary Conditions for Thermal Transient Analyses (Stress Pass)....... 19 Figure 9. Stress Path Definitions for Maximum Weld Overlay used for Thermal Transient Analyses for Later ASME Code Evaluations...................................
20 Figure 10. Stress Path Definitions for Minimum Weld Overlay used for Unit Pressure, Unit Axial and Unit Moment (In-Plane/Out-of Plane) Analyses for Later A SM E Code Evaluations.................................................................................
21 Figure 11. Stress Path Definitions for Maximum Weld Overlay used for Thermal Transient Analyses for Later Crack Growth Evaluations.................................
22 Figure 12. Stress Path Definitions for Minimum Weld Overlay used for Unit Pressure, Unit Axial and Unit Moment (In-Plane/Out-of Plane) Analyses for Later Crack Growth Evaluations...............................................................................
23 Figure 13. Stress Intensity Contour Plot for 1000 psi Internal Pressure...........................
24 Figure 14. Stress Intensity Contour Plot for 1000 lb Axial Force.....................................
25 Figure 15. Stress Intensity Contour Plot for 1000 in-lb In-Plane Moment Load.............. 26 Figure 16. Stress Intensity Contour Plot for 1000 in-lb Out-of-Plane Moment Load.....
27 Figure 17. Temperature Plot for Heatup Transient (Time = 17532 seconds).................... 28 Figure 18. Intensity Contour Plot for Heatup Transient (Time = 17532 seconds)............ 29 File No.: 0800368.323 Page 3 of 29 Revision: 0 F0306-011
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1.0 OBJECTIVE The objective of this calculation is to perform stress analyses due to applicable thermal transients and unit mechanical loads on the reactor coolant pump (RCP) discharge nozzle weld overlay repair at Davis-Besse Nuclear Power Station. The geometry, including the weld overlay, is generated in a separate finite element model development calculation [1].
Several stress paths are defined through the location of the weld overlay repair. The stresses extracted along these paths are stored in computer files and will be used in separate ASME Code,Section III qualification and fatigue crack growth evaluations.
2.0 ASSUMPTIONS o For the thermal transients and internal pressure analyses, plane strain conditions are assumed at the cold leg piping free ends to simulate the connected piping.
o For all thermal and mechanical load cases, plane strain conditions are assumed at the free end of the cold leg spray nozzle to simulate the connected piping.
" For all thermal and mechanical load cases, axial and rotational constraints are applied at the free end of the pump body. This provides a rigid pump body, while still allowing proper thermal expansion at the free end.
o The stress free reference temperature for the thermal strain calculation is assumed to be 70'F.
o The exterior surfaces of the cold leg piping, RCP discharge nozzle and pump body are assumed to be perfectly insulated [2].
o Bulk fluid temperatures and heat transfer coefficients are applied to all interior surfaces with the exception of the pressure tap nozzle which is assumed to be capped and therefore has no significant circulation.
o Due to model symmetry, a duplicate cold leg spray nozzle is created in the out-of-plane moment model, but as no boundary conditions nor stress paths are local to this area the effects are deemed negligible.
3.0 DESIGN INPUT 3.1 Finite Element Models Two three-dimensional finite element models were developed for operating stress analyses in a previous calculation package [1] using the ANSYS finite element software package [3]. One model was developed using minimum "optimized" weld overlay dimensions (to be used for mechanical loading analyses), and another was developed using maximum "full structural" weld overlay dimensions (to be used for thermal transient analyses). Using the minimum "optimized" weld overlay configuration for mechanical loading, and using the maximum "full structural" weld overlay configuration for thermal transient analyses, is expected to yield conservative stress results.
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The models include the reactor coolant pump discharge nozzle, the nozzle-to-safe end weld, the safe end, the safe end-to-piping weld and weld butter, a postulated ID weld repair (2-D residual minimum optimized weld overlay dimension model only), a portion of attached cold leg piping (elbow) and pipe internal cladding, the stainless steel buffer layer, the cold leg spray nozzle, the pressure tap nozzle and associated weld, and the weld overlay repair, as shown in Figures 1 and 2. Additional details regarding the development of these models are provided in Reference 1.
The finite element models are constructed using the 8, 10, and 20-node elements, SOLID45, SOLID92, and SOLID95, respectively. These elements are converted to thermal solid elements (SOLID70, SOLID87, and SOLID90, respectively) for the thermal transient analyses to determine the resulting temperature distribution time histories. The structural solid elements are then used to calculate the stresses due to the thermal loads, as well as the mechanical loading stresses. Additional details regarding the development of these models are provided in Reference 1.
