View source for HNP-16-095, Relief Request l3R-16, Reactor Vessel Closure Head Nozzle Repair Technique, Inservice Inspection Program, Third Ten-Year Interval, Non-Proprietary Version of Calculation

{{Adams
| number = ML16295A159
| issue date = 10/21/2016
| title = Relief Request l3R-16, Reactor Vessel Closure Head Nozzle Repair Technique, Inservice Inspection Program, Third Ten-Year Interval, Non-Proprietary Version of Calculation
| author name = Waldrep B
| author affiliation = Duke Energy Progress, LLC
| addressee name = 
| addressee affiliation = NRC/Document Control Desk, NRC/NRR
| docket = 05000400
| license number = NPF-063
| contact person = 
| case reference number = HNP-16-095
| document type = Calculation, Letter type:HNP
| page count = 118
| project = 
| stage = Request
}}

=Text=
{{#Wiki_filter:Benjamin C. Waldrep
~~ DUKE                                                                                        Vice President Harris Nuclear Plant
~  ENERGY.                                                                         5413 Shearon Harris Road New Hill, NC 27562-9300 919.362.2502 10 CFR 50.55a October 21, 2016 Serial: HNP-16-095 ATIN: Document Control Desk U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 Shearon Harris Nuclear Power Plant, Unit 1 Docket No. 50-400/Renewed License No. NPF-63

==Subject:==
Relief Request l3R-16, Reactor Vessel Closure Head Nozzle Repair Technique, lnservice Inspection Program, Third Ten-Year Interval, Non-Proprietary Version of Calculation Ladies and Gentlemen:
Duke Energy Progress, LLC (Duke Energy), requested NRC approval of relief request 13R-16 for the Shearon Harris Nuclear Power Plant, Unit 1 (HNP) inservice inspection program in a letter dated October 19, 2016 (Agencywide Documents Access and Management System (ADAMS) Accession Nos. ML16294A218 and ML16294A219). The October 19, 2016, letter contained the relief request and the proprietary version of the AREVA Inc. calculation to support this request. The purpose of this letter is to provide the non-proprietary version of the calculation provided in the October 19, 2016, letter.
This letter does not contain any regulatory commitments.
Please refer any questions regarding this submittal to John Caves, HNP Regulatory Affairs Manager, at (919) 362-2406.
Sincerely,
   ~a~n*~~

==Enclosure:==
Calculation 32-9215680-002, Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non-Proprietary) cc:    Mr. M. Riches, NRC Resident Inspector, HNP Ms. M. Barillas, NRC Project Manager, HNP NRC Regional Administrator, Region II

Benjamin C. Waldrep Vice President Harris Nuclear Plant 5413 Shearon Harris Road New Hill, NC 27562-9300 919.362.2502 10 CFR 50.55a October 21, 2016 Serial: HNP-16-095 ATTN: Document Control Desk U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 Shearon Harris Nuclear Power Plant, Unit 1 Docket No. 50-400/Renewed License No. NPF-63

==Subject:==
Relief Request I3R-16, Reactor Vessel Closure Head Nozzle Repair Technique, Inservice Inspection Program, Third Ten-Year Interval, Non-Proprietary Version of Calculation Ladies and Gentlemen:
Duke Energy Progress, LLC (Duke Energy), requested NRC approval of relief request I3R-16 for the Shearon Harris Nuclear Power Plant, Unit 1 (HNP) inservice inspection program in a letter dated October 19, 2016 (Agencywide Documents Access and Management System (ADAMS) Accession Nos. ML16294A218 and ML16294A219). The October 19, 2016, letter contained the relief request and the proprietary version of the AREVA Inc. calculation to support this request. The purpose of this letter is to provide the non-proprietary version of the calculation provided in the October 19, 2016, letter.
This letter does not contain any regulatory commitments.
Please refer any questions regarding this submittal to John Caves, HNP Regulatory Affairs Manager, at (919) 362-2406.
Sincerely, Benjamin C. Waldrep

==Enclosure:==
Calculation 32-9215680-002, Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non-Proprietary) cc:    Mr. M. Riches, NRC Resident Inspector, HNP Ms. M. Barillas, NRC Project Manager, HNP NRC Regional Administrator, Region II

U.S. Nuclear Regulatory Commission                                       Relief Request I3R-16 HNP-16-095 Enclosure HNP-16-095 Shearon Harris Nuclear Power Plant, Unit 1 Docket No. 50-400/Renewed License No. NPF-63 Relief Request I3R-16, Reactor Vessel Closure Head Nozzle Repair Technique, Inservice Inspection Program, Third Ten-Year Interval, Non-Proprietary Version of Calculation Enclosure Calculation 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non-Proprietary)

Controlled Document                                 0402-01-F01 (Rev. 019, 6/25/2015)
CALCULATION 

==SUMMARY==
SHEET (CSS)
Document No.             32     -   9215680      -    002                                  Safety Related: Yes  No Title   Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
PURPOSE AND 

==SUMMARY==
OF RESULTS:
AREVA NP Proprietary information in the document are indicated by pairs of brackets                           [ ] . The proprietary version of this document is in AREVA document 32- 9176350-003.
Purpose The purpose of the present fracture mechanics analysis is to determine the suitability of leaving degraded J-groove weld and butter material in the Shearon Harris Unit 1 reactor vessel head following the repair of either a Control Rod Drive Mechanism (CRDM) nozzle or Core Exit Thermocouple (CET) nozzle by the ID temper bead (IDTB) weld procedure. It is postulated that a small flaw in the head would combine with a large stress corrosion crack in the weld and butter to form a radial corner flaw that would propagate into the low alloy steel head by fatigue crack growth under cyclic loading conditions.
The purpose of Rev 001 is to revise the primary stress limit analysis performed in Section 6.5 (updated analysis in Appendix C) by performing a detailed primary stress limit analysis considering each of the CRDM repairs performed on Shearon Harris Unit 1s RVCH. Also, the objective is to determine the RVCH service life considering all the repaired CRDM configurations that have been performed to date as of the Spring (April) 2015 Outage.
The purpose of Rev 002 is to add a brief evaluation for nozzle repair at penetrations 30, 40 and 51 in the absence of original J-groove weld sizes and head thickness at these locations for additional 5 years operation.
Summary of Results Based on a combination of linear elastic and elastic-plastic fracture mechanics analysis of a postulated remaining flaw in the original Alloy 182 J-groove weld and butter material, a Shearon Harris Unit 1 CRDM or CET nozzle is considered to be acceptable for 30 years of operation following an IDTB weld repair based on EPFM analysis consideration only. The controlling loading condition is a large loss of coolant accident, for which it was shown that with safety factors of 3 on primary loads and 1.5 on secondary loads that the applied J-integral (2.359 kips/in) was still less than the J-integral of the low alloy steel head material (2.474 kips/in) at a crack extension of 0.1 inch.
Rev 001: Based on the evaluation presented in Appendix C, the RVCH repairs are acceptable for an additional 12 years beyond the Spring (April) 2015 outage (or 15 years from the time of installation).
Rev 002: Rev 001 conclusion for the nine repaired nozzles remains valid. Nozzle repairs at penetrations 30, 40 and 51 are acceptable for additional 5 years beyond the repair (Fall 2016 outage) based on the assumptions listed in Sub-Sections 3.1 and 3.2, and the analysis presented in Section C.7 of Appendix C. The limiting service life of all nozzle repairs is 5 years from the Fall 2016 outage.
If the computer software used herein is not the latest version per the EASI list,                  THE DOCUMENT CONTAINS AP 0402-01 requires that justification be provided.                             ASSUMPTIONS THAT SHALL BE VERIFIED PRIOR TO USE THE FOLLOWING COMPUTER CODES HAVE BEEN USED IN THIS DOCUMENT:
CODE/VERSION/REV                            CODE/VERSION/REV YES ANSYS 12.1 (Rev 000)
NO Page 1 of 115

Controlled Document Controlled Document 0402-01-F01 (Rev. 019, 6/25/2015)
Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Record of Revision Revision    Pages/Sections/Paragraphs No.                  Changed                      Brief Description / Change Authorization 000      All                               Original release. The corresponding proprietary version is in AREVA document 32- 9176350-001.
001      All                               Updated with the latest form (0402-01-F01 Rev. 018).
CSS page                          Added purpose and summary of Rev 001.
Section 6.5                       Text deleted and replaced with statement referencing Appendix C for Limit Load Analysis.
Section 7.0                       Added statements to address the service life of the RVCH considering all the CRDM repaired configurations to-date as of April 2015.
Appendix C                        Added the updated Limit Load Analysis to address each of the repaired CRDM configurations to-date as of April 2015.
002      All                               Updated with the latest form (0402-01-F01 Rev. 019).
CSS page                          Added purpose and summary of Rev 002.
Throughout                        Changed terminology from limit load analysis to primary stress limit analysis since limit load analysis is only one of the possible methods for satisfying primary stress limits.
Pages 2-3                         Updated for Rev 002.
Section 3.1                       Revised to include two unverified assumptions.
Section 3.2                       Added clarification to second paragraph.
Added a justified assumption (last paragraph).
Section 6.5                       Updated service life discussion based on Appendix C revision.
Section 7.1                       Deleted discussion of service life due to primary stress limit, which was redundant with discussion in Section 7.2 Section 7.2                       Updated service life discussion based on Appendix C revision.
Section 8.0                       Updated Reference 1 to latest revision.
Section C.2                       Revised second paragraph and inserted a table.
Sections C.4, C.6                 Corrected table titles for Tables C9 and C10.
Section C.7                       Added to address the three nozzle repairs (#30, #40 and #51).
Section C.8                       Updated from C.7; added References C14 to C16; updated revision for References C2 and C12.
Page 3

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table of Contents Page SIGNATURE BLOCK ................................................................................................................................ 2 RECORD OF REVISION .......................................................................................................................... 3 LIST OF TABLES ..................................................................................................................................... 6 LIST OF FIGURES ................................................................................................................................... 7

==1.0   INTRODUCTION==
 ........................................................................................................................... 8 2.0   ANALYTICAL METHODOLOGY ................................................................................................. 10 2.1     Stress Intensity Factor Solution ..................................................................................................... 12 2.1.1      Finite Element Crack Models ........................................................................................... 12 2.1.2      Stress Mapping ................................................................................................................ 12 2.1.3      Crack Growth Considerations .......................................................................................... 15 2.1.4      Plastic Zone Correction ................................................................................................... 15 2.2     Linear Elastic Fracture Mechanics ................................................................................................. 16 2.3     Elastic-Plastic Fracture Mechanics ................................................................................................ 17 2.3.1      Screening Criteria ............................................................................................................ 17 2.3.2      Primary Stress Limit Analysis .......................................................................................... 17 2.3.3      Flaw Stability and Crack Driving Force ............................................................................ 18 3.0   ASSUMPTIONS .......................................................................................................................... 20 3.1     Unverified Assumptions.................................................................................................................. 20 3.2     Justified Assumptions..................................................................................................................... 20 3.3     Modeling Simplifications ................................................................................................................. 20 4.0   DESIGN INPUTS ........................................................................................................................ 21 4.1     Materials ......................................................................................................................................... 21 4.1.1      Mechanical and Thermal Properties ................................................................................ 21 4.1.2      Toughness Properties ...................................................................................................... 23 4.1.3      Fracture Toughness ......................................................................................................... 23 4.1.4      J-integral Resistance Curve............................................................................................. 23 4.1.5      Fatigue Crack Growth Rate ............................................................................................. 25 4.2     Basic Geometry .............................................................................................................................. 26 4.3     Operating Transients ...................................................................................................................... 26 4.4     Applied Stresses ............................................................................................................................ 28 4.4.1      Residual Stresses ............................................................................................................ 28 4.4.2      Operating Stresses .......................................................................................................... 28 5.0   COMPUTER USAGE .................................................................................................................. 29 Page 4

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table of Contents (continued)
Page 5.1     Hardware/Software......................................................................................................................... 29 5.2     Installation/Validation Test ............................................................................................................. 29 5.3     Computer Files ............................................................................................................................... 31 6.0  CALCULATIONS ......................................................................................................................... 35 6.1     Initial Flaw Size .............................................................................................................................. 35 6.2     Fatigue Crack Growth .................................................................................................................... 35 6.3     LEFM Flaw Evaluations.................................................................................................................. 39 6.3.1      Normal and Upset Conditions .......................................................................................... 39 6.3.2      Faulted Conditions ........................................................................................................... 40 6.4     EPFM Flaw Evaluations ................................................................................................................. 41 6.4.1      Operating Conditions ....................................................................................................... 41 6.4.2      Low Temperature Conditions........................................................................................... 43 6.4.3      Faulted Conditions ........................................................................................................... 45 6.5     Primary Stress Limit Analysis ......................................................................................................... 47 7.0  

==SUMMARY==
OF RESULTS AND CONCLUSIONS....................................................................... 48 7.1     Summary of Results ....................................................................................................................... 48 7.2     Conclusion ...................................................................................................................................... 49

==8.0  REFERENCES==
 ............................................................................................................................ 49 APPENDIX A :    DETAILED FLAW EVALUATIONS FOR UPHILL SIDE ............................................................. 51 APPENDIX B :    DETAILED FLAW EVALUATIONS FOR DOWNHILL SIDE....................................................... 69 APPENDIX C :    CALCULATION OF AVAILABLE YEARS OF SERVICE BASED ON AVAILABLE REINFORCEMENT AREA DUE TO CRACK GROWTH............................................................ 89 Page 5

