JAFP-08-0067, Calculation No. 0800846.301, Revision 0, 2 Instrument Nozzle Stress Analysis.

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Calculation No. 0800846.301, Revision 0, 2 Instrument Nozzle Stress Analysis.
ML082100460
Person / Time
Site: FitzPatrick Constellation icon.png
Issue date: 07/16/2008
From: Chintapalli A, Qin M
Structural Integrity Associates
To:
Office of Nuclear Reactor Regulation
References
10201335, JAFP-08-0067 0800846.301, Rev 0
Download: ML082100460 (24)
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Text

Proprietary Information Withhold from Public Disclosure Pursuant to 10 CFR 2.390(a)(4)

ATTACHMENT 10 to JAFP-08-0067 Entergy Nuclear Operations, Inc.

James A. FitzPatrick Nuclear Power Plant Structural[Integrity. Associates SCalculationNo.00800846.301, Revision 0, "2" Instrument Nozzle Stress Analysis," 7/16/2008 Attachments 2, 6, and 8 contain proprietary information as described in 10 CFR 2.390.

When separated from these attachments this letter and its contents are non-proprietary.

Proprietary Information Withhold from Public Disclosure Pursuant to 10 CFR 2.390(a)(4)

ATTACHMENT 10 to JAFP-08-0067 CONTENTS

1) SIA Calculation 0800846.301 22 Pages Attachments 2, 6, and 8 contain proprietary information as described in 10 CFR 2.390.

When separated from these attachments this letter and its contents are non-proprietary.

StructuralIntegrityAssociates, Inc. File No.: 0800846.301.RO CALCULATION PACKAGE Project No.: 0800846 Z Q [ Non-Q PROJECT NAME:

James A. Fitzpatrick Support for NRC RAIs on P-T Curves CONTRACT NO.:

10201335 CLIENT: PLANT:

Entergy Nuclear Operations, Inc. James A. Fitzpatrick Nuclear Power Plant (JAFNPP)

CALCULATION TITLE:

2" Instrument Nozzle Stress Analysis Document Affected Project Manager Preparer(s) &

Revision Pages Revision Description Approval Checker(s)

Signature & Date Signatures & Date 0 1 -22. Initial Issue G. L. Stevens M. Qin 07/16/2008 07/16/2008 A. Chintapalli 07/16/2008 I

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Table of Contents

1.0 INTRODUCTION

........ 44.......................

2.0 DESIGN INPUTS ................................................... 4 3.0 ASSUMPTIONS ....... 44.......................

4.0 METHODLOGY OF HEAT TRANSFER COEFFICIENT CALCULATION ...................... 4 5.0 FINITE ELEMENT MODEL ..................................................... 5 6.0 APPLIED LOADS ................................................................. 5 7.0 THERMAL AND PRESSURE LOAD RESULTS ................................................................. 7

8.0 REFERENCES

..................................................... 8 List of Tables Table 1: List of Component Materials............................................................................................ 10 Table 2: SA-533, Grade B, Class 1 (Mn-1/2Mo-1/2Ni) .................... v......................................... 10 Table 3: SA-182 F304 (18Cr-8Ni) ............................................................................................... 10 Table 4: Alloy 82/182/600 (N06600) ........................ .................................................................... 11 T able 5: A ir Properties ............................. .......................................................... ................................ 11 Table 6: Thermal Transients ......................................................................................................... 11 Table 7: Heat Transfer Coefficient Calculation for Region 1 .......................... 12 Table 8: Summary of Heat Transfer Coefficient at Regions 1 to 3 ...................... 12 File No.: 0800846.301.RO Page 2 of 22 F0306-O1RO