3.2 Material Properties The material properties are included in the Reference 1 model creation process, and are left unchanged for the analyses performed herein.
3.3 Thermal Transient Definitions A total of six thermal transients are evaluated based on Table 5 of Reference 2. The temperatures for these transients are shown in Table 1. The Hydrostatic Test is not evaluated as a transient but as two steady-state conditions.
4.0 METHODOLOGY The finite element models developed in Reference 1 are used to analyze the mechanidal loading and the thermal transients shown in Table 1 using the ANSYS finite element software [3]. The unit mechanical loading includes internal pressure, axial loading, and in-plane and out-of-plane moment loading. The resulting stresses are then scaled in later ASME Code,Section III and crack growth analyses using the actual load magnitudes.
For conservatism, the finite element model with the minimum "optimized" overlay dimensions was used to perform stress analyses of unit mechanical loadings (unit pressure, unit axial and unit in-plane and out-of-plane moments); the finite element model with the maximum "full structural" overlay dimensions was used to perform thermal transient analyses.
In support of future ASME Code,Section III stress and fatigue evaluations, several through-wall stress paths are defined through the RCP Discharge nozzle weld overlay repair region and linearized stresses are extracted along these paths. Several additional paths are defined to support future fatigue crack growth analyses, and mapped (hoop and axial) stresses are extracted along these paths. Stresses for mechanical loading analyses are extracted from the model with the minimum "optimized" weld overlay File No.: 0800368.323 Page 5 of 29 Revision: 0 F0306-011
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dimensions; stresses for thermal analyses are extracted from the model with the maximum "full structural" weld overlay dimensions. The stress results are stored in computer files for usage in future calculations, which will address ASME Code,Section III and crack growth evaluations.
5.0 ANALYSIS Four separate mechanical loading analysis and five separate thermal transients stress analyses are performed as described in the following sections. The Hydrostatic Test is not evaluated as a transient but as two steady-state thermal conditions.
5.1 Thermal Transient Definitions 5.1.1 Thermal Analyses Appropriate bulk fluid temperatures and heat transfer coefficients are applied to the interior nodes of the cold leg pipe and RCP Discharge nozzle as specified in Reference 2 and shown in Table 1 herein. No heat transfer coefficients are applied to the outside surfaces of the cold leg pipe and RCP Discharge nozzle since the surfaces are assumed to be perfectly insulated. The heat transfer film coefficients that are applied to the interior nodes are depicted in Figure 7 and are applicable for all transients. An additional time of one hour is appended to the end of each transient to ensure that any lagging peak stresses are captured.
5.1.2 Thermal Stress Analyses Axial and rotational constraints are applied at the free end of the pump body and symmetry boundary conditions along the half model planes of symmetry. The axial free end of the cold leg piping (elbow) and the cold leg spray nozzle are coupled in their respective axial directions. The boundary conditions for the thermal stress analyses are shown in Figure 8. By coupling the nodes in the axial displacement direction at the cold leg, no resulting moment is generated. The coupled boundaries allow axial thermal expansion while simulating the un-modeled attached piping's resistance to overturning moments.
5.2 Mechanical Stress Analyses 5.2.1 Internal Pressure A unit internal pressure of 1,000 psi is applied to the interior surfaces of the model. An end-cap load is applied to the free end of the attached cold leg piping (the elbow), the spray nozzle and the pressure tap in the form of a tensile axial pressure, the values of which are calculated below. These end-cap loads are included to simulate axial line loads induced by pressure at bends and transmitted through the un-modeled piping systems. The ANSYS program assumes that a positive value for pressure results in a load applied into the surface of the structure. In order to generate "traction" or a load away from the surface of the structure, it is necessary to apply the pressure with a negative value. Therefore, the end-File No.: 0800368.323 Page 6 of 29 Revision: 0 F0306-0o
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cap loads calculated below will be applied in ANSYS using the negative of the calculated values. The applied pressures are shown in Figure 3.
Axial and rotational constraints are applied at the free end of the pump body and symmetry boundary conditions along the half model planes of symmetry. The axial free end of the cold leg piping (elbow),
the pressure tap and cold leg spray nozzle are coupled in their respective axial direction. The boundary conditions for the unit pressure analysis are shown in Figure 3.