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
List of Tables Page Table 1-1: Safety Factors for Flaw Acceptance ....................................................................................... 9 Table 4-1: Material Properties for Head ................................................................................................. 21 Table 4-2: Material Properties for Weld Metal ....................................................................................... 22 Table 4-3: Material Properties for Cladding ........................................................................................... 22 Table 4-4: Bounding Transients for Normal and Upset Conditions........................................................ 27 Table 4-5: Emergency and Faulted Condition Transients...................................................................... 27 Table 5-1: Test Case Results ................................................................................................................ 30 Table 6-1: LEFM Fracture Toughness Margins for Uphill Side .............................................................. 37 Table 6-2: LEFM Fracture Toughness Margins for Downhill Side ......................................................... 38 Page 6

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
List of Figures Page Figure 1-1: ID Temper Bead Weld Repair ............................................................................................... 8 Figure 2-1: Postulated Radial Flaw on Uphill Side................................................................................. 11 Figure 2-2: Postulated Radial Flaw on Downhill Side ............................................................................ 11 Figure 2-3: Finite Element Crack Model - Uphill Side ........................................................................... 13 Figure 2-4: Finite Element Crack Model - Downhill Side....................................................................... 14 Figure 4-1: Correlation of Coefficient, C, of Power Law with Charpy V-Notch Upper Shelf Energy ...... 24 Figure 4-2: Correlation of Exponent, m, of Power Law with Coefficient, C, and Flow Stress, o ........... 24 Page 7

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)

==1.0     INTRODUCTION==

Due to the susceptibility of Alloy 600 partial penetration nozzles to primary water stress corrosion cracking (PWSCC), the Progress Energy plans to inspect the Control Rod Drive Mechanism (CRDM) and Core Exit Thermocouple (CET) nozzles in the Shearon Harris Unit 1 reactor vessel head. In the event that a repair is necessary, an ID temper bead weld repair procedure has been developed wherein the lower portion of the nozzle is removed by a boring procedure and the remaining portion is welded to the low alloy steel reactor vessel head above the original Alloy 82/182 J-groove attachment weld. The repair concept is illustrated in Figure 1-1, both with and without an overlap between the original J-groove weld and the new IDTB weld. The IDTB repair is more fully described by the design drawing [1]
and the technical requirements document [2]. Since a potential flaw in the J-groove weld cannot be sized by currently available non-destructive examination techniques, it is assumed that the as-left condition of the remaining J-groove weld includes degraded or cracked weld material extending through the entire J-groove weld and Alloy 82/182 butter material.
(a) With Weld Overlap                           (b) With Overlap Removed Figure 1-1: ID Temper Bead Weld Repair Page 8

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Since it is known from the residual stress analysis of the Shearon Harris reactor vessel head outermost nozzle penetration [3] that the hoop stress in the J-groove weld is greater than the axial stress at the same location, the preferential direction for cracking would be axial, or radial relative to the nozzle. It is postulated that a radial crack in the Alloy 82/182 weld metal would propagate by PWSCC, through the weld and butter, to the interface with the low alloy steel head material, where it is fully expected that such a crack would then blunt, or arrest, as discussed in Reference [4]. Since the vertical distance along the bored surface between the inside corner of the remnant J-groove weld and the point where the butter meets the head is more than two inches, a crack extending from the corner of the weld to the low alloy steel head would be very deep. Although primary water stress corrosion cracking would not extend into the head, it is further postulated that a small fatigue initiated flaw forms in the low alloy steel head and combines with the stress corrosion crack in the weld to form a large radial corner flaw that would propagate into the head by fatigue crack growth under cyclic loading conditions. Linear-elastic (LEFM) and elastic-plastic (EPFM) fracture mechanics procedures are utilized to evaluate this worst case flaw in the original J-groove weld and butter.
Key features of the fracture mechanics analysis are:
* This analysis applies specifically to the CRDM nozzle penetrations in the Shearon Harris Unit 1 reactor vessel closure head. A J-integral resistance curve is developed based on the Charpy V-notch upper-shelf energy for the Shearon Harris Unit 1 head plate material.
* Flaw growth is calculated for a 30 year period of operation, corresponding to 20 18-month fuel cycles.
* Final flaw acceptance is based on the available fracture toughness and ductile tearing resistance of the RVCH material considering the safety factors listed in Table 1-1.
* Since the same design is used at Shearon Harris Unit 1 for both the CRDM and CET nozzles and the CET nozzles are located within the same outermost penetration circle as the CRDM nozzles, the analysis performed herein for the CRDM nozzles is also applicable to the CET nozzles.
Table 1-1: Safety Factors for Flaw Acceptance Linear-Elastic Fracture Mechanics Operating Condition          Evaluation Method           Fracture Toughness / KI Normal/Upset            KIa fracture toughness                10 = 3.16 Emergency/Faulted          KIc fracture toughness                 2 = 1.41 Elastic-Plastic Fracture Mechanics Operating Condition          Evaluation Method            Primary        Secondary Normal/Upset           J/T based flaw stability           3.0            1.5 Normal/Upset          J0.1 limited flaw extension         1.5            1.0 Emergency/Faulted         J/T based flaw stability           1.5            1.0 Emergency/Faulted        J0.1 limited flaw extension         1.5            1.0 Page 9

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.0     ANALYTICAL METHODOLOGY A radial flaw at the inside corner of non-radial head penetration is evaluated based on a combination of linear elastic fracture mechanics (LEFM) and elastic-plastic fracture mechanics (EPFM), as outlined below.
: 1. Postulate radial flaws in the J-groove weld, extending from the inside corner of the penetration to the interface between the butter and head, as shown in Figure 2-1 and Figure 2-2 for the uphill and downhill sides of the penetration, respectively. Initial flaw size, ao, is arbitrarily characterized by the vertical distance along the uphill side penetration bore, from the inside surface of the cladding to the weld-to-butter/head interface, as shown Figure 2-1. For the constant depth J-groove design used for the Shearon Harris head, this same flaw depth is also used for the downhill side flaw evaluations.
: 2. Develop finite element models of the reactor vessel head in the vicinity of the outermost nozzle penetration, with crack tip elements along the interface between the Alloy 82/182 butter and the low alloy steel base metal. These models will be used to obtain stress intensity factors at various positions along the crack front for linearly superimposed residual and operating stresses.
: 3. Develop a mapping procedure to transfer stresses from an uncracked finite element stress model to the crack face of each crack model. This will enable stress intensity factors to be calculated for arbitrary stress distributions over the crack face utilizing the principle of superposition.
: 4. Calculate fatigue crack growth, in one year increments, for cyclic loading conditions using operational stresses from pressure and thermal loads. Since the stresses used in the fatigue crack growth analysis are the combined residual plus operating stresses, the effect of the residual stresses on fatigue crack growth is captured by the R ratio, or Kmin/Kmax. Starting from the stress intensity factor calculated by the finite element crack model for the initial flaw size, stress intensity factors are updated for each increment of crack growth by the square root of the flaw size.
: 5. Utilize the screening criteria of ASME Code Section XI, Appendix C to determine the failure mode and appropriate method of analysis (LEFM, EPFM, or limit load) for flaws in ferritic materials, considering the applied stress, temperature, and material toughness. For LEFM flaw evaluations, compare the stress intensity factor at the final flaw size to the available fracture toughness, with appropriate safety factors, as discussed in Section 2.2. When the material is more ductile and EPFM is the appropriate analysis method, evaluate flaw stability and crack driving force as described in Section 2.3. A primary stress limit analysis would be performed to satisfy the primary stress limits of the ASME Code, as described in Section 2.3.2.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure 2-1: Postulated Radial Flaw on Uphill Side Figure 2-2: Postulated Radial Flaw on Downhill Side Page 11

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.1      Stress Intensity Factor Solution Stress intensity factors for corner flaws at a non-radial nozzle penetration are best determined by finite element analysis using three-dimensional models with crack tip elements along the crack front.
Although loads can be applied to finite element crack models like any other structural model, the crack models were developed to serve as a flaw evaluation tool that could accept stresses from separate stress analyses. This strategy makes it possible, for example, to obtain pressure and thermal stresses from an independent thermal/structural analysis and then transfer these stresses to a crack model for flaw evaluations. Using the principle of superposition common to fracture mechanics analysis, the only stresses that need be considered for these flaw evaluations are the stresses on the crack face. A mapping procedure is developed to transfer stresses from a separate stress analysis to the crack face of the crack model.
2.1.1    Finite Element Crack Models Three-dimensional finite element models are developed for the reactor vessel head in the vicinity of the outermost nozzle penetration, by modeling a portion of the head, cladding, and butter with the ANSYS finite element computer program [5]. Since stresses increase with penetration angle, it is conservative to base the finite element models on the outermost nozzle penetration.
A three-dimensional finite element model is first constructed to represent an unflawed non-radial nozzle penetration in the reactor vessel head using the ANSYS SOLID186 20-node structural element.
Elements along the crack front are then replaced by a sub-model of crack tip elements along the interface between the Alloy 82/182 butter and the low alloy steel base metal. These elements consist of 20-node isoparametric elements that are collapsed to form a wedge with the appropriate mid-side nodes shifted to quarter-point locations to simulate the singularity at the crack tip. The final crack models are shown in Figure 2-3 and Figure 2-4 for the uphill and downhill sides of the nozzle, respectively.
Stress intensity factors will be obtained using the ANSYS CINT contour integral procedure at 17 positions along each crack front, as indicated in Figure 2-3 and Figure 2-4 for the two crack models.
Position 1 is located on the cladding surface, Position 3 at the cladding/base metal interface, Position 11 at the kink in the crack profile, and Position 17 is at the bored surface in the head.
2.1.2    Stress Mapping Stresses from the finite element stress model are mapped onto the crack faces of the uphill and downhill finite element crack models (Figure 2-3 and Figure 2-4). An ANSYS scripting language instruction (macro) has been developed to query the residual and operating stress models for nodal locations associated with each crack face node of the crack model. The nodal stress from the stress model is then transferred to the corresponding node on the crack model.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure 2-3: Finite Element Crack Model - Uphill Side Page 13

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure 2-4: Finite Element Crack Model - Downhill Side Page 14

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.1.3  Crack Growth Considerations The fundamental expression for the crack tip stress intensity factor is K I =  a Since each crack model is developed for a single flaw size, stress intensity factors are updated at each increment of crack growth by the square root of the flaw size; i.e.,
ai +1 K I ( a i +1 ) = K I (a i )                ,
ai where                                                   a = flaw size i = increment of crack growth.
Since the stress intensity factor is directly proportional to the magnitude of the stress and both residual and operating stresses decrease in the direction of crack growth, this procedure produces conservative estimates of stress intensity factor as the crack extends into the head and stresses diminish over the expanding crack face.
2.1.4  Plastic Zone Correction The Irwin plasticity correction is used to account for a moderate amount of yielding at the crack tip. For plane strain conditions, this correction is 2
1  K I (a) ry =                       ,           [ Ref. 6, Eqn. (2.63) ]
6   y where                    K I ( a ) = stress intensity factor based on the actual crack size, a y = material yield strength.
A stress intensity factor, K I (a e ) , is then calculated for an effective crack size, a e = a + ry ,
based on the same scaling technique utilized for crack growth; i.e, ae K I (a e ) = K I (a)          .
a Page 15

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.2     Linear Elastic Fracture Mechanics Section XI, Article IWB-3612 [11] requires that the applied stress intensity factor, KI, at the final flaw size be less than the available fracture toughness at the crack tip temperature, with appropriate safety factors, as outlined below.
Normal Conditions:                           K I < K Ia / 10 where KIa is the fracture toughness based on crack arrest.
Faulted Conditions:                           K I < K Ic / 2 where KIc is the fracture toughness based on crack initiation.
Section XI, Article IWB-3613 [11] provides alternate fracture toughness requirements for shell regions near structural discontinuities, such as nozzle penetrations, when the pressure does not exceed 20% of the design pressure and the temperature is not less than RTNDT + 60 &deg;F. Within these operational limits a lower safety factor may be used to evaluate fracture toughness margin. For the Shearon Harris Unit 1 reactor vessel head, the design pressure is [               ] psig [13] and the fracture toughness reference temperature is [          ] [9]. Thus for pressures at or below [        ] psig and crack tip temperatures at or above [          ] the acceptance criterion for applied stress intensity factor is as follows:
At pressures     [     ]  psig and temperatures         [      ]
K I < K Ia / 2 Page 16