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List of Figures Figure 1: The Instrument Nozzle Dimensions and Thermal Regions................................... 13 Figure 2: As-Modeled Instrument Nozzle and Reactor Pressure Vessel................................ 14 Figure 3: Close-Up View of As-Modeled Nozzle Forging and Safe End .............................. 15 Figure 4: Element Plot of Applied Internal Pressure Load to As-Modeled Instrument Nozzle......16 Figure 5: Applied Boundary Conditions to As-Modeled Instrument Nozzle........................... 17 Figure 6: Overall Stress Intensity for Unit Pressure Load ............................................... 18 Figure 7: Overall Stress Intensity for Thermal Transient 11 ............................................. 19 Figure 8: Overall Stress Intensity for Thermal Transient 14 ............................................ 20 Figure 9: Path 1 Definition ................................................................................. 21 Figure 10: Path 2 Definition ............................................................................... 22 Page 3 of 22 0800846.301.RO File No.: 0800846.301.RO F0306-OIRO

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1.0 INTRODUCTION

The objective of this calculation is to perform stress analysis for the reactor pressure vessel (RPV) 2" instrument nozzle at the James A. Fitzpatrick Nuclear Power Plant (JAFNPP). To accomplish this task, an internal pressure and two bounding thermal transients were separately analyzed with a detailed, three-dimensional (3-D) finite element model (FEM) of the instrument nozzle. Hoop stress histories were extracted from a path that starts from inside comer of the nozzle, passing through the peak stress location, and ends at the outside surface of the RPV wall. The resulting stress distributions will be used as an input to a subsequent pressure-temperature (P-T) curve analysis.

2.0 DESIGN INPUTS The 2" instrument nozzle dimensions are taken from References [1] and [8]. Figure 1 shows the main dimensions of the nozzle.

The materials of the various components are listed in Table 1 along with the associated references.

The material property values (Young's modulus E, thermal expansion coefficient cc, thermal conductivity k, and specific heat cp) are obtained from Reference [3] and are shown in Tables 2 through 4. The air property values (thermal expansion coefficient a, thermal conductivity k, specific heat cp, and density p) are obtained from Reference [4] and are also shown in Table 5. An ANSYS

[5] material input file (MA TPROPS.INP)was generated that contains the material properties.

3.0 ASSUMPTIONS The weld material properties listed in Table 1 are assumed based on practices established in ASME Code Section IX [6]. Weld material properties are based on weld procedure qualifications. Testing

  • isthe only way to verify the properties. In general, the failure location is at base metal during the test. Therefore, applying the weaker base metal properties instead of weld material properties is conservative. In this project, since the chemical composition of Alloy 600 (N06600) is close to Alloy 82/182, Alloy 82/182 material properties are used for Alloy 600 materials.

The (Tw - T.) term for natural convection heat transfer was taken as the difference between the fluid temperature and a lower bound ambient temperature of 70'F. This conservatively maximizes the heat transfer coefficient value for stagnant flow conditions.

4.0 METHODLOGY OF HEAT TRANSFER COEFFICIENT CALCULATION The instrument nozzle does not experience any significant flow. Therefore, an expression for the natural convection heat transfer coefficient can be developed by combining Equations 5-42 and 7-56 of Reference [7], as follows:

Nuftee =C. (Gr . Pr)n (1)

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hfree = C.(Gr. Pr)n .k (2) x At 0.75 <x/D < 2.0 Where:

hfree = Natural-convection heat transfer coefficient, h = Nu

  • k / x C = Linear coefficient representing the pipe geometry Gr = Grashof number for the flow n = Polynomial coefficient representing the pipe geometry x = Characteristic length (the pipe diameter for tube flow and difference of radius for annular flow), ft D = Pipe diameter, ft As shown in the accompanying text for Equation 7-56 of Reference [7], values of C = 0.55 and n =

0.25 are reasonable for the pipe geometry under consideration. The Grashof number is a

.dimensionless quantity representing the free convection state of a system, and it is calculated with the following equation [7, Equation 7-21]:

