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

{{Adams
| number = ML082100460
| issue date = 07/16/2008
| title = Calculation No. 0800846.301, Revision 0, 2 Instrument Nozzle Stress Analysis.
| author name = Chintapalli A, Qin M
| author affiliation = Structural Integrity Associates, Inc
| addressee name = 
| addressee affiliation = NRC/NRR
| docket = 05000333
| license number = 
| contact person = 
| case reference number = 10201335, JAFP-08-0067
| document report number = 0800846.301, Rev 0
| document type = Calculation
| page count = 24
}}

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{{#Wiki_filter: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 -&deg;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-&deg;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-&deg;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/&deg;F)                  (Btu/hr-ft-&deg;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-&deg;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             &deg;c k                          1.7307            0.6006         0.6300       0.6784     0.6836       0.6611      0.6040        0.5071        W/m-&deg;C Thermal Conductivity)                                   0.3470         0.3640       0.3920     0.3950       0.3820      0.3490        0.2930      Btu/hr-ft-&deg;F cp                          4.1869            4.185           4.183        4.229      4.313       4.522        4.982         6.322       kJ/kg-&deg;C
        ......... &Specific H     . .............                       1.000          0.999        1.010      1.030        1.080       1.190         1.510      Btu/Ibm-&deg;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

StructuralIntegrity Associates, Inc.
564 Instrument Nozzle.
Figure 8: Overall Stress Intensity for Thermal Transient 14 File No.: 0800846.301.R0                                                           Page 20 of 22 F0306-O1RO

V     StructuralIntegrityAssociates, Inc.
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

v      StructuralIntegrityAssociates, Inc.
Figure 10: Path 2 Definition File No.: 0800846.301.RO                                       Page 22 of 22 F0306-O1RO}}