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.3     Elastic-Plastic Fracture Mechanics Elastic-plastic fracture mechanics (EPFM) will be used as alterative acceptance criteria when the flaw related failure mechanism is unstable ductile tearing. This type of failure falls between rapid, non-ductile crack extension and plastic collapse. Linear elastic fracture mechanics (LEFM) would be used to assess the potential for non-ductile failure, whereas primary stress limit analysis would be used to check for plastic collapse.
2.3.1   Screening Criteria Screening criteria for determining failure modes in ferritic materials may be found in Appendix C of Section XI. Although Appendix C, Article C-4221 [11] contains specific rules for evaluating flaws in Class 1 ferritic piping, its screening criteria may be adapted to other ferritic components, such as the reactor vessel head, as follows:
Let,                                 Kr = KIapp / KIc Sr = max / f Then the appropriate method of analysis is determined by the following limits:
LEFM Regime:                              Kr / Sr  1.8 EPFM Regime:                     1.8 > Kr / Sr  0.2 Limit Load Regime:               0.2 > Kr / Sr 2.3.2   Primary Stress Limit Analysis While in most instances the screening criteria identify EPFM as the appropriate method of analysis, there are cases where low stress intensity factors (Kr) relative to the applied stress (Sr) places the analysis in the limit load regime. Such cases are analyzed through consideration of the primary stress limits of ASME Code Section III as embodied in the equation in Article NB-3324 [7] for the minimum required thickness (tmin) of the spherical closure head, PRo t min =       ,
2Sm where                                   P = design pressure,      [   ]  psig [13]
Ro = outside radius,     [         ] [1]
Sm = design stress intensity, 26.7 ksi [12]
A conservative primary stress limit analysis would be to limit the remaining net-section of the head after removal of the final volume of weld material (after fatigue crack growth) to the minimum required design thickness, tmin. This is equivalent to removing a uniform depth of material along the inner surface of the vessel to encompass the final flaw and comparing the remaining thickness to t min = 3.74 in.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 2.3.3   Flaw Stability and Crack Driving Force Elastic-plastic fracture mechanics analysis will be performed using a J-integral/tearing modulus (J-T) diagram to evaluate flaw stability under ductile tearing, where J is either the applied (Japp) or the material (Jmat) J-integral, and T is the tearing modulus, defined as (E/f2)(dJ/da). The crack driving force, as measured by Japp, is also checked against the J-R curve at a crack extension of 0.1 inch (J0.1).
Consistent with industry practice for the evaluation of flaws in partial penetration welds used to attach nozzles to vessels, different safety factors will be utilized for primary and secondary loads. Flaw stability assessments for normal and upset conditions will consider a safety factor of 3 on the stress intensity factor due to primary (pressure) stresses and a safety factor of 1.5 for secondary (residual plus thermal) stresses. The crack driving force will be calculated using safety factors of 1.5 and 1 for primary and secondary stresses, respectively. For EPFM analysis of faulted conditions, safety factors of 1.5 and 1 will be used for flaw stability assessments and 1.5 and 1 for evaluations of crack driving force.
The general methodology for performing an EPFM analyses is outlined below.
Let                                             E = E/(1-2)
Final flaw depth = a Total applied KI = KIapp KI due to pressure (primary) = KIp KI due to residual plus thermal (secondary) = KIs = KIapp - KIp Safety factor on primary loads = SFp Safety factor on secondary loads = SFs For small scale yielding at the crack tip, a plastic zone correction is used to calculate an effective flaw depth based on ae = a + [1/(6)] [ (KIp + KIs) / y ]2, which is used to update the stress intensity factors based on ae K 'Ip = K Ip a
ae and         K'Is = K Is        .
a The applied J-integral is then calculated using the relationship Japp = (SFp*KIp + SFs*KIs)2/E.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
The final parameter needed to construct the J-T diagram is the tearing modulus. The applied tearing modulus, Tapp, is calculated by numerical differentiation for small increments of crack size (da) about the final crack size (a), according to E  Japp (a + da)  Japp (a  da)
Tapp =                                   .
2f               2(da)
Using the power law expression for the J-R curve, JR = C(a)m ,
the material tearing modulus, Tmat, can be expressed as Tmat = (E/f2)Cm(a)m-1.
Constructing the J-T diagram, J
Unstable Region Tapp  Tmat Applied Instability Point Material Stable Region Tapp < Tmat T
flaw stability is demonstrated at an applied J-integral when the applied tearing modulus is less than the material tearing modulus. Alternately, the applied J-integral is less than the J-integral at the point of instability.
To complete the EPFM analysis, it must be shown that the applied J-integral is less than J0.1, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 3.0     ASSUMPTIONS This section discusses assumptions and modeling simplifications applicable to the present analysis.
3.1     Unverified Assumptions This analysis contains the following two assumptions used in Appendix C for Nozzles 30, 40 and 51 that must be verified before structural integrity of the ASME Code Class 1 Reactor Vessel is assured.
: 1) The RV head wall thickness at any of the three penetrations (30, 40 and 51) is assumed to be no less than [        ] inches.
: 2) The J-groove weld size (in terms of cross-sectional area) of penetration 37 is assumed for penetrations 30 and 40; the J-groove weld size of penetration 49 is assumed for penetration 51.
3.2     Justified Assumptions The austenitic cladding is assumed to be adequately represented by 18Cr-8Ni (Type 304) stainless steel material.
In the body of the document, the size of the J-groove weld prep and the thickness of the buttering are based on nominal dimensions. This is considered to be standard practice in stress analysis and fracture mechanics analysis. It is conservatively assumed that the postulated flaw extends through the entire J-groove weld and butter.
In Appendix C, the crack growth areas at the three penetrations 30, 40 and 51 are estimated by the crack growth areas at Nozzles 14 and 37 (Figures C8 to C10). A review of Figures C8 to C10 indicates that closer the nozzle to the head center higher the crack growth area results. Therefore the crack growth area of Nozzle 14 for 15 years operation is taken as the bounding case for the three nozzles. A linear crack grown is assumed in the 15 years which is conservative, as the crack grown area in earlier years is less than that in later years.
3.3     Modeling Simplifications The finite element computer models used to generate residual stresses do not include the ID temper bead repair weld. This is deemed to be an appropriate modeling simplification since compressive stresses induced in the material adjacent to the repair weld would lower stresses on the uphill side of the J-groove weld (in close proximity to the repair weld) and have negligible effect on the downhill side of the J-groove weld (far removed from the repair weld).
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 4.0     DESIGN INPUTS This section provides basic input data needed to perform a fatigue crack growth analysis and a flaw evaluation of the final flaw size.
4.1     Materials 4.1.1   Mechanical and Thermal Properties Table 4-1, Table 4-2, and Table 4-3 list the temperature dependent values of modulus of elasticity (E),
Poissons ratio (), and coefficient of thermal expansion () properties used in the finite element crack models. These properties are obtained from the ASME Code, Section II [8], except for Poissons ratio, where 0.3 is a typical value used in structural analysis. The flow stress in Table 4-1 is the average of the yield and ultimate strengths.
Component                                  Material Head                               SA-533, Grade B Class 1 [Ref. 2, Par. 6.1.1]
Cladding                           use Type 304 stainless steel (SA-240)
J-groove weld filler               Equivalent to Alloy 600, SB-167 [Ref. 2, Par. 6.1.5]
J-groove weld butter               use Alloy 600, SB-167 Table 4-1: Material Properties for Head Component                                                   Head Material                             SA-533 Grade B Class 1 (Mn-1/2Mo-1/2Ni)
Temperature         E (106 psi)           (10-6 in./in./oF)    y (ksi)    u (ksi)      f (ksi) 70              29.20       0.3            7.0              50.0         80.0          65.0 100              29.04       0.3            7.1              50.0         80.0          65.0 150              28.77       0.3            7.2              48.1         80.0          64.1 200              28.50       0.3            7.3              47.0         80.0          63.5 250              28.25       0.3            7.3              46.2         80.0          63.1 300              28.00       0.3            7.4              45.5         80.0          62.8 350              27.70       0.3            7.5              44.9         80.0          62.4 400              27.40       0.3            7.6              44.2         80.0          62.1 450              27.20       0.3            7.6              43.7         80.0          61.9 500              27.00       0.3            7.7              43.2         80.0          61.6 550              26.70       0.3            7.8              42.7         80.0          61.3 600              26.40       0.3            7.8              42.1         80.0          61.1 650              25.85       0.3            7.9              41.5         80.0          60.8 700              25.30       0.3            7.9              40.7         80.0          60.4 Page 21

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table 4-2: Material Properties for Weld Metal Component                                    Weld Butter and Weld Filler Material                     Use Alloy 600, SB-167 (72Ni-15Cr-8Fe) - UNS N06600 Temperature                E (106 psi)                                     (10-6 in./in./oF) 70                      31.00                     0.3                        6.8 100                      30.82                     0.3                        6.9 150                      30.51                     0.3                        7.0 200                      30.20                     0.3                        7.1 250                      30.00                     0.3                        7.2 300                      29.80                     0.3                        7.3 350                      29.65                     0.3                        7.4 400                      29.50                     0.3                        7.5 450                      29.25                     0.3                        7.6 500                      29.00                     0.3                        7.6 550                      28.85                     0.3                        7.7 600                      28.70                     0.3                        7.8 650                      28.45                     0.3                        7.8 700                      28.20                     0.3                        7.9 Table 4-3: Material Properties for Cladding Component                                            Cladding Material                             Use Type 304 Stainless Steel (18Cr-8Ni) 6 Temperature                E (10 psi)                                      (10-6 in./in./oF) 70                       28.30                    0.3                        8.5 100                       28.14                    0.3                        8.6 150                       27.87                    0.3                        8.8 200                       27.60                    0.3                        8.9 250                       27.30                    0.3                        9.1 300                       27.00                    0.3                        9.2 350                       26.75                    0.3                        9.3 400                       26.50                    0.3                        9.5 450                       26.15                    0.3                        9.6 500                       25.80                    0.3                        9.7 550                       25.55                    0.3                        9.8 600                       25.30                    0.3                        9.8 650                       25.05                    0.3                        9.9 700                       24.80                    0.3                       10.0 Page 22

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 4.1.2   Toughness Properties The reference temperature for nil-ductility transition for the SA-533 Grade B Class 1 plate material in the dome portion of the Shearon Harris reactor vessel closure head is reported as RTNDT = [               ] [9]
and the Charpy upper-shelf energy is [                ] [9] in the transverse (weak) direction. Based on the welding procedure qualification record [10] for the ID temperature bead weld, a temperature of +5 &deg;F should be added to the RTNDT of the base material to account for embrittlement in the heat affected zone, so that the effective RTNDT is [         ] for flaw evaluations in the head.
4.1.3   Fracture Toughness From Article A-4200 of Section XI [11], the lower bound KIa fracture toughness for crack arrest can be expressed as KIa = 26.8 + 12.445 exp [ 0.0145 (T - RTNDT) ],
where T is the crack tip temperature, RTNDT is the reference nil-ductility temperature of the material, KIa is in units of ksiin, and T and RTNDT are in units of &deg;F. In the present flaw evaluations, KIa is limited to a maximum value of 200 ksiin (upper-shelf fracture toughness). Using the above equation with an RTNDT of [          ] KIa equals 200 ksiin at a crack tip temperature of [          ].
A higher measure of fracture toughness is provided by the KIc fracture toughness for crack initiation, approximated in Article A-4200 of Section XI [11] by KIc = 33.2 + 20.734 exp [ 0.02 (T - RTNDT) ].
4.1.4   J-integral Resistance Curve The J-integral resistance (J-R) curve, needed for the EPFM method of analysis, is obtained from the following power law expression for nuclear reactor pressure vessel steels, JR = C(a)m, where the coefficient, C, and exponent, m, depend on the Charpy V-notch upper-shelf energy, CVN, and the flow stress, o or f, as shown in Figure 4-1 and Figure 4-2.
Using the above referenced Charpy V-notch upper-shelf energy correlation for the J-integral resistance curve with a Charpy V-notch upper-shelf energy of [                     ] the coefficients of the power law equation over a wide range of temperatures are:
C=     [      ]
m=     [      ]
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure 4-1: Correlation of Coefficient, C, of Power Law with Charpy V-Notch Upper Shelf Energy Figure 4-2: Correlation of Exponent, m, of Power Law with Coefficient, C, and Flow Stress, o Page 24

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 4.1.5   Fatigue Crack Growth Rate Flaw growth due to cyclic loading is calculated using the fatigue crack growth rate model from Article A-4300 of Section XI [11],
da
                                              = C o (  K I )n ,
dN where KI is the stress intensity factor range in ksiin and da/dN is in inches/cycle. The crack growth rates for a surface flaw will be used for the evaluation of the corner crack since it is assumed that the degraded condition of the J-groove weld and butter exposes the low alloy steel head material to the primary water environment.
The following equations from Section XI [11] are used to model fatigue crack growth.
KI = KImax - KImin R = KImin / KImax 0  R  0.25:           KI < 17.74, n = 5.95 Co = 1.02 x 10-12 x S S = 1.0 KI  17.74, n = 1.95 Co = 1.01 x 10-7 x S S = 1.0 0.25  R  0.65:        KI < 17.74 [ (3.75R + 0.06) / (26.9R - 5.725) ]0.25, n = 5.95 Co = 1.02 x 10-12 x S S = 26.9R - 5.725 KI  17.74 [ (3.75R + 0.06) / (26.9R - 5.725) ]0.25, n = 1.95 Co = 1.01 x 10-7 x S S = 3.75R + 0.06 0.65  R < 1.0:         KI < 12.04, n = 5.95 Co = 1.02 x 10-12 x S S = 11.76 KI  12.04, n = 1.95 Co = 1.01 x 10-7 x S S = 2.5 Page 25