P. ri~id&2 1000-14.02
- 1898p end-cap-l=
routside 2 _rinside2 17.32 _14.02 9
- where, Pend-cap-cl
= End cap pressure on cold leg piping elbow free end (psi)
P
= Internal pressure (psi) rinside
= Inside radius of modeled cold leg pipe elbow (in) [1]
routside
= Outside radius of modeled cold leg pipe elbow (in) [1]
kend-cap-sp P*rinside2 1000"1.0625 2 220 psi
-sroutside2_
riide 2.52 - 1.06252
- where, Pend-cap-sp
= End cap pressure on cold leg spray nozzle free end (psi)
P
= Internal pressure (psi) rinside
= Inside radius of cold leg spray nozzle (in) [1]
routside
= Outside radius of cold leg spray nozzle (in) [1]
P. rinside2 1000.0.3062 Kend-cap-ptap 2
2=2)36ps (routside
-rinside2 (0.593752 -0.3062
=362
- where, Pend-cap-ptap
= End cap pressure on pressure tap free end (psi)
P
= Internal pressure (psi) rinside
= Inside radius of pressure tap (in) [1]
routside
= Outside radius of pressure tap (in) [1]
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5.2.2 In-Plane Moment The 1800 finite element model is used to evaluate the in-plane moment loading. The finite element model can be seen in Figure 4 with the applied boundary conditions and load. Axial and rotational constraints are applied at the free ends of the pump body and symmetry boundary conditions along the half model planes of symmetry. The free end of the cold leg spray nozzle is coupled in its axial direction.
An in-plane unit moment of 1000 in-lb is applied about the positive local Cartesian (coordinate system
- 54) Z-axis (for a half model, a 500 in-lb moment is actually applied). The moment is applied to the free end of the attached cold leg piping (elbow) by making use of a pilot node to transfer the loading. The TARGE 170 target element type from the ANSYS element library is used to create the pilot node. The CONTA174 contact element type is used to create a contact surface at the free end of the elbow. The pilot node and surface are bonded together, so that the moment applied to the pilot node is transferred to the free end of the elbow.
5.2.3 Out-of-Plane Moment A modified, full 3600 finite element model is used to evaluate the out-of-plane moment loading. The finite element model can be seen in Figure 5 with the applied boundary conditions and load. Due to model symmetry a duplicate cold leg spray nozzle is created, but as no boundary conditions nor stress paths are local to this area the effects are deemed negligible. Axial and rotational constraints are applied at the free ends of the pump body. The free end of the original cold leg spray nozzle is coupled in its axial direction. The fictitious second spray nozzle (resulting from the reflection of the half-model) is not coupled as there is no piping present. An out-of-plane unit moment of 1000 in-lb is applied about a local negative Cartesian (coordinate system 54) X-axis. The moment is applied to the free end of the attached cold leg piping (elbow) by making use of a pilot node to transfer the loading. The TARGE 170 target element type from the ANSYS element library is used to create the pilot node. The CONTA 174 contact element type is used to create a contact surface at the free end of the elbow. The pilot node and surface are bonded together, so that the moment applied to the pilot node is transferred to the free end of the elbow.
5.2.4 Axial Force An axial force of 500 lbs is applied in the positive Global-X direction to the half model (thereby generating 1000 lbs of equivalent loading for the full structure) at the free end of the attached cold leg piping (elbow) to simulate axial loads acting on the RCP Discharge nozzle/weld overlay. An opposing moment is then applied about the postive Global-Z direction to counteract the induced moment associated with the application of the force at the free end of the attached cold leg piping elbow. The opposing moment is determined as follows.
Mcounter = Faxial
- Lpipe = 500 lbs
- 9.78 inches = 4888.5 in-lb where:
Mcounter =
Counter moment, in-lb Faxial
= Applied axial force, 500 lbs Lpipe
= Perpendicular distance from application of force to nozzle centerline, 9.78 inches [1]
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The addition of the counter moment is necessary, as the resulting stresses need to be the result of a pure axial loading. Because of the elbow's proximity to the weld overlay, the only reasonable application point for the axial load is the free end of the elbow. The axial load produces an undesired moment addition which needs to be countered.
The axial force is applied as a distributed nodal force to the end-section of the attached cold leg piping.