Gr = g "f,8 (Tw 2 T )" x, 3 Where:

g Acceleration due to gravity, 32.173 ft/sec 2 03 = Volumetric rate of expansion of the fluid, ft3/ft3 -oF T, = Temperature of the pipe wall (surface), 'F T.o = Temperature of the fluid, 'F x = Characteristic length (the pipe diameter for tube flow and difference of radius for annular flow), ft v = kinematic viscosity, ft2/s 5.0 FINITE ELEMENT MODEL A 3-D FEM was constructed using the dimensions and information shown in Figure 1 with the ANSYS [5] finite element software. A symmetric one-quarter portion of the nozzle and attached nozzle vessel was modeled. SOILD45 (structural) and SOLID70 (thermal) element types were used for the model. Figure 2 shows the overall model and Figure 3 shows a close-up view of the as-modeled nozzle forging and safe end.

6.0 APPLIED LOADS Both pressure and thermal loads will be applied to the FEM.

6.1 Pressure Load A uniform pressure of 1,000 psi was applied along the inside surface of the instrument nozzle and the RPV wall. In addition, a membrane or "cap" load was applied to the piping at the end of the nozzle to File No.: 0800846.301.RO Page 5 of 22 F0306-O1RO

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account for closed-end effects of the attached piping, which is not modeled. This cap load was calculated as follows:

P*R 2 PCAP =R.2_R2 where:

P = Pressure 1000 psi Ri = Inner Radius = 1.9375 in / 2 = 0.96875 in Ro Outer Radius = 2.40625 in / 2 =1.203125 in Therefore, the cap load is 1,843.6 psi. The calculated value was given a negative sign in order for it to exert tension on the end of the model. The nodes on the end of the safe end are coupled in the axial direction to ensure mutual displacement of the end of the nozzle due to the attached piping that is not modeled.

The same boundary condition and cap load are applied on the RPV wall cross section. Since the vessel innerradius is 110.0625 inches and outer radius is 117.0625 inches, the cap load is 7,619.3 psi. The nodes on the end of the RPV are coupled in the axial direction to ensure mutual displacement of the end of the RPV.

The ANSYS input file IN.INP generates the instrument nozzle geometry and INPRESS.INP performs the internal pressure load case just described. Figures 4 and 5 show the applied axial cap load on the safe end and RPV, the applied internal pressure distribution, the applied symmetric boundary conditions on the RPV wall, and the coupling on the safe end / RPV.

In the meantime, to avoid overlap during analysis for the gap between the nozzle and RPV wall, a pair of contact element types (CONTA 172 and TARGE 170) is used.

All ANSYS input files for the pressure analyses, as listed below, are saved in the project computer files:

MA TPROPS.INP: Material properties IN.INP: Geometry input file IN PRESS.INP: Pressure load 6.2 Thermal Load Since there isn't any flow coming through the instrument nozzle, the nozzle temperature depends on the RPV fluid temperature. Per Reference [8], the instrument nozzle is located in RPV Region B.

Based on the Reactor Thermal Cycles Drawing [9], the two most severe thermal transients are Transient 11 (Loss of Feedwater Pumps) and Transient 14 (SRV Blowdown). Since it is not clear a priori which of these transients causes the higher thermal stress in the nozzle, both are selected for analysis. These transients are listed in Table 6.

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Figure 1 shows the regions of the model with different heat transfer coefficients. The heat transfer coefficient at Region 2 is 500 Btu/hr-ft2 -°F for all temperatures per Reference [2, page B 115]. The heat transfer coefficient at Region 3 is assumed as 0.2 Btu/hr-ft2 - F for all temperatures. The heat transfer coefficients for Region 1 were determined for different temperatures, as included in spreadsheet "IN-HTC.xls" based on the methodology discussed in Section 4. Table 7 shows the EXCEL script sheet, and Table 8 summaries the heat transfer coefficients for the three regions.