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 4.2     Basic Geometry The reactor vessel head and CRDM nozzle penetration are described by the following key dimensions:
Spherical radius to base metal                = [          ]   in. [9]
Head thickness                                =  [        ]    in. [9]
Cladding thickness                            =  [        ]    in. [9]
Butter thickness                              =  [        ]    in. [9]
Penetration bore                              =  [        ]    in. [9]
Horizontal radius to outermost penetration =    [          ]    in. [9]
Penetration angle at outermost nozzle         = [       ] deg. (derived*)
                                                 * (sin-1(horizontal radius/spherical radius))
4.3     Operating Transients Based on bounding transients developed for the companion ASME Code Section III fatigue stress analysis [12], fatigue crack growth will be calculated for the normal and upset condition transients listed in Table 4-4. Since crack growth will be calculated in one-year increments, the number of cycles is obtained by dividing the forty-year design life cycles by 40. While not physically meaningful, a fractional yearly cycle count is computationally acceptable since it is merely used to determine an increment of crack growth from a calculated value of da/dN.
Table 4-5 lists the emergency and faulted condition transients applicable to Shearon Harris reactor vessel components [13]. From a review of the pressure and temperature time-history definitions for these transients, it is clear that the large LOCA and large steam line break transients would bound the remaining transients for emergency and faulted condition flaw evaluations.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table 4-4: Bounding Transients for Normal and Upset Conditions Table 4-5: Emergency and Faulted Condition Transients
* Bounding transients to be considered in emergency and faulted condition flaw evaluations Page 27

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 4.4     Applied Stresses Two sources of applied stress are considered for the present flaw evaluations, residual stresses from welding and stresses that occur during plant operation.
4.4.1   Residual Stresses Residual stresses are obtained from a three-dimensional elastic-plastic finite element stress analysis [3]
that simulates fabrication of the outermost nozzle to head partial penetration weld and the effect of subsequent hydrostatic tests and operating cycles on stresses in the welded joint. It is widely accepted that stresses at the outermost CRDM nozzle location conservatively bound stresses at all other nozzle locations exhibiting a smaller penetration angle (the angle between the nozzle and inside surface of the head on the downhill side of the penetration). Stresses are transferred from the finite element residual stress model in the form of nodal arrays contained in ANSYS parameter save files.
4.4.2   Operating Stresses Operating stresses are obtained from the three-dimensional finite element stress analysis [12] used to qualify the nozzle repair to ASME Code Section III requirements. Hoop stresses from the Section III analysis are conservatively superimposed on the residual stresses to represent the crack face opening stresses during operation. Stresses are transferred from the finite element operating stress model in the form of nodal arrays contained in ANSYS parameter save files. Pressure is added to the operating stresses to account for the additional loading on the crack face due to pressure.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 5.0    COMPUTER USAGE This section describes computer resources, software testing, and stored computer files.
5.1    Hardware/Software 5.2    Installation/Validation Test Page 29

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table 5-1: Test Case Results Verification Problem VM256 Fracture Mechanics Analysis of a Crack in a Plate File: vm256.vrt
---------------------------------------- VM256 RESULTS COMPARISON ----------------------------------------
l TARGET l ANSYS l RATIO USING PLANE 183 ELEMENT (2-D ANALYSIS)
KI            1.0249        1.0038        0.979 USING SOLID 185 ELEMENT (3-D ANALYSIS)
KI            1.0249        1.0383        1.013 USING SOLID 186 ELEMENT - SURFACE CRACK (3-D ANALYSIS)
KI            1.4000        1.4132        1.009 Page 30

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 5.3     Computer Files The computer files listed below are stored in the AREVA ColdStor repository in the directory
\cold\41304\32-9176350-000\official.
ANSYS Models ColdStor       ColdStor File Name                  Description                         Storage         Storage      Checksum Date           Time
[
[                 ]                                            04-15-12       09:01:06         22856
                                                     ]
[
[                    ]                                         04-15-12       09:00:56         18509
                                                        ]
ANSYS Macros ColdStor       ColdStor File Name                      Description                     Storage         Storage      Checksum Date           Time
[                      ]       [                    ]          04-15-12       09:01:22         15845
[                          ]   [                       ]       04-15-12       09:01:21         11056 ANSYS Input Files ColdStor       ColdStor File Name                          Description                 Storage         Storage      Checksum Date           Time
[
[                        ]                                     04-15-12       09:01:42         32454
                                                 ]
[
[                            ]                                 04-15-12       09:01:41         08793
                                                   ]
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
ANSYS Result Files for Uphill Stress Intensity Factors File Name                                                      ColdStor       ColdStor Loading Condition                   Storage         Storage      Checksum Date           Time 04-15-12       09:04:35         22371 04-15-12       09:04:07         16344 04-15-12       09:04:03         19578 04-15-12       09:04:10         45340 04-15-12       09:04:10         36382 04-15-12       09:04:09         50736 04-15-12       09:04:08         46959 04-15-12       09:04:09         35163 04-15-12       09:04:07         46631 04-15-12       09:04:04         15882 04-15-12       09:04:05         54622 04-15-12       09:04:08         25345 04-15-12       09:04:04         17221 04-15-12       09:04:03         01071 04-15-12       09:04:06         55706 04-15-12       09:04:05         62230 04-15-12       09:04:06         06099 Page 32

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
ANSYS Result Files for Downhill Stress Intensity Factors Loading Condition                   ColdStor       ColdStor File Name                                                      Storage         Storage      Checksum Date           Time 04-15-12       09:04:34         59428 04-15-12       09:03:13         59492 04-15-12       09:03:10         49475 04-15-12       09:03:16         50217 04-15-12       09:03:17         37165 04-15-12       09:03:16         34304 04-15-12       09:03:15         19734 04-15-12       09:03:16         29947 04-15-12       09:03:14         23156 04-15-12       09:03:11         35585 04-15-12       09:03:12         60112 04-15-12       09:03:15         42106 04-15-12       09:03:11         65275 04-15-12       09:03:10         04872 04-15-12       09:03:13         36168 04-15-12       09:03:12         09825 04-15-12       09:03:13         31095 Page 33

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Excel Spreadsheets Description                  ColdStor       ColdStor File Name                                                      Storage         Storage      Checksum Date           Time 04-15-12       09:06:58         58102 04-15-12       09:06:57         00505 04-15-12       09:06:57         38955 04-15-12       09:06:57         63694 04-15-12       09:06:56         21575 04-15-12       09:06:56         25218 ANSYS Test Cases ColdStor       ColdStor File Name                      Description                     Storage         Storage      Checksum Date           Time
[
[          ]                                                   04-15-12       09:07:25         49343
                                       ]
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.0      CALCULATIONS Propagation of a postulated initial flaw in the J-groove weld and butter is calculated to determine the final flaw size after 30 years of service. Flaw evaluations are then performed to assess the acceptability of the final flaw size.
6.1      Initial Flaw Size It is both difficult and unnecessary to prescribe initial flaw sizes for the non-classical flaw shapes comprising the postulated uphill and downhill flaws in the J-groove weld and butter. Since the explicit finite element crack models described in Section 2.1.1 were developed to realistically capture the basic geometry of the J-shaped flaws, any characteristic dimension of the flaws may be used to track flaw growth during cyclic fatigue. The constant depth J-groove design suggests that a common value can be utilized to describe the initial depth of the uphill and downhill flaws. Accordingly, the vertical distance along the uphill side penetration bore, from the inside surface of the cladding to the weld-to-butter/head interface, is used to define the initial flaw size, ao (as shown Figure 2-1). From the uphill crack model, the initial flaw size value is determined to be 2.1482.
As discussed in Section 2.1.3, crack tip stress intensity factors are calculated directly from the finite element crack models for the initial flaw size and then updated based on incremental crack growth according to ai +1 K I ( a i +1 ) = K I (a i )        ,
ai so that after the first increment of crack growth, a1 K I ( a i ) = K I (a 0 )      .
a0 6.2      Fatigue Crack Growth Although it is believed that a PWSCC flaw would be confined to the J-groove weld and butter, it is postulated that a fatigue flaw would initiate in the low alloy steel head, combine with the PWSCC flaw, and propagate farther into the head under cyclic loads. Fatigue crack growth is calculated from finite element based stress intensity factors using residual and operational stresses from References [3] and
[12], respectively. The actual flaw growth calculations are presented in Appendix A for the uphill flaw and Appendix B for the downhill flaw, along with a comparison of the final stress intensity factor for each transient with the fracture toughness requirements of Section XI. Table 6-1 and Table 6-2 summarize the flaw growth analyses for the uphill and downhill sides of the flaw, respectively. These tables serve several purposes; they present the final flaw size at the end the design life, they compare stress intensity factors at the final flaw size with LEFM acceptance criteria, and they serve as a means of screening for the worst case loading conditions and stress intensity factors for subsequent EPFM analysis.
Crack growth is calculated in one-year increments for each of the analyzed transients, while uniformly distributing the growth over the service life by linking the yearly crack growth between the crack growth tables in Appendix A for the uphill flaw and the tables in Appendix B for the downhill flaw.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Stress intensity factors are provided in the crack growth tables for all locations along the postulated crack fronts, including the cladding. It is apparent from the tables in Appendix A that on the uphill side of the penetration, the highest stress intensity factors in the low alloy steel head occur near the cladding surface (Position 3) for residual stresses and near the penetration bore (Position 16) for operating stresses. It is noted that due to residual tensile strain in the cladding material, cladding stresses and the associated stress intensity factors may be higher than those in the adjacent head material. However, stress intensity factors within the stainless steel cladding portion of the crack front need not be considered in the evaluation of the potential for non-ductile failure of the low alloy steel head. Fatigue crack growth analysis performed for both Position 3 and 16 showed that the operating stresses controlled, producing higher final stress intensity factors at Position 16. Thus Position 16 on the uphill side will be used to calculate fatigue crack growth and evaluate the final stress intensity factors for each transient considering flaw acceptance standards for the low alloy steel head material. The downhill side crack growth tables in Appendix B, use Position 7 to calculate crack growth and evaluate fracture toughness margins since the highest stress intensity factors occur either at or near this crack front position for both the residual and operating stresses.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table 6-1: LEFM Fracture Toughness Margins for Uphill Side Period of Operation:      Time =       30     years Flaw Size:                    a=
Loading Conditions Temperature Pressure Fracture Toughness, KIc           200.0     200.0    98.0   200.0  200.0  200.0      63.5      200.0  200.0  200.0   200.0  200.0   200.0  63.5    200.0  ksiin Fracture Toughness, KIa           200.0     85.5     55.2   200.0  200.0  200.0      43.2      200.0  200.0  200.0   200.0  200.0   200.0  43.2    200.0  ksiin Position 16 KI(a)                  73.546    50.736   31.531 78.325 79.225 94.843     64.199    82.085 72.962 109.077 73.540 96.413  89.569 233.116 190.113 ksiin ae                    3.1971    3.0955   3.0602 3.2163 3.2219 3.2883     3.1266    3.2381 3.1944 3.3708  3.1972 3.2988  3.2369 4.1923  3.9097  in.
KI(ae)                  75.434    51.204   31.640 80.576 81.573 98.653     65.117    84.729 74.802 114.874 75.428 100.448 92.437 273.795 215.630 ksiin Margin = KIc / KI(ae)            n/a       n/a      n/a    n/a    n/a    n/a        n/a        n/a   n/a    n/a     n/a    n/a     n/a   0.23    0.93 Margin = KIa / KI(ae)           2.65      1.67     1.75   2.48   2.45   2.03       0.66      2.36   2.67   1.74    2.65   1.99    2.16    n/a     n/a Required Margin               3.16      1.41     1.41   3.16   3.16   3.16       1.41      3.16   3.16   3.16    3.16   3.16    3.16   1.41    1.41 Acceptable by LEFM?               No        Yes     Yes     No     No     No         No         No    No     No      No     No      No     No      No where:        ae = a + 1/(6) [KI(a)/Sy] 2 KI(ae) = KI(a)*(ae/a)
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table 6-2: LEFM Fracture Toughness Margins for Downhill Side Period of Operation:      Time =        30    years Flaw Size:                    a=
Loading Conditions Temperature Pressure Fracture Toughness, KIc           200.0     200.0  98.0    200.0   200.0  200.0      63.5      200.0  200.0  200.0  200.0  200.0  200.0  63.5   200.0 ksiin Fracture Toughness, KIa           200.0     85.5   55.2    200.0   200.0  200.0      43.2      200.0  200.0  200.0  200.0  200.0  200.0  43.2   200.0 ksiin Position 7 KI(a)                  56.220    22.499 17.076  58.314  58.716 65.540     55.130    59.913 55.969 72.039 56.216 66.756 65.585 77.409 63.626 ksiin ae                    2.3201    2.2388 2.2339  2.3259  2.3279 2.3467     2.2923    2.3337 2.3191 2.3724 2.3201 2.3515 2.3338 2.3549 2.3255 in.
KI(ae)                  57.373    22.555 17.099  59.585  60.021 67.267     55.923    61.322 57.105 74.341 57.369 68.584 67.127 79.587 65.007 ksiin Margin = KIc / KI(ae)            n/a       n/a    n/a      n/a    n/a    n/a        n/a        n/a   n/a    n/a    n/a    n/a    n/a   0.80   3.08 Margin = KIa / KI(ae)           3.49      3.79   3.23     3.36   3.33   2.97       0.77      3.26   3.50   2.69   3.49   2.92   2.98    n/a    n/a Required Margin               3.16      1.41   1.41     3.16   3.16   3.16       1.41      3.16   3.16   3.16   3.16   3.16   3.16   1.41   1.41 Acceptable by LEFM?               Yes       Yes   Yes      Yes     Yes    No         No        Yes    Yes    No     Yes    No     No     No     Yes where:        ae = a + 1/(6) [KI(a)/Sy] 2 KI(ae) = KI(a)*(ae/a)
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.3     LEFM Flaw Evaluations Results of the linear-elastic fracture mechanics flaw evaluations are summarized below for the final flaw size after 30 years of crack growth.
6.3.1   Normal and Upset Conditions Listed below are the controlling LEFM fracture toughness margins from the fatigue crack growth tables.
Uphill Side             Downhill Side Flaw Sizes Initial flaw size,                                ai = 2.148 in.             2.148 in.
Final flaw size,                                  af =  [         ]  in.      [         ]  in.
Flaw growth,                                     a =   [         ]  in.      [         ]  in.
Operating Conditions                                      Reactor Trip              Reactor Trip Temperature,                                       T=   [      ]   o F         [      ]   o F
Fracture toughness,                              KIa = 200.0 ksiin          200.0 ksiin Final stress intensity factor,                KI(af) = 109.1 ksiin          72.04 ksiin Effective flaw size,                              ae = 3.371 in.             2.372 in.
Effective stress intensity factor,            KI(ae) = 114.9 ksiin          74.34 ksiin Fracture toughness margin (> 3.16),       KIa/KI(ae) = 1.74                  2.69 Low Temperature Conditions                                  Refueling                Refueling Temperature,                                       T=   [    ]   o F           [    ]   o F
Fracture toughness,                              KIa = 43.2 ksiin           43.2 ksiin Final stress intensity factor,                KI(af) = 64.20 ksiin          55.13 ksiin Effective flaw size,                              ae = 3.127 in.             2.292 in.
Effective stress intensity factor,            KI(ae) = 65.12 ksiin          55.92 ksiin Fracture toughness margin (> 1.41),       KIa/KI(ae) = 0.66                  0.77 Since the above fracture toughness margins for the controlling normal and upset conditions are less than the Code required minimums, EPFM flaw evaluations will be performed in Section 6.4 to account for the ductile behavior of the low alloy steel under stable crack propagation.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.3.2   Faulted Conditions The bounding faulted condition stress intensity factors are evaluated below for the final flaw size after 30 years of crack growth.
Uphill Side             Downhill Side Flaw Sizes Final flaw size,                                  af =  [         ]  in.      [         ]  in.
Large Loss of Coolant Accident Temperature,                                       T=   [    ]   o F           [    ]   o F
Fracture toughness,                              KIc = 63.5 ksiin           63.5 ksiin Final stress intensity factor,                KI(af) = 233.1 ksiin          77.41 ksiin Effective flaw size,                              ae = 4.192 in.             2.355 in.
Effective stress intensity factor,            KI(ae) = 273.8 ksiin          79.59 ksiin Fracture toughness margin (> 1.41),       KIc/KI(ae) = 0.23                  0.80 Large Steam Line Break Temperature,                                       T=   [      ]   o F         [      ]   o F
Fracture toughness,                              KIc = 200.0 ksiin          200.0 ksiin Final stress intensity factor,                KI(af) = 190.1 ksiin          63.63 ksiin Effective flaw size,                              ae = 3.910 in.             2.326 in.
Effective stress intensity factor,            KI(ae) = 215.6 ksiin          65.01 ksiin Fracture toughness margin (> 1.41),       KIc/KI(ae) = 0.93                  3.08 Since some of the above fracture toughness margins for the controlling faulted conditions are less than the Code required minimums, EPFM flaw evaluations will be performed in Section 6.4 to account for the ductile behavior of the low alloy steel under stable crack propagation.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.4     EPFM Flaw Evaluations The EPFM analysis is used to evaluate the limiting loading conditions that fail the LEFM-based Code margins. In this context, EPFM is meant to include either classical elastic-plastic fracture mechanics or primary stress limit analysis, as applicable.
6.4.1   Operating Conditions Uphill Side              Downhill Side Controlling Conditions                                      Reactor Trip               Reactor Trip Flaw size at 30 years of service,                           a=    [        ]  in.         [         ]  in.
Effective flaw size,                                       ae = 3.371 in.                2.373 in.
SCREENING PROCEDURE T=    [      ]  o F            [       ]  o F
E = 27200 ksi                27200 ksi
                                                             = 0.3                      0.3 E = E/(1-2) = 29890 ksi                 29890 ksi y = 43.6 ksi                 43.6 ksi u = 80.0 ksi                 80.0 ksi f = 61.8 ksi                61.8 ksi Crack initiation toughness,                                KIc = 200.0 ksiin            200.0 ksiin Total applied KI,                                      KI(ae) = 114.9 ksiin             74.34 ksiin Kr = KI(ae) / KIc = 0.574                    0.372 From finite element analysis, the maximum crack face stresses due to residual stress, pressure, and thermal gradients are max = 68.3 ksi                  70.9 ksi Sr = max / f = 1.105                    1.147 Screening ratio,                                     Kr / Sr = 0.520                   0.324 (1.8 > Kr / Sr  0.2)        (1.8 > Kr / Sr  0.2)
Analysis regime:                                            EPFM                        EPFM Page 41