The opposing moment is applied to the free end of the attached cold leg piping (elbow) by making use of a pilot node to transfer the loading. The TARGE 170 target element type from the ANSYS element library is used to create the pilot node. The CONTA174 contact element type is used to create a contact surface at the free end of the elbow. The pilot node and surface are bonded together, so that the moment applied to the pilot node is transferred to the free end of the elbow. Axial and rotational constraints are applied at the free end of the pump body and symmetry boundary conditions along the planes of symmetry. The free end of the cold leg spray nozzle is coupled in its axial direction. The boundary conditions and loads for the unit axial force analysis are shown in Figure 6.
6.0 RESULTS Stress paths are defined around the region of the weld overlay repair. Stresses are linearized along Paths 1 through 6 for all time steps in the analyses (unit loads and thermal transient loads) and the results are saved to an Excel Workbook format for later ASME Code,Section III evaluations. The linearized stress paths are shown in Figures 9 and 10. The axial and hoop stresses are mapped along Paths 7 through 15 to support crack growth calculations for all time steps in the analyses (unit loads and thermal transient loads) and output to *.OUT files. The crack growth paths are shown in Figure 11 and 12. All of the files are included with the project computer files (see Appendix A for file listings).
Representative total stress intensity contour plots are provided in Figures 13 through 16 for the mechanical loading analyses. The temperature and stress intensity contour plots for the Heatup transient at 17532 seconds, as an example, are shown in Figures 17 and 18 for the thermal and stress passes respectively.
7.0 CONCLUSION
S A unit internal pressure analysis, in-plane moment analysis, out-of-plane moment afialysis, axial load analysis, and six separate thermal transient stress analyses are performed, and both linearized and mapped stresses are extracted and saved for later fatigue crack growth evaluations and ASME Code,Section III stress and fatigue evaluations. The stress results are saved in individual files for future usage.
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8.0 REFERENCES
- 1. SI Calculation Package 0800368.322, "Finite Element Models of Reactor Coolant Pump Discharge Nozzle with Weld Overlay Repair," (for revision refer to SI Project Revision Log, Latest Revision).
- 2. SI Calculation Package 0800368.311, "Design Loads for the 28" I.D. Reactor Coolant Pump (RCP) Suction and Discharge Nozzles," (for revision refer to SI Project Revision Log, Latest Revision).
- 3. ANSYS/Mechanical, Release 8.1 (w/ Service Pack 1), ANSYS Inc., June 2004 File No.: 0800368.323 Revision: 0 Page 10 of 29 F0306-01:
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Table 1: Bounding Transients for Analysis Transient
- Time, Btu/hr-T Number Description sec T, IF m', lb/hr P, psia Cycles ft2-°F factor 1
Plant Heatup 0
70 0
15 240 27.6 0.000 IA 17532 557 46323539 1050 8461.5 1.002 23400 557 46323539 2250 8461.5 1.002 24480 579 46323539 2250 8666.6 1.047 2
Plant Cooldown 0
550 46323539 2250 240 8426.2 1.008 lB 10800 300 22560165 350 3638.4 0.473 21600 280 22560165 250 3492.9 0.432 43200 140 0
15 43.2 0.144 3
556.5 46323539 2250 590 8461.5 1.001 8A (bounds 7, 8B, 14, 15) 12 570 18800138 2500 4176.2 1.028 30 550 10026740 2200 2477.0 0.987 25200 550 0
2250 81.8 0.987 4
556.5 46323539 2200 188 8461.5 1.001 8C (bounds 9, 11, 17A) 2 560 46323539 2240 8505.0 1.008 10 565 46323539 2400 8507.5 1.018 15 562 46323539 2500 8505.0 1.012 20 585 46323539 2620 8626.0 1.059 30 590 46323539 2500 8642.9 1.070 40 580 46323539 2200 8588.8 1.049 60 565 46323539 2100 8507.5 1.018 100 552 46323539 2025 8442.8 0.991 5
Change of Flow 0
556.5 46323539 2190 21060 8461.5 1.001 10 (bounds 2, 3, 4, 5, 6) 30 546.5 11580885 2130 2773.4 0.980 150 557.5 0
2250 81.9 1.003 180 559.5 0
2200 82.3 1.007 6
Hydrotest 100 15 20 0.062 12 400 3125 0.679 100 15 0.062 Notes:
- 1) Reproduced from Table 5 of Reference 2.