The FEM geometry discussed in Section 5.0 is used as input to the files in which the thermal transient stress analyses are performed. The SOLID70 element type is used for thermal analysis and the SOLID45 element type is used for stress analysis. During the thermal analysis, the elements at the nozzle and the vessel gap are selected and air thermal properties are applied to them to simulate the heat transfer between the two surfaces. These elements are unselected during the stress analysis.

For the thermal transient ANSYS analyses, the thermal transients defined in Table 6 are analyzed applying heat transfer coefficients from Table 7.

Stress analyses are performed using the temperature distributions calculated in the thermal transient analyses as input. Symmetric boundary conditions are applied to the symmetry faces of the instrument nozzle model. The nodes at the end of the safe are coupled in the axial direction to simulate the effects of the attached piping.

All ANSYS input files for the thermal analyses, as listed below, are saved in the project computer files:

MATPROPS.INP: Material properties IN.INP: Geometry input file IN-htbc.INP: Heat transfer boundary conditions TRANll-T.INP: Transient 11, thermal analysis TRANJl-Tmntr.INP: Transient 11, thermal monitoring file TRANll-S.INP: Transient 11, stress analysis TRAN14-T.INP: Transient 14, thermal analysis TRAN14-Tmntr.INP: Transient 14, thermal monitoring file TRAN14-S.INP: Transient 14, stress analysis 7.0 THERMAL AND PRESSURE LOAD RESULTS A thermal transient analysis for each defined transient, as well as a unit pressure stress analysis, was performed for the instrument nozzle. Figures 6 through 8 show the maximum stress intensity location under unit pressure load and the two -thermal transients. The maximum stress intensity for unit pressure is located at Node 4747 and the maximum stress intensity in the nozzle for thermal Transients 11 and 14 is located at Node 5482 at times of 290 seconds and 4,055 seconds, respectively. Therefore, results will be extracted at two paths to ensure that the limiting case can be evaluated when both pressure and thermal stresses are combined.

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Node 4747 is located at the end of the nozzle and vessel gap at approximately a 450 azimuth. Path 1 is from the nozzle comer (Node 5497) through the maximum stress location (Node 4747) to the outside of the vessel (Node 47485). The length of the path is 7.3949 inches. For the P-T curve assessment, only a quarter of the total length is of interest. Therefore, Node 44900 was selected and the path from Node 5497 to Node 44900 is 2.1054 inches which covers the 1/4T range. Figure 9 shows this path definition.

Node 5482 is located at the comer of the nozzle end at 90'. Path 2 is from the nozzle comer (Node 5482) to the outside of the vessel (Node 47365). The length of the path is 7.4152 inches. For the P-T curve assessment, only a quarter of the total length is of interest. Therefore, Node 42132 was selected and the path from Node 5482 to Node 42132 is 2.1067 inches which covers the 1/4T range.

Figure 10 shows this path definition.

Hoop stress (circumferential direction to nozzle pipe) through these paths was extracted. The thermal stress and pressure hoop stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:

MAP STRESS- MAX-PI.INP Extract stress file for Path 1 IN_Press-Pl1Map.out: Path 1 stress analysis results for unit pressure TRAN11-S-P1_Map.out: Path 1 Transient 11, thermal stress analysis results TRAN14-S-P1_Map.out: Path 1 Transient 14, thermal stress analysis results MAP STRESS- MAX-P2.INP Extract stress file for Path 2 INPress-P2_Map.out: Path 2 stress analysis results for unit pressure TRANI1 -S-P2_Map.out: Path 2 Transient 11, thermal stress analysis results TRAN14-S-P2_Map.out: Path 2 Transient 14, thermal stress analysis results There are no specific stress limits that apply to the results of this calculation; rather, there are fracture limits that must be met when these stresses are used in the P-T curve assessment that will be performed in a follow-on calculation.

8.0 REFERENCES

1. JAF File No. 11825-5.17-1, Revision D, (Combustion Engineering Inc. Drawing No. E233-242),

"Nozzle Details for 218" ID BWR," SI File No. 0800846.201.