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
EPFM ANALYSIS Uphill Side           Downhill Side Controlling Conditions                                       Reactor Trip            Reactor Trip KI primary,                                              KIp(a) = 190.8 ksiin         86.02 ksiin KI secondary (residual plus thermal),                    KIs(a) = 68.19 ksiin         65.05 ksiin Total KI,                                                 KI(a) = 259.0 ksiin         151.1 ksiin Effective flaw size,                                         ae = 4.912 in.            2.865 in.
Total KI,                                               KI(ae) = 329.3 ksiin         171.3 ksiin Table A-14 (uphill side) and Table B-14 (downhill side) develop all the data necessary to construct J-T diagrams for the controlling operating conditions. The J-T diagrams are presented in Figures A-1 and B-1 for the uphill and downhill sides, respectively.
Uphill Side:
It can be seen from Table A-14 that for an applied J-integral of 3.628 kips/in, corresponding to safety factors of 3 and 1.5, the applied tearing modulus, 8.502, is less than the material tearing modulus, 50.70, indicating flaw stability. Alternately, the applied J-integral is less than the J-integral, 8.181 kips/in, at the point of instability. For safety factors of 1.5 and 1, the applied J-integral of 0.785 kips/in is less than the J0.1 value of 2.473 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
Downhill Side:
Table B-14 shows that for an applied J-integral of 0.982 kips/in, corresponding to safety factors of 3 and 1.5, the applied tearing modulus, 3.139, is less than the material tearing modulus, 242.0, indicating flaw stability. The applied J-integral is also less than the J-integral, 7.102 kips/in, at the point of instability.
For safety factors of 1.5 and 1, the applied J-integral of 0.273 kips/in is less than the J0.1 value of 2.473 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.4.2   Low Temperature Conditions Uphill Side             Downhill Side Controlling Conditions                                      Refueling                 Refueling Flaw size at 30 years of service,                         a=    [         ] in.         [         ]  in.
Effective flaw size,                                     ae = 3.127 in.                2.292 in.
SCREENING PROCEDURE T=    [     ]  o F             [     ]  o F
E = 29200 ksi                29200 ksi
                                                           = 0.3                      0.3 2
E = E/(1- ) = 32080 ksi                 32080 ksi y = 50.0 ksi                 50.0 ksi u = 80.0 ksi                 80.0 ksi f = 65.0 ksi                65.0 ksi Crack initiation toughness,                              KIc = 63.5 ksiin             63.5 ksiin Total applied KI,                                    KI(ae) = 65.12 ksiin             55.92 ksiin Kr = KI(ae) / KIc = 1.025                    0.880 From finite element analysis, the maximum crack face stresses due to residual stress, pressure, and thermal gradients are max = 59.1 ksi                  49.5 ksi Sr = max / f = 0.909                    0.762 Screening ratio,                                   Kr / Sr = 1.127                   1.156 (1.8 > Kr / Sr  0.2)        (1.8 > Kr / Sr  0.2)
Analysis regime:                                          EPFM                        EPFM Page 43

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
EPFM ANALYSIS Uphill Side           Downhill Side Controlling Conditions                                         Refueling               Refueling KI primary,                                              KIp(a) = 0.0 ksiin           0.0 ksiin KI secondary (residual plus thermal),                    KIs(a) = 96.30 ksiin         82.70 ksiin Total KI,                                                 KI(a) = 96.30 ksiin         82.70 ksiin Effective flaw size,                                         ae = 3.236 in.            2.373 in.
Total KI,                                               KI(ae) = 99.37 ksiin         85.35 ksiin Table A-15 (uphill side) and Table B-15 (downhill side) develop all the data necessary to construct J-T diagrams for the controlling operating conditions. The J-T diagrams are presented in Figures A-2 and B-2 for the uphill and downhill sides, respectively.
Uphill Side:
It can be seen from Table A-15 that for an applied J-integral of 0.308 kips/in, corresponding to safety factors of 3 and 1.5, the applied tearing modulus, 0.700, is less than the material tearing modulus, 942.9, indicating flaw stability. Alternately, the applied J-integral is less than the J-integral, 8.179 kips/in, at the point of instability. For safety factors of 1.5 and 1, the applied J-integral of 0.132 kips/in is less than the J0.1 value of 2.474 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
Downhill Side:
Table B-15 shows that for an applied J-integral of 0.227 kips/in, corresponding to safety factors of 3 and 1.5, the applied tearing modulus, 0.704, is less than the material tearing modulus, 1357, indicating flaw stability. The applied J-integral is also less than the J-integral, 7.101 kips/in, at the point of instability.
For safety factors of 1.5 and 1, the applied J-integral of 0.097 kips/in is less than the J0.1 value of 2.474 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.4.3   Faulted Conditions Uphill Side             Downhill Side Controlling Conditions                                       LLOCA                      LLOCA Flaw size at 30 years of service,                         a=    [         ] in.         [         ]  in.
Effective flaw size,                                     ae = 4.192 in.                2.355 in.
SCREENING PROCEDURE T=    [     ]  o F             [     ]  o F
E = 29200 ksi                29200 ksi
                                                           = 0.3                      0.3 2
E = E/(1- ) = 32080 ksi                 32080 ksi y = 50.0 ksi                 50.0 ksi u = 80.0 ksi                 80.0 ksi f = 65.0 ksi                65.0 ksi Crack initiation toughness,                              KIc = 63.5 ksiin             63.5 ksiin Total applied KI,                                    KI(ae) = 273.8 ksiin             79.59 ksiin Kr = KI(ae) / KIc = 4.310                    1.253 From finite element analysis, the maximum crack face stresses due to residual stress, pressure, and thermal gradients are max = 198.3 ksi                 163.2 ksi Sr = max / f = 3.051                    2.511 Screening ratio,                                   Kr / Sr = 1.413                   0.499 (1.8 > Kr / Sr  0.2)        (1.8 > Kr / Sr  0.2)
Analysis regime:                                          EPFM                        EPFM Page 45

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
EPFM ANALYSIS Uphill Side           Downhill Side Controlling Conditions                                          LLOCA                   LLOCA KI primary,                                              KIp(a) = 2.596 ksiin         1.170 ksiin KI secondary (residual plus thermal),                    KIs(a) = 231.4 ksiin         76.63 ksiin Total KI,                                                 KI(a) = 234.0 ksiin         77.80 ksiin Effective flaw size,                                         ae = 4.201 in.            2.356 in.
Total KI,                                               KI(ae) = 275.1 ksiin         80.01 ksiin Table A-16 (uphill side) and Table B-16 (downhill side) develop all the data necessary to construct J-T diagrams for the controlling operating conditions. The J-T diagrams are presented in Figures A-3 and B-3 for the uphill and downhill sides, respectively.
Uphill Side:
It can be seen from Table A-16 that for an applied J-integral of 2.359 kips/in, corresponding to safety factors of 1.5 and 1, the applied tearing modulus, 5.364, is less than the material tearing modulus, 82.38, indicating flaw stability. Alternately, the applied J-integral is less than the J-integral, 8.179 kips/in, at the point of instability. For safety factors of 1.5 and 1, the applied J-integral of 2.359 kips/in is less than the J0.1 value of 2.474 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
Downhill Side:
Table B-16 shows that for an applied J-integral of 0.200 kips/in, corresponding to safety factors of 1.5 and 1, the applied tearing modulus, 0.619, is less than the material tearing modulus, 1584, indicating flaw stability. The applied J-integral is also less than the J-integral, 7.101 kips/in, at the point of instability. For safety factors of 1.5 and 1, the applied J-integral of 0.200 kips/in is less than the J0.1 value of 2.474 kips/in, demonstrating that the crack driving force falls below the J-R curve at a crack extension of 0.1 inch.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 6.5     Primary Stress Limit Analysis The primary stress limit analysis (also referred to as primary stress limits of NB-3000) that addresses all the Shearon Harris repaired configurations as of the Fall 2016 outage are addressed in Appendix C. Based on this primary stress limit analysis, it is concluded that amongst the twelve repairs performed to-date as of October 2016, Nozzles 30, 40, and 51 yield the most limiting life of 5 years since the repairs were performed in October 2016.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) 7.0     