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ELEIYENTS MAT N~v MN KOr NO.1 Figure 1. Finite Element Model of the RCP Discharge Nozzle with Minimum "Optimized" Weld Overlay Repair File No.: 0800368.323 Revision: 0 Page 12 of 29 F0306-01
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ELEŽ']WS r,,RT NUL1 AN PLOTW.
IO Figure 2. Finite Element Model of the RCP Discharge Nozzle with Maximum "Full Structural" Weld Overlay Repair File No.: 0800368.323 Revision: 0 Page 13 of 29 F0306-01
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MY FPLOT NO.
-1898
-1254
-610 34 678
-157 6
-932
-288 356 1000 RCP Outlet Nozzle Figure 3. Applied Boundary Conditions and Pressure Loading for Unit Pressure Analysis File No.: 0800368.323 Revision: 0 Page 14 of 29 F0306-01
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ELF'ENTS MAT NUN AN PLOT2 NO.
1 Figure 4. Applied Boundary Conditions and Loading for Unit In-Plane Moment Analysis File No.: 0800368.323 Revision: 0 Page 15 of 29 F0306-01
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IELEvMNS 11UýT NEm AN PLOT' NO.
1 Figure 5. Applied Boundary Conditions and Loading for Unit Out-of-Plane Moment Analysis File No.: 0800368.323 Revision: 0 Page 16 of 29 F0306-01
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ELEME=S AN IN OF NO.I Figure 6. Applied Boundary Conditions and Loading for Unit Axial Force Analysis File No.: 0800368.323 Revision: 0 Page 17 of 29 F0306-01
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ELEIVENS
=T NUA CONV-HCOE
.016b322 AN PJi0I' W3.
1 Figure 7. Applied Heat Transfer Coefficients for Thermal Transient Analyses (Thermal Pass)
(Heatup transient example is shown but remains valid for all transient cases.)
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E1.IP1ENS HAT NUM AN PLOT NO.
1 Figure 8. Applied Boundary Conditions for Thermal Transient Analyses (Stress Pass)
(Heatup transient example is shown but remains validfor all transient cases.)
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Figure 9. Stress Path Definitions for Maximum Weld Overlay used for Thermal Transient Analyses for Later ASME Code Evaluations File No.: 0800368.323 Revision: 0 Page 20 of 29 F0306-01
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Figure 10. Stress Path Definitions for Minimum Weld Overlay used for Unit Pressure, Unit Axial and Unit Moment (In-Plane/Out-of Plane) Analyses for Later ASME Code Evaluations File No.: 0800368.323 Revision: 0 Page 21 of 29 F0306-0t
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Figure 11. Stress Path Definitions for Maximum Weld Overlay used for Thermal Transient Analyses for Later Crack Growth Evaluations File No.: 0800368.323 Revision: 0 Page 22 of 29 F0306-01
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Figure 12. Stress Path Definitions for Minimum Weld Overlay used for Unit Pressure, Unit Axial and Unit Moment (In-Plane/Out-of Plane) Analyses for Later Crack Growth Evaluations File No.: 0800368.323 Revision: 0 Page 23 of 29 F0306-01
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NCDAL SOLUTICN STEP=1 SUB =1 TIME=1 SINT TOP DHX =. 0031 SHN =186.43 SMX =16034 186.43 1947 RCP Outlet Nozzle AN PLOT NO.
3708 7230 10751 14273 5469 8990 12512 16034 Figure 13. Stress Intensity Contour Plot for 1000 psi Internal Pressure File No.: 0800368.323 Revision: 0 Page 24 of 29 F0306-O1
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NODAL SOLUTION STEP=1 SUB =1 TTME=l SINT (AVG)
TOP LXMX =.143E-04 SM4 =. 194E-06 SMX =39.314 SHM -49. 599 AN PLOT M NO.
.194E-06 8.737 17.473 26.21 34.946 3194E-06 8.737 17.473 26.21 34.946 Figure 14. Stress Intensity Contour Plot for 1000 lb Axial Force 9.314--.
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NODAL SOLUTION STEP=1 SUB =1 TTME=1 SINT (AVG)
[VfX =.293E-05 S1N
=.405E-07 SMX
- 1. 179 S1vDIW1.541 ANSYS 8.1 PLOT NO.
1
.405E-07
.261913
.523826
.78574 1.048
.13095
.39287
.6547i83
.916696 1.179 Figure 15. Stress Intensity Contour Plot for 1000 in-lb In-Plane Moment Load File No.: 0800368.323 Revision: 0 Page 26 of 29 F0306-01
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N(VAL SOLLTI'ON STEP=
SUB ='1 TINE >1 SINTP (AVG)
TOP DK( =.252E--05 SvIC =. 251E-08 SMX ='1.324 SNXB-2.266 AN PLOT NO.