2. Combustion Engineering, Inc. Nuclear Components Department, Report No. CENC-1 159, August 1971, "Analytical Report for Pasny Reactor Vessel for Fitzpatrick Station," SI file No.

FITZ-07Q-208.

3. ASME Boiler and Pressure Vessel Code,Section II, Part D, Material Properties, 2001 Edition with Addenda through 2003.
4. N. P. Cheremisinoff, "Heat Transfer Pocket Handbook," Gulf Publishing Co., 1984.
5. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.

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6. ASME Boiler and Pressure Vessel Code,Section IX, Qualification Standard for Welding and Brazing Procedures, Welders, Brazers, and Welding and Brazing Operators, 2001 Edition with Addenda through 2003.
7. J. P. Holman, "Heat Transfer," 5 th Edition, McGraw-Hill, Inc., 1981.
8. SI File No. 0800846.103, "Instrument Nozzle Fluence," received on 6/19/08, from M. Alvi, Entergy.
9. Fitzpatrick Drawing No. 11825.5-15-lA, Revision 2, 08/11/2005, (General Electric Drawing No.

729E762, Revision 0) "Reactor Thermal Cycles," 1 sheet, SI File No. 0800846.202.

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Table 1: List of Component Materials Component Material Reference RPV Shell SA-533 Gr. B Class 1 2, page A-9 RPV Cladding Stainless Steel Type 304 2, page A-9 Nozzle Forging SB-166 (use N06600) 1 Safe End SA-182 F304 1 Nozzle-to-Vessel End Butter Inconel (use N06600) 1 Weld use N06600 Assumed Table 2: SA-533, Grade B, Class 1 (Mn-1/2Mo-1/2Ni)

Temperature Young's Modulus Mean Thermal Expansion Thermal Conductivity Specific Heat 6

(OF) (x10 psi) (x10"6 in/in/*F) (Btu/hr-ft-°F) (Btu/Ib-*F)

70. 29.2 7.0 23.5 0.105 200 28.5 7.3 23.6 0.114 300 28.0 7.4 23.4 0.119 400 27.4 7.6 23.1 0.125 500 27.0 7.7 22.7 0.130 600 26.4 7.8 22.2- 0.135 Density (p) = 0.283 ibm/in 3, assumed temperature independent.

Poisson's Ratio (u) - 0.3, assumed temperature independent.

Table 3: SA-182 F304 (18Cr-8Ni)

Temperature Young's Modulus Mean Thermal Expansion Thermal Conductivity Specific Heat (OF) (xl06 psi) (x10"6 in/in/0 F) (Btu/hr-ft-*F) (Btu/Ib-°F) 70 28.3 8.5 8.6 0.116 200 27.6 8.9 9.3 0.122 300 27.0 9.2 9:8 0.125 400 26.5 9.5 10.4 0.129 500 25.8 9.7 10.9 0.131 600 25.3 9.8 11.3 0.133 Density (p) = 0.283 lbm/in 3, assumed temperature independent.

Poisson's Ratio (u) = 0.3, assumed temperature independent.

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Table 4: Alloy 82/182/600 (N06600)

Temperature Young's Modulus Mean Thermal Expansion Thermal Conductivity Specific Heat (OF) (x10 6 psi) (x10"6 in/in/°F) (Btu/hr-ft-°F) (Btu/lb-0 F) 70 31.0 6.8 8.6 0.108 200 30.2 7.1 9.1 0.113 300 29.8 7.3 9.6 0.116 400 29.5 7.5 10.1 0.118 500 29.0 7.6 10.6 0.120 600 28.7 7.8 11.1 0.123 Density (p) = 0.300 ibm/in3 , assumed temperature independent.

Poisson's Ratio (u) = 0.3, assumed temperature independent.