==SUMMARY==
OF RESULTS AND CONCLUSIONS Linear-elastic and elastic-plastic fracture mechanics has been used to evaluate a postulated radial flaw in the J-groove weld and butter of an outermost CRDM nozzle reactor vessel head penetration. It was determined that an acceptable flaw size would be present after 30 years of fatigue crack growth, based on EPFM analysis consideration only, as summarized below.
7.1     Summary of Results Uphill Side             Downhill Side Flaw Sizes Initial flaw size,                              ai = 2.148 in.              2.148 in.
Final flaw size after 30 years,                 af =   [         ]  in.      [          ]  in.
Flaw growth,                                   a =    [         ]  in.      [          ]  in.
Operating Conditions                                     Reactor Trip              Reactor Trip Temperature,                                     T=    [      ]   o F         [       ]   o F
Material tearing modulus,                    Tmat = 50.70                   242.0 Material J-integral at 0.1 crack extension,  J0.1 = 2.473 kips/in.         2.473 kips/in.
Safety factors (primary/secondary),            SF = 3 / 1.5                 3 / 1.5 Applied tearing modulus (< Tmat)             Tapp = 8.502                   3.139 Safety factors (primary/secondary),            SF = 1.5 / 1                 1.5 / 1 Applied J-integral (< J0.1)                  Japp = 0.785 kips/in           0.273 kips/in Low Temperature Conditions                                Refueling                 Refueling Temperature,                                     T=    [    ]   o F           [     ]   o F
Material tearing modulus,                    Tmat = 942.9                   1357 Material J-integral at 0.1 crack extension,  J0.1 = 2.474 kips/in.         2.474 kips/in.
Safety factors (primary/secondary),            SF = 3 / 1.5                 3 / 1.5 Applied tearing modulus (< Tmat)             Tapp = 0.700                   0.704 Safety factors (primary/secondary),            SF = 1.5 / 1                 1.5 / 1 Applied J-integral (< J0.1)                  Japp = 0.132 kips/in           0.097 kips/in Page 48

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Summary of Results (Contd)
Faulted Conditions                                          LLOCA                  LLOCA Temperature,                                      T=    [    ] o F           [     ] o F
Material tearing modulus,                    Tmat = 82.38                  1584 Material J-integral at 0.1 crack extension,  J0.1 = 2.474 kips/in.        2.474 kips/in.
Safety factors (primary/secondary),            SF = 1.5 / 1                1.5 / 1 Applied tearing modulus (< Tmat)             Tapp = 5.364                  0.619 Safety factors (primary/secondary),            SF = 1.5 / 1                1.5 / 1 Applied J-integral (< J0.1)                  Japp = 2.359 kips/in          0.200 kips/in 7.2    Conclusion Based on a combination of linear elastic and elastic-plastic fracture mechanics analysis of a postulated remaining flaw in the original Alloy 182 J-groove weld and butter material, the Shearon Harris Unit 1 CRDM and CET nozzles are considered to be acceptable for at least 30 years of operation following an IDTB weld repair. However, based on primary stress limit analysis, considering all the CRDM repaired configurations as of October 2016, the overall service life of the Shearon Harris Unit 1 RVCH is 5 years from the performance of the October 2016 repairs, as determined in Appendix C of the document.

==8.0    REFERENCES==
: 1. AREVA Drawing 02-9175500E-007, Shearon Harris CRDM ID Temper Bead Weld Repair
: 2. AREVA Document 08-9172870-003, Shearon Harris RVCH CRDM and CET Nozzle Penetration Modification
: 3. AREVA Document 32-9176344-000, Shearon Harris Unit 1 IDTB CRDM/CET Nozzle Weld Residual Stress Analysis - Proprietary Document
: 4. AREVA Document 51-5012047-00, Stress Corrosion Cracking of Low Alloy Steel
: 5. ANSYS Finite Element Computer Code, Version 12.1, ANSYS Inc., Canonsburg, PA.
: 6. T.L. Anderson, Fracture Mechanics: Fundamentals and Applications, CRC Press, 1991.
: 7. ASME Boiler and Pressure Vessel Code, Section III, Rules for Construction of Nuclear Facility Components, Division 1, Subsection NB, Class 1 Components, 2001 Edition with Addenda through 2003.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
: 8. ASME Boiler and Pressure Vessel Code, Section II, Materials, 2001 Edition with Addenda through 2003.
: 9. AREVA Document 38-2200979-000, Shearon Harris - Proprietary Document Transmittal 1
: 10. AREVA Document 55-PQ7183-005, Procedure Qualification Record PQ7183-005
: 11. ASME Boiler and Pressure Vessel Code, Section XI, Rules for Inservice Inspection of Nuclear Power Plant Components, 2001 Edition with Addenda through 2003.
: 12. AREVA Document 32-9175220-003, Shearon Harris Unit 1 Contingency CRDM IDTB Weld Repair Analysis
: 13. AREVA Document 38-2201004-000, Shearon Harris - Proprietary Document Transmittal 4 Page 50

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
APPENDIX A:           DETAILED FLAW EVALUATIONS FOR UPHILL SIDE This appendix presents the fatigue crack growth tables and the elastic-plastic fracture mechanics flaw evaluations for the uphill side of the CRDM penetration.
Table A-1: Stress Intensification Factors for Uphill Side - Welding Residual Stress Condition    WRS Temperature   70.0   F Pressure      n/a   psig Sy        50.0   ksi KIc       98.0   ksiin KIa       55.2   ksiin Crack Front     KI Position  (ksiin) 1      45.118 2      41.056 3      38.435 4      31.191 5      27.747 6      24.365 7      20.513 8      14.773 9      18.055 10        9.772 11       -2.101 12        7.352 13      14.344 14      18.763 15      22.133 16      26.509 17      17.849 Page 51

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-2: Fatigue Crack Growth for Uphill Side - Heatup/Cooldown STRESS INTENSITY FACTORS                                                                   FATIGUE CRACK GROWTH Condition*     HU1         HU2         CD          SD                Transient

== Description:==
200   cycles        over       40      years Temperature     557.0       349.0      120.0       70.0   F Pressure       2317         467        467          0    psig                         N =    5.0  cycles/year Sy          42.6        44.9       49.2        50.0   ksi KIc         200.0       200.0      200.0       98.0   ksiin                                                         Position 16 KIa         200.0       200.0      85.5        55.2   ksiin       Operating                       HU1        HU2                           CD       SD Crack Front           Stress Intensity Factor, KI                        Time      Cycle        a     KI(a)      KI(a)      KI          a    KI(a)    KI(a)
Position    (ksiin)    (ksiin)   (ksiin)    (ksiin)             (end of yr.)            (in.)  (ksiin)   (ksiin)  (ksiin)      (in.) (ksiin) (ksiin) 1        18.527      -18.920     13.250      0.000                    0         0.0             61.833     13.247     48.586             42.656   26.509 2        18.826      -17.438     12.738      0.000                    1         5.0             61.857     13.252     48.604             42.672   26.519 3        19.351      -15.934     12.257      0.000                    2        10.0             62.217     13.329     48.888             42.921   26.674 4        18.420      -13.078     10.820      0.000                    3        15.0             62.579     13.407     49.172             43.171   26.829 5        18.505      -11.272     10.097      0.000                    4        20.0             62.943     13.485     49.458             43.422   26.985 6        18.197       -9.462      9.289      0.000                    5        25.0             63.309     13.563     49.746             43.674   27.142 7        16.954       -7.589      8.195      0.000                    6        30.0             63.678     13.642     50.035             43.929   27.300 8        12.946       -5.678      6.169      0.000                    7        35.0             64.048     13.722     50.326             44.184   27.459 9        16.968       -5.646      7.508      0.000                    8        40.0             64.420     13.801     50.619             44.441   27.618 10          8.787      -3.529      4.085      0.000                    9        45.0             64.795     13.881     50.913             44.699   27.779 11         -3.688      -1.066     -0.898      0.000                   10        50.0             65.171     13.962     51.209             44.959   27.940 12         7.147       -2.712      3.264      0.000                   11        55.0             65.550     14.043     51.506             45.220   28.102 13        14.991       -4.996      6.623      0.000                   12        60.0             65.930     14.125     51.805             45.483   28.266 14        20.357       -7.186      9.121      0.000                   13        65.0             66.313     14.207     52.106             45.747   28.430 15        25.782       -9.743     11.777      0.000                   14        70.0             66.698     14.289     52.409             46.012   28.595 16        35.324      -13.262     16.147      0.000                   15        75.0             67.085     14.372     52.713             46.279   28.761 17        23.491       -9.495     10.995      0.000                   16        80.0             67.474     14.455     53.018             46.547   28.927 17        85.0             67.865     14.539     53.326             46.817   29.095
* Condition  Description                                                   18        90.0             68.258     14.624     53.635             47.089   29.264 HU1      Time step 6 at 7.67 hr. (Heatup) - Maximum KI                 19        95.0             68.654     14.708     53.946             47.362   29.433 HU2      Time step 3 at 2.29 hr. (Heatup) - Minimum KI                 20       100.0             69.052     14.794     54.258             47.636   29.604 CD      Time step 15 at 14.37 hr. - Maximum KI at Low Temperature     21       105.0             69.452     14.879     54.572             47.912   29.775 SD      Shutdown at Ambient Conditions                                22       110.0             69.854     14.965     54.888             48.189   29.948 23       115.0             70.258     15.052     55.206             48.468   30.121 24       120.0             70.665     15.139     55.526             48.749   30.295 25       125.0             71.073     15.227     55.847             49.031   30.471 26       130.0             71.484     15.315     56.170             49.314   30.647 27       135.0             71.898     15.403     56.494             49.599   30.824 28       140.0             72.313     15.492     56.821             49.886   31.002 29       145.0             72.731     15.582     57.149             50.174   31.181 30       150.0             73.151     15.672     57.479             50.464   31.361 Page 52

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-3: Fatigue Crack Growth for Uphill Side - Unit Loading/Unloading STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      UL          UU                               Transient

== Description:==
18300   cycles        over        40     years Temperature     533.8       574.3  F Pressure       2265        2209   psig                                        N =   457.5  cycles/year Sy          42.9        42.4   ksi KIc         200.0       200.0  ksiin                                                                    Position 16 KIa         200.0       200.0  ksiin                      Operating                        UL         UU Crack Front            KI                                        Time       Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)             (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        23.007      10.659                                   0         0.0              65.851     53.629      12.222 2        23.018      11.371                                   1        457.5             65.891     53.662      12.229 3        23.249      12.295                                   2        915.0             66.275     53.974      12.301 4        21.710      12.334                                   3       1372.5             66.661     54.288      12.372 5        21.430      12.954                                   4       1830.0             67.049     54.604      12.444 6        20.760      13.214                                   5       2287.5             67.439     54.922      12.517 7        19.115      12.658                                   6       2745.0             67.831     55.241      12.589 8        14.550       9.722                                   7       3202.5             68.225     55.563      12.663 9        18.795      13.197                                   8       3660.0             68.622     55.886      12.736 10         9.829       6.679                                   9       4117.5             69.021     56.210      12.810 11         -3.731      -3.452                                 10       4575.0             69.422     56.537      12.885 12          7.964       5.477                                 11       5032.5             69.825     56.865      12.960 13        16.596      11.668                                  12       5490.0             70.230     57.196      13.035 14        22.593      15.748                                  13       5947.5             70.638     57.528      13.110 15        28.716      19.782                                  14       6405.0             71.048     57.861      13.187 16        39.342      27.120                                  15       6862.5             71.460     58.197      13.263 17        26.287      17.846                                  16       7320.0             71.875     58.535      13.340 17       7777.5             72.291     58.874      13.417
* Condition  Description                                           18       8235.0             72.710     59.215      13.495 UL      Time step 12 at 0.29 hr. - Maximum KI                 19       8692.5             73.132     59.559      13.573 UU      Time step 11 at 0.29 hr. - Minimum KI                 20       9150.0             73.555     59.904      13.652 21       9607.5             73.981     60.250      13.731 22       10065.0            74.410     60.599      13.811 23       10522.5            74.841     60.950      13.890 24       10980.0            75.274     61.303      13.971 25       11437.5            75.709     61.657      14.052 26       11895.0            76.147     62.014      14.133 27       12352.5            76.587     62.372      14.215 28       12810.0            77.030     62.733      14.297 29       13267.5            77.475     63.095      14.379 30       13725.0            77.922     63.460      14.462 Page 53

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-4: Fatigue Crack Growth for Uphill Side - Step Load Increase/Decrease STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      SLI        SLD                               Transient