I
.251E-08
.294166
.588332
.882498 1.177
.147083.294.....441249 735415 1.03 1.324 Figure 16. Stress Intensity Contour Plot for 1000 in-lb Out-of-Plane Moment Load File No.: 0800368.323 Revision: 0 Page 27 of 29 F0306-01
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NODAL SOLUTIION SMEP=2 SUB =4 TIME=17532 TMIP (AVG)
RSYS=0 SMN =412.829 SMX =556.937 AN PLOT NO.
412.829 444.853 476.877 508.901 540.925 428.841 460.865 Po492.889 52f.91373 seconds Figure 17. Temperature Plot for Heatup Transient (Time = 17532 seconds)
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NODAL SOLUTION STEP=5 SUB =1 TIMWS=17532 SIN]T (AVG)
TOP DMX =.300518 SMN =9.189 SMX =91424 AN PLOT NO.
9.189 20324 40638 60953 81267 10166 0.5095 Figure 18. Intensity Contour Plot for Heatup Transient (Time = 17532 seconds)
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APPENDIX A ANALYSIS COMPUTER FILES File No.: 0800368.323 Revision: 0 F0306-01RO Page A-I of A-2
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Filename Description DB-OUTLET-MIN.INP Base model geometry input file with min "optimized" WOL dimensions [1].
DB-OUTLET-MAX.INP Base model geometry input file with max "full structural" WOL dimensions r I].
MProp Linear DB.INP Linear material properties file [1 ].
TR*.INP Thermal pass input file for the bounding transients. * = 1 - 6 for transients (see Table 1).
SR*.INP Stress pass input files for bounding transients. * = 1 - 6 for transients (see Table 1).
Thermal temperature load files called by stress pass input files. * = 1 - 6 for T
T Ptransients (see Table 1).
DB-PRES.INP Internal pressure input file.
DB-MOMENTZ.INP In-plane moment input file.
DB-MOMENTY.INP Out-of-plane moment input file.
DB-AXIAL.INP Axial load input file.
Paths 1 - 6 linearized stress extraction file for stress pass for ASME,Section III
-S E
Manalyses for all thermal transients.
MAPSTRESSMAX.1NP Paths 7 - 15 mapped stress extraction file for stress pass for Crack Growth analysis for all thermal transients.
Paths 1 - 6 linearized stress extraction file for stress pass for ASME,Section III L -
S Manalyses for all unit mechanical analyses.
Paths 7 - 15 mapped stress extraction file for stress pass for Crack Growth MP S
Manalysis for all unit mechanical analyses.
SR*_P$.OUT Linearized stress output for all thermal transients for paths $ = I - 6;
- = 1 - 6 for transients (see Table 1).
SR* P$ MAP.OUT Mapped stress output for all thermal transients for paths $ = 7 - 15;
- = 1 - 6 for transients (see Table 1).
DB-PRES P$$ MAP.OUT Mapped stress output for unit pressure stress analysis for Crack Growth for D -P S paths $$ = 7 - 15.
DB-AXIAL P$$ MAP.OUT Mapped stress output for unit axial stress analysis for Crack Growth for paths $$
=7-15.
DB-MOMENTY P$$ MAP.OUT Mapped stress output for unit out-of-plane moment stress analysis for Crack M M Y
$T Growth for paths $$ = 7 - 15.
DB-MOMENTZ P$$ MAP.OUT Mapped stress output for unit in-plane moment stress analysis for Crack Growth D-M T
-for paths $$ = 7 - 15.
Linearized stress output for unit pressure stress analysis for ASME,Section III DB-PRES P$$.OUTAnalysis for paths $$ =
- 6.
DB-AXIAL P$$.OUT Linearized stress output for unit axial stress analysis for ASME,Section III Analysis for paths $$ = 1 - 6.
Linearized stress output for unit out-of-plane moment stress analysis for ASME,
-Section III Analysis for paths $$ = 1 - 6.
Linearized stress output for unit in-plane moment stress analysis for ASME, DB-MOMENTZP$$.OUT Section III Analysis for paths $$ = 1 - 6.
File No.: 0800368.323 Revision: 0 Page A-2 of A-2 F0306-O1RO