Table 5: Air Properties Temperature Density Mean Thermal Expansion Thermal Conductivity Specific Heat (OF) (lblfe) (jj0"3in/in/lF) (x10- 3 Btu/hr-ft-°F) (xl10 3 Btu/Ib-0 F) 70 0.0751 1.888 0.0149 0.906 200 0.0602 1.520 0.0179 1.234 300 0.0523 1.320 0.0203 1.597 400 0.0462 1.160 0.0225 1.988 500 0.0413 1.040 0.0246 2.412 600 0.0374 0.944 0.0270 2.876 Table 6: Thermal Transients Transient Time Temp Time Step fuf (E1 Wi 0 527 220 220 2200 500 1980 2380 300 180.

11. Loss of 6880 500 4500 FW Pumps  ?-.

7300 300 420 17300 i 300 10000 26336 5_5_1

. 9036 36336 551 10000 36337 i 543 1 1

46337-- 543 10000 46338 - 527 ' 1 56338 L 527 - 10000

14. SRV '600 1 375 i 600 Blowdown 10500 9.00 9...

20500 100 i 10000 Note: 1. One-second for step changes and 10,000 seconds for steady state conditions to be achieved were assumed.

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Table 7: Heat Transfer Coefficient Calculation for Region 1 Title = Safe End Pipe Inside Diameter, D = 1.938 inches = 0.161 ft

= 0.049 m Outer Pipe, Inside radius, r. = 0.96875 inches = 0.081 ft 0.025 m Inner Pipe Outside Diameter, D = n/a inches = 0.000 ft

0.000 m Inner Pipe, Outside radius, r, = 0 inches = 0.000 ft 0.000 m Fluid Velocity, V= 0.000 ft/sec = 0.000 gpm

Characteristic Length, L = D= 0.161 ft = 0.049 m (Outside) Tfui - Tsurfcm, AT = 0.00 30.00 130.00 230.00 330.00 430.00 530.00 -F

= 0.00 16.67 72.22 127.78 183.33 238.89 294.44 C Value at Fluid Temperature, T [4] Units Conversion 70 100 200 300 400 50 600 -F Water Property Factor M 21.11 37.78 93.33 148.89 204." 260.00 315.56 °c k 1.7307 0.6006 0.6300 0.6784 0.6836 0.6611 0.6040 0.5071 W/m-°C Thermal Conductivity) 0.3470 0.3640 0.3920 0.3950 0.3820 0.3490 0.2930 Btu/hr-ft-°F cp 4.1869 4.185 4.183 4.229 4.313 4.522 4.982 6.322 kJ/kg-°C

......... &Specific H . ............. 1.000 0.999 1.010 1.030 1.080 1.190 1.510 Btu/Ibm-°F p 16.018 997.1 994.7 962.7 917.8 858.6 784.9 679.2 kg/rn 3

(Density) 62.3 62.1 60.1 57.3 53.6 49.0 42.4 Ibm/ft 3 3 1.8 1.89E-04 3.24E-04 6.66E-04 1.01E-03 1.40E-03 1.98E-03 3.15E-03 m /m -.C 3 3 Volumetric Rate of Expansion) 1.05E-04 1.80E-04 3.70E-04 5.60E-04 7.80E-04 1.1OE-03 1.75E-03 ft /ft -F 2

g 0.3048 9.806 9.806 9.806 9.806 9.806 9.806 9.806 m/s (Gravitational Constant) 32.17 32.17 32.17 32.17 32.17 32.17 32.17 ft/s' 1.4881 9.95E-04 6.82E-04 3.07E-04 1.93E-04 1.38E-04 1.04E-04 8.60E-05 kg/m-s

... ynamicViss 6.69E-04 4.58E-04 2.06E-04 1.30E-04 9.31E-05 7.OOE-05 5.78E-05 Ibm/ft-s Pr 6.980 4.510 1.910 1.220 0.950 0.859 1.070 ---

(Prandtl Number)