== Description:==
4000  cycles        over        40     years Temperature     551.4       570.8  F Pressure       2367        2246   psig                                        N =  100.0  cycles/year Sy          42.7        42.5   ksi KIc         200.0       200.0  ksiin                                                                   Position 16 KIa         200.0       200.0  ksiin                      Operating                       SLI        SLD Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        22.974      11.043                                   0         0.0             66.608     54.168      12.440 2        23.070      11.733                                   1        100.0            66.884     54.393      12.492 3        23.434      12.620                                   2        200.0            67.274     54.709      12.564 4        21.981      12.614                                   3        300.0            67.665     55.028      12.637 5        21.803      13.209                                   4        400.0            68.059     55.348      12.711 6        21.191      13.451                                   5        500.0            68.455     55.670      12.785 7        19.546      12.878                                   6        600.0            68.853     55.994      12.859 8        14.887       9.896                                   7        700.0            69.253     56.319      12.934 9        19.268      13.414                                   8        800.0            69.656     56.647      13.009 10        10.061       6.796                                   9        900.0            70.061     56.976      13.085 11         -3.874      -3.486                                 10       1000.0            70.468     57.307      13.161 12          8.146       5.579                                 11       1100.0            70.877     57.640      13.237 13        16.990      11.874                                  12       1200.0            71.288     57.974      13.314 14        23.108      16.034                                  13       1300.0            71.702     58.311      13.391 15        29.318      20.161                                  14       1400.0            72.118     58.649      13.469 16        40.099      27.659                                  15       1500.0            72.536     58.989      13.547 17        26.771      18.203                                  16       1600.0            72.957     59.331      13.626 17       1700.0            73.380     59.675      13.705
* Condition  Description                                           18       1800.0            73.805     60.021      13.784 SLI     Time step 10 at 0.05 hr. - Maximum KI                 19       1900.0            74.233     60.369      13.864 SLD      Time step 10 at 0.042 hr. - Minimum KI                20       2000.0            74.663     60.718      13.944 21       2100.0            75.095     61.070      14.025 22       2200.0            75.530     61.424      14.106 23       2300.0            75.967     61.779      14.188 24       2400.0            76.406     62.136      14.270 25       2500.0            76.848     62.496      14.353 26       2600.0            77.293     62.857      14.436 27       2700.0            77.739     63.221      14.519 28       2800.0            78.189     63.586      14.603 29       2900.0            78.640     63.953      14.687 30       3000.0            79.095     64.323      14.772 Page 54

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-5: Fatigue Crack Growth for Uphill Side - Turbine Roll Test STRESS INTENSITY FACTORS                                                          FATIGUE CRACK GROWTH Condition*     TRT1        TRT2                             Transient

== Description:==
80   cycles        over        40     years Temperature     443.4       557.4  F Pressure       1692        2317   psig                                       N =    2.0  cycles/year Sy          43.8        42.6   ksi KIc         200.0       200.0  ksiin                                                                  Position 16 KIa         200.0       200.0  ksiin                     Operating                      TRT1       TRT2 Crack Front            KI                                       Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                           (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        40.587       7.354                                  0         0.0             79.738     50.447      29.291 2        39.304       8.260                                  1         2.0             80.133     50.697      29.436 3        38.158       9.378                                  2         4.0             80.599     50.992      29.607 4        34.061       9.845                                  3         6.0             81.069     51.289      29.780 5        32.161      10.713                                  4         8.0             81.540     51.587      29.953 6        29.935      11.230                                  5        10.0             82.015     51.887      30.127 7        26.687      10.973                                  6        12.0             82.492     52.189      30.303 8        20.115       8.468                                  7        14.0             82.971     52.493      30.479 9        24.921      11.756                                  8        16.0             83.453     52.798      30.656 10        13.413       5.859                                  9        18.0             83.938     53.104      30.834 11         -3.551      -3.409                                10        20.0             84.426     53.413      31.013 12        10.752       4.835                                 11        22.0             84.916     53.723      31.193 13        21.987      10.400                                 12        24.0             85.409     54.035      31.374 14        30.173      13.981                                 13        26.0             85.905     54.348      31.556 15        38.799      17.463                                 14        28.0             86.403     54.664      31.739 16        53.229      23.938                                 15        30.0             86.904     54.981      31.923 17        36.060      15.642                                 16        32.0             87.408     55.300      32.109 17        34.0             87.915     55.620      32.295
* Condition  Description                                          18        36.0             88.424     55.943      32.482 TRT1     Time step 5 at 0.278 hr. - Maximum KI                19        38.0             88.937     56.267      32.670 TRT2     Time step 8 at 1.418 hr. - Minimum KI                20        40.0             89.452     56.593      32.859 21        42.0             89.970     56.920      33.050 22        44.0             90.491     57.250      33.241 23        46.0             91.014     57.581      33.433 24        48.0             91.541     57.914      33.627 25        50.0             92.070     58.249      33.821 26        52.0             92.603     58.586      34.017 27        54.0             93.138     58.924      34.213 28        56.0             93.676     59.265      34.411 29        58.0             94.217     59.607      34.610 30        60.0             94.761     59.952      34.810 Page 55

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-6: Fatigue Crack Growth for Uphill Side - Refueling STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      RF1         RF2                              Transient

== Description:==
80   cycles        over        40     years Temperature     32.0        140.0  F Pressure         0           0    psig                                        N =    2.0  cycles/year Sy          50.0        48.5   ksi KIc         63.5        200.0  ksiin                                                                   Position 16 KIa         43.2        105.3  ksiin                      Operating                       RF1        RF2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        27.949       -4.885                                  0         0.0             53.975     22.705      31.270 2        26.345       -4.536                                  1         2.0             54.247     22.819      31.427 3        24.683       -4.194                                  2         4.0             54.563     22.952      31.610 4        21.095       -3.491                                  3         6.0             54.880     23.086      31.794 5        18.978       -3.063                                  4         8.0             55.200     23.220      31.979 6        16.815       -2.617                                  5        10.0             55.521     23.355      32.165 7        14.330       -2.135                                  6        12.0             55.844     23.491      32.353 8        10.707       -1.614                                  7        14.0             56.168     23.628      32.541 9        12.277       -1.643                                  8        16.0             56.495     23.765      32.730 10         6.961       -1.007                                  9        18.0             56.823     23.903      32.920 11         -0.430      -0.243                                 10        20.0             57.153     24.042      33.111 12          5.491      -0.781                                 11        22.0             57.485     24.181      33.303 13        10.857       -1.457                                 12        24.0             57.819     24.322      33.497 14        15.170       -2.084                                 13        26.0             58.154     24.463      33.691 15        19.962       -2.802                                 14        28.0             58.492     24.605      33.887 16        27.466       -3.804                                 15        30.0             58.831     24.748      34.083 17        19.022       -2.699                                 16        32.0             59.172     24.891      34.281 17        34.0             59.515     25.035      34.480
* Condition  Description                                           18        36.0             59.860     25.180      34.679 RF1      Time step 7 at 0.171 hr. - Maximum KI                 19        38.0             60.207     25.326      34.880 RF2      Time step 1 at 0.0001 hr. - Minimum KI                20        40.0             60.555     25.473      35.082 21        42.0             60.906     25.621      35.285 22        44.0             61.259     25.769      35.490 23        46.0             61.613     25.918      35.695 24        48.0             61.969     26.068      35.902 25        50.0             62.328     26.219      36.109 26        52.0             62.688     26.370      36.318 27        54.0             63.051     26.523      36.528 28        56.0             63.415     26.676      36.739 29        58.0             63.781     26.830      36.951 30        60.0             64.150     26.985      37.165 Page 56

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-7: Fatigue Crack Growth for Uphill Side - Loss of Load STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      LL1         LL2                              Transient

== Description:==
210   cycles        over        40     years Temperature     575.8       588.8  F Pressure       2710        1844   psig                                        N =   5.25  cycles/year Sy          42.4        42.2   ksi KIc         200.0       200.0  ksiin                                                                   Position 16 KIa         200.0       200.0  ksiin                      Operating                       LL1        LL2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        23.554       -4.474                                  0         0.0             69.012     37.236      31.776 2        23.806       -3.022                                  1         5.3             69.364     37.426      31.938 3        24.444       -1.387                                  2        10.5             69.768     37.644      32.124 4        23.114        0.461                                  3        15.8             70.174     37.863      32.311 5        23.111        2.069                                  4        21.0             70.582     38.083      32.499 6        22.576        3.396                                  5        26.3             70.993     38.305      32.688 7        20.873        4.163                                  6        31.5             71.406     38.527      32.878 8        15.923        3.330                                  7        36.8             71.821     38.751      33.069 9        20.646        5.710                                  8        42.0             72.238     38.977      33.261 10       10.754        2.498                                  9        47.3             72.658     39.203      33.455 11        -4.216      -2.966                                 10        52.5             73.080     39.431      33.649 12         8.702       2.160                                 11        57.8             73.504     39.660      33.844 13       18.163        5.054                                 12        63.0             73.931     39.890      34.041 14       24.668        6.566                                 13        68.3             74.360     40.122      34.238 15       31.190        7.815                                 14        73.5             74.792     40.354      34.437 16       42.503      10.727                                  15        78.8             75.225     40.588      34.637 17       28.370        6.584                                 16        84.0             75.662     40.824      34.838 17        89.3             76.100     41.060      35.040
* Condition  Description                                           18        94.5             76.541     41.298      35.243 LL1     Time step 2 at 0.003 hr. - Maximum KI                 19        99.8             76.985     41.538      35.447 LL2     Time step 12 at 0.033 hr. - Minimum KI                20       105.0             77.430     41.778      35.652 21       110.3             77.879     42.020      35.859 22       115.5             78.330     42.263      36.066 23       120.8             78.783     42.508      36.275 24       126.0             79.239     42.754      36.485 25       131.3             79.697     43.001      36.696 26       136.5             80.158     43.250      36.908 27       141.8             80.621     43.500      37.121 28       147.0             81.087     43.751      37.336 29       152.3             81.555     44.004      37.551 30       157.5             82.026     44.258      37.768 Page 57

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-8: Fatigue Crack Growth for Uphill Side - Loss of Power STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      LP1         LP2                              Transient

== Description:==
100   cycles        over        40     years Temperature     553.8       600.5  F Pressure       2295        2464   psig                                        N =    2.5  cycles/year Sy          42.7        42.1   ksi KIc         200.0       200.0  ksiin                                                                   Position 16 KIa         200.0       200.0  ksiin                      Operating                       LP1        LP2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        18.177       2.404                                   0         0.0             61.342     46.871      14.471 2        18.484       3.685                                   1         2.5             61.668     47.120      14.548 3        19.014       5.180                                   2         5.0             62.027     47.395      14.633 4        18.116       6.387                                   3         7.5             62.388     47.671      14.718 5        18.212       7.727                                   4        10.0             62.751     47.948      14.803 6        17.922       8.703                                   5        12.5             63.116     48.227      14.890 7        16.708       8.918                                   6        15.0             63.483     48.507      14.976 8        12.759       6.975                                   7        17.5             63.852     48.789      15.063 9        16.740      10.142                                   8        20.0             64.224     49.073      15.151 10         8.663       4.906                                   9        22.5             64.597     49.358      15.239 11         -3.661      -3.498                                 10        25.0             64.972     49.645      15.327 12          7.047       4.105                                 11        27.5             65.349     49.933      15.416 13        14.789       9.001                                  12        30.0             65.729     50.223      15.506 14        20.078      12.011                                  13        32.5             66.110     50.514      15.596 15        25.423      14.846                                  14        35.0             66.494     50.807      15.686 16        34.833      20.362                                  15        37.5             66.879     51.102      15.777 17        23.159      13.095                                  16        40.0             67.267     51.398      15.869 17        42.5             67.657     51.696      15.961
* Condition  Description                                           18        45.0             68.049     51.996      16.053 LP1      Time step 2 at 0.003 hr. - Maximum KI                 19        47.5             68.443     52.297      16.146 LP2      Time step 11 at 0.053 hr. - Minimum KI                20        50.0             68.840     52.600      16.240 21        52.5             69.238     52.905      16.334 22        55.0             69.639     53.211      16.428 23        57.5             70.042     53.519      16.523 24        60.0             70.447     53.828      16.619 25        62.5             70.855     54.140      16.715 26        65.0             71.264     54.453      16.812 27        67.5             71.676     54.767      16.909 28        70.0             72.090     55.084      17.007 29        72.5             72.507     55.402      17.105 30        75.0             72.926     55.722      17.204 Page 58

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-9: Fatigue Crack Growth for Uphill Side - Reactor Trip STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      RT1         RT2                              Transient

== Description:==
250   cycles        over        40     years Temperature     457.4       537.4  F Pressure       2205        1803   psig                                        N =   6.25  cycles/year Sy          43.6        42.8   ksi KIc         200.0       200.0  ksiin                                                                   Position 16 KIa         200.0       200.0  ksiin                      Operating                       RT1        RT2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        50.109      15.130                                   0         0.0             91.705     55.567      36.138 2        48.502      15.368                                   1         6.3             92.195     55.864      36.331 3        47.097      15.728                                   2        12.5             92.732     56.189      36.543 4        42.010      14.966                                   3        18.8             93.272     56.516      36.755 5        39.651      14.995                                   4        25.0             93.814     56.845      36.969 6        36.864      14.741                                   5        31.3             94.360     57.176      37.184 7        32.808      13.760                                   6        37.5             94.909     57.508      37.401 8        24.760      10.481                                   7        43.8             95.461     57.843      37.618 9        30.517      13.823                                   8        50.0             96.016     58.179      37.837 10        16.474       7.136                                   9        56.3             96.573     58.517      38.056 11         -4.144      -3.110                                 10        62.5             97.134     58.857      38.278 12        13.197       5.817                                  11        68.8             97.698     59.199      38.500 13        26.924      12.241                                  12        75.0             98.266     59.542      38.723 14        36.980      16.629                                  13        81.3             98.836     59.888      38.948 15        47.575      21.108                                  14        87.5             99.409     60.235      39.174 16        65.196      29.058                                  15        93.8             99.986     60.585      39.401 17        44.202      19.322                                  16       100.0             100.566    60.936      39.630 17       106.3             101.149    61.289      39.859
* Condition  Description                                           18       112.5             101.735    61.644      40.090 RT1      Time step 13 at 0.171 hr. - Maximum KI                19       118.8             102.324    62.001      40.323 RT2      Time step 8 at 0.025 hr. - Minimum KI                 20       125.0             102.917    62.361      40.556 21       131.3             103.513    62.722      40.791 22       137.5             104.112    63.085      41.027 23       143.8             104.714    63.450      41.265 24       150.0             105.320    63.817      41.503 25       156.3             105.929    64.186      41.743 26       162.5             106.542    64.557      41.985 27       168.8             107.157    64.930      42.227 28       175.0             107.777    65.305      42.471 29       181.3             108.399    65.683      42.717 30       187.5             109.025    66.062      42.963 Page 59