Calculated Parameter Formula 70 100 200 300 400 50 600 -F Reynold's Number, Re pVD/IA 0.OOE+00 0.OOE+00 0.OOE+00 0.00E+00 0.OOE+00 0.OOE+00 0.OOE+00 --

3 2 Grashof Number, Gr gpATL /(pip) 0.OOE+00 1.34E+07 5.54E+08 3.39E+09 1.16E+10 3.14E+10 6.76E+10 --

Rayleigh Number, Ra GrPr 0.00E+00 6.06E+07 1.06E+09 4.13E+09 1.10E+10 2.70E+10 7.24E+10 -

From [7]:

Inside Surface NaturalConvection Heat TransferCoefficient:

Case: Enclosed cylinder C= 0.55 n= 0.25 page 289 of [7])

2 Hfme C(GrPr)nk/L 0.00 621.24 1,367.40 1,937.31 2,392.13 2,735.37 2,939.49 W/m -. C 2

0 109 241 341 421 482 518 Btu/hr-ft -0F Table 8: Summary of Heat Transfer Coefficient at Regions 1 to 3 Heat Transfer Coefficient Btu/hr-ft2-F)

Temo (OF) Realon I Reuion 2 Realon 3 100 109 500 0.2 300 341 500 0.2 375 316 500 0.2 500 482 500 0.2 527 491 500 0.2 543 497 500 0.2 551 500 500 0.2 File No.: 0800846.301.RO Page 12 of 22 F0306-01 RO

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TYPE NUM I3 Instrument Nozzle Note: All dimensions are from Reference [1] except for the two dimensions identified from Reference [8].

Figure 1: The Instrument Nozzle Dimensions and Thermal Regions File No.: 0800846.301.RO Page 13 of 22 F0306-O1RO

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HAT NUM Instrument Nozzle Figure 2: As-Modeled Instrument Nozzle and Reactor Pressure Vessel File No.: 0800846.301.RO Page 14 of 22 F0306-O1RO

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HAT NUM Figure 3: Close-Up View of As-Modeled Nozzle Forging and Safe End File No.: 0800846.301.RO Page 15 of 22 F0306-O1RO

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AN 1 2008 23:4 9

-6662 . ..'- i2* -286i -915.403 1000 UNIT INTERNAL PRESS Figure 4: Element Plot of Applied Internal Pressure Load to As-Modeled Instrument Nozzle File No.: 0800846.301.RO Page 16 of 22 F0306-O1RO

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ELEMENTS MAT NUM Figure 5: Applied Boundary Conditions to As-Modeled Instrument Nozzle File No.: 0800846.301.RO Page 17 of 22 F0306-O1 RO

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NODAL SOLUTION STEP=1 SUB =1 TIME=1 SINT (AVG)

DMX =.054755 SMN =1201 SMX =60159 y -0.$12011' 2 0.951491 9=7 - 60109.5 F~*~1 3D ,m wi itp-

. .......... . ...43. 03... . ... ... 27405 .... ,,,,,,,,, , ,, I I I 1201 14303 27405 40507 53609 7752 20854 33956 47058 60159 UNIT INTERNAL PRESSURE (1000PSI) ANALYSIS Figure 6: Overall Stress Intensity for Unit Pressure Load File No.: 0800846.301.RO Page 18 of 22 F0306-O1RO

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Figure 7: Overall Stress Intensity for Thermal Transient 11 File No.: 0800846.301.R0 Page 19 of 22 F0306-O1RO

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564 Instrument Nozzle.

Figure 8: Overall Stress Intensity for Thermal Transient 14 File No.: 0800846.301.R0 Page 20 of 22 F0306-O1RO

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ELEMENTS ANSYS 8.1A1 JUL 11 2008 MAT NUM 12:08:56 I rode IM; I]

Figure 9: Path 1 Definition File No.: 0800846.301.R0 Page 21 of 22 F0306-O1RO

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Figure 10: Path 2 Definition File No.: 0800846.301.RO Page 22 of 22 F0306-O1RO

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