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-10: Fatigue Crack Growth for Uphill Side - Inadvertent Depressurization STRESS INTENSITY FACTORS                                                            FATIGUE CRACK GROWTH Condition*       ID1         ID2                              Transient

== Description:==
100   cycles        over        40     years Temperature      557.4       556.6  F Pressure        2317        1161   psig                                        N =    2.5  cycles/year Sy          42.6        42.6   ksi KIc          200.0       200.0  ksiin                                                                   Position 16 KIa          200.0       200.0  ksiin                      Operating                       ID1        ID2 Crack Front             KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position     (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1         18.517       -4.170                                  0         0.0             61.828     33.923      27.905 2         18.817       -3.034                                  1         2.5             62.182     34.117      28.065 3         19.343       -1.801                                  2         5.0             62.544     34.316      28.228 4         18.414       -0.310                                  3         7.5             62.908     34.515      28.392 5         18.500        0.933                                  4        10.0             63.274     34.716      28.558 6         18.193        1.996                                  5        12.5             63.642     34.918      28.724 7         16.951        2.674                                  6        15.0             64.012     35.121      28.891 8         12.944        2.112                                  7        17.5             64.384     35.325      29.059 9         16.966        3.967                                  8        20.0             64.758     35.531      29.228 10         8.786        1.655                                  9        22.5             65.135     35.737      29.397 11         -3.689      -2.383                                 10        25.0             65.513     35.945      29.568 12          7.146       1.450                                 11        27.5             65.893     36.154      29.740 13        14.989        3.509                                 12        30.0             66.276     36.363      29.912 14        20.354        4.514                                 13        32.5             66.660     36.574      30.086 15        25.779        5.327                                 14        35.0             67.047     36.787      30.261 16        35.319        7.414                                 15        37.5             67.436     37.000      30.436 17        23.488        4.490                                 16        40.0             67.827     37.215      30.613 17        42.5             68.220     37.430      30.790
* Condition   Description                                           18        45.0             68.616     37.647      30.968 ID1      Time step 1 at 0.0001 hr. - Maximum KI                19        47.5             69.013     37.865      31.148 ID2      Time step 9 at 0.022 hr. - Minimum KI                 20        50.0             69.413     38.085      31.328 21        52.5             69.815     38.305      31.510 22        55.0             70.219     38.527      31.692 23        57.5             70.625     38.750      31.875 24        60.0             71.034     38.974      32.060 25        62.5             71.445     39.199      32.245 26        65.0             71.858     39.426      32.432 27        67.5             72.273     39.654      32.619 28        70.0             72.691     39.883      32.808 29        72.5             73.110     40.113      32.997 30        75.0             73.533     40.345      33.188 Page 60

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-11: Fatigue Crack Growth for Uphill Side - Excessive Feedwater Flow STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*     EFF1        EFF2                              Transient

== Description:==
40   cycles        over        40     years Temperature     462.4       557.4  F Pressure       1977        2317   psig                                        N =    1.0  cycles/year Sy          43.6        42.6   ksi KIc         200.0       200.0  ksiin                                                                   Position 16 KIa         200.0       200.0  ksiin                      Operating                      EFF1       EFF2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        40.206      18.517                                   0         0.0             81.058     61.828      19.230 2        39.093      18.817                                   1         1.0             81.529     62.187      19.342 3        38.174      19.343                                   2         2.0             82.003     62.549      19.454 4        34.281      18.414                                   3         3.0             82.480     62.913      19.567 5        32.584      18.500                                   4         4.0             82.960     63.279      19.681 6        30.503      18.193                                   5         5.0             83.443     63.647      19.796 7        27.311      16.951                                   6         6.0             83.928     64.017      19.911 8        20.626      12.944                                   7         7.0             84.416     64.389      20.027 9        25.683      16.966                                   8         8.0             84.907     64.764      20.143 10        13.771       8.786                                   9         9.0             85.400     65.140      20.260 11         -3.839      -3.689                                 10        10.0             85.896     65.518      20.378 12        11.051       7.146                                  11        11.0             86.395     65.899      20.496 13        22.647      14.989                                  12        12.0             86.896     66.281      20.615 14        31.036      20.354                                  13        13.0             87.401     66.666      20.735 15        39.815      25.779                                  14        14.0             87.908     67.053      20.855 16        54.549      35.319                                  15        15.0             88.418     67.442      20.976 17        36.881      23.488                                  16        16.0             88.930     67.833      21.098 17        17.0             89.446     68.226      21.220
* Condition  Description                                           18        18.0             89.964     68.621      21.343 EFF1     Time step 30 at 0.167 hr. - Maximum KI                19        19.0             90.485     69.019      21.466 EFF2     Time step 1 at 0.0001 hr. - Minimum KI                20        20.0             91.009     69.418      21.591 21        21.0             91.536     69.820      21.716 22        22.0             92.066     70.225      21.842 23        23.0             92.599     70.631      21.968 24        24.0             93.134     71.039      22.095 25        25.0             93.673     71.450      22.223 26        26.0             94.215     71.863      22.351 27        27.0             94.759     72.279      22.480 28        28.0             95.307     72.696      22.610 29        29.0             95.857     73.116      22.741 30        30.0             96.411     73.539      22.872 Page 61

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-12: Fatigue Crack Growth for Uphill Side - Leak Test STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      LT1         LT2                              Transient

== Description:==
280   cycles        over        40     years Temperature     238.0       82.0   F Pressure       2351         602   psig                                        N =    7.0  cycles/year Sy          46.4        50.0   ksi KIc         200.0       115.6  ksiin                                                                   Position 16 KIa         200.0       60.6   ksiin                      Operating                       LT1        LT2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)        KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)    (ksiin)    (in.)
1        36.203       7.924                                   0         0.0             75.304     37.270      38.034 2        35.188       7.716                                   1         7.0             75.743     37.487      38.255 3        34.376       7.578                                   2        14.0             76.184     37.705      38.478 4        30.852       6.820                                   3        21.0             76.627     37.925      38.702 5        29.318       6.511                                   4        28.0             77.073     38.145      38.927 6        27.425       6.103                                   5        35.0             77.521     38.367      39.154 7        24.524       5.455                                   6        42.0             77.972     38.590      39.381 8        18.585       4.155                                   7        49.0             78.425     38.815      39.610 9        22.970       5.093                                   8        56.0             78.881     39.040      39.841 10       12.351       2.750                                   9        63.0             79.339     39.267      40.072 11        -3.258      -0.668                                 10        70.0             79.800     39.495      40.305 12         9.923       2.208                                 11        77.0             80.263     39.725      40.539 13       20.272       4.493                                  12        84.0             80.729     39.955      40.774 14       27.806       6.166                                  13        91.0             81.198     40.187      41.011 15       35.677       7.901                                  14        98.0             81.669     40.420      41.249 16       48.795      10.761                                  15       105.0             82.143     40.655      41.488 17       33.019       7.282                                  16       112.0             82.619     40.890      41.729 17       119.0             83.098     41.127      41.970
* Condition  Description                                           18       126.0             83.579     41.366      42.214 LT1     Time step 6 at 3.92 hr. - Maximum KI                  19       133.0             84.064     41.605      42.458 LT2     Time step 2 at 0.12 hr. - Minimum KI                  20       140.0             84.550     41.846      42.704 21       147.0             85.040     42.089      42.951 22       154.0             85.532     42.332      43.200 23       161.0             86.027     42.577      43.450 24       168.0             86.525     42.823      43.701 25       175.0             87.025     43.071      43.954 26       182.0             87.528     43.320      44.208 27       189.0             88.034     43.571      44.464 28       196.0             88.543     43.822      44.721 29       203.0             89.054     44.075      44.979 30       210.0             89.569     44.330      45.239 Page 62

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-13: Stress Intensification Factors for Uphill Side - Faulted Conditions STRESS INTENSITY FACTORS                             TOTAL STRESS INTENSITY FACTORS FOR OPERATING CONDITIONS                                   WITH RESIDUAL STRESS Condition*   LLOCA        LSLB Temperature     32.0       204.3 F Pressure        60         1331   psig                          ao = 2.1482    in.
Sy          50.0        46.9   ksi KIc         63.5       200.0 ksiin KIa         43.2       200.0 ksiin                  Condition*   LLOCA         LSLB Crack Front            KI                                Crack Front           KI Position    (ksiin)    (ksiin)                        Position    (ksiin)    (ksiin) 1       172.666 125.310                                 1        217.784     170.428 2       162.695 118.971                                 2        203.751     160.027 3       152.220 112.724                                 3        190.655     151.159 4       129.976      97.510                             4        161.167     128.701 5       116.733      89.073                             5        144.480     116.820 6       103.336      80.161                             6        127.701     104.526 7        88.075      69.285                             7        108.588     89.798 8        65.634      51.855                             8        80.407      66.628 9        75.591      61.179                             9        93.646      79.234 10        42.758      34.017                             10       52.530      43.789 11         -3.101      -4.606                            11        -5.202      -6.707 12        33.734      26.937                             12       41.086      34.289 13        66.840      53.893                             13       81.184      68.237 14        93.354      74.686                             14       112.117     93.449 15       122.911      97.237                             15       145.044     119.370 16       169.481 133.327                                 16       195.990     159.836 17       117.360      91.670                             17       135.209     109.519
* Condition  Description LLOCA     Time step 15 at 0.03889 hr. (140 sec.) - Maximum KI LSLB     Time step 10 at 0.09889 hr. (356 sec.) - Maximum KI Page 63

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-14: EPFM Evaluations for Uphill Side - Reactor Trip EPFM Equations:                           Jmat = C(a)m                          C=
Tmat = (E/f 2)*Cm(a)m-1              m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors          KI*p        KI*s         KI*(a)      ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary        (ksiin)    (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00         63.614      45.463      109.077    3.3712   114.881      0.442        1.035    Yes 2.00       1.00       127.227       45.463      172.690    3.8714   194.907      1.271        2.978    Yes 3.00       1.50       190.841       68.194      259.035    4.9117   329.307      3.628        8.502    Yes 4.00       1.00       254.455       45.463      299.918    5.5495   405.277      5.495      12.877     Yes 6.00       1.00       381.682       45.463      427.145    8.1310   698.669    16.331       38.270      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 3.1437     3.1437      199.980     142.920       342.900    6.3206   494.503      8.181      19.171    19.171 at Jmat =   3.628     kips/in,         Tmat =     50.698 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors          KI*p        KI*s         KI*(a)      ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00         95.421      45.463      140.883    3.5931   153.185      0.785      2.473      Yes Page 64

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure A-1: J-T Diagram for Uphill Side - Reactor Trip 10 9
Instablility Point 8
7 J-T Material 6
J-Integral (kips/in) 5 J-T Applied 4
SF = 3 & 1.5 3
2 1
0 0      5       10        15        20         25          30       35     40      45      50 Tearing Modulus Page 65

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-15: EPFM Evaluations for Uphill Side - Refueling EPFM Equations:                          Jmat = C(a)m                           C=
Tmat = (E/f 2)*Cm(a)m-1               m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00         0.000       64.199       64.199    3.1266    65.117      0.132        0.301    Yes 3.00       1.50         0.000       96.299       96.299    3.2359    99.368      0.308        0.700    Yes 10.00      3.00         0.000     192.598       192.598    3.8263   216.106      1.456        3.311    Yes 10.00      4.00         0.000     256.798       256.798    4.4385   310.338      3.002        6.827    Yes 10.00      7.00         0.000     449.396       449.396    7.3248   697.672    15.173       34.504      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 5.7241     5.7241        0.000     367.482       367.482    5.9048   512.230      8.179      18.599    18.599 at Jmat =   0.308     kips/in,         Tmat = 942.947 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00         0.000       64.199       64.199    3.1266    65.117      0.132      2.474      Yes Page 66

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure A-2: J-T Diagram for Uphill Side - Refueling 10 9
Instablility Point 8
7 J-T Material 6
J-T Applied J-Integral (kips/in) 5 4
3 2
1 SF = 3 & 1.5 0
0      5          10       15   20         25          30      35     40      45      50 Tearing Modulus Page 67

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table A-16: EPFM Evaluations for Uphill Side - LLOCA EPFM Equations:                          Jmat = C(a)m                           C=
Tmat = (E/f 2)*Cm(a)m-1               m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors         KI*p         KI*s         KI*(a)      ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00         1.731     231.385       233.116    4.1923   273.795      2.337        5.314    Yes 1.50       1.00         2.596     231.385       233.982    4.2009   275.092      2.359        5.364    Yes 20.00      1.00        34.620     231.385       266.005    4.5407   325.143      3.295        7.494    Yes 50.00      1.00        86.549     231.385       317.934    5.1842   415.242      5.375      12.223     Yes 100.00      1.00       173.098     231.385       404.484    6.5110   592.037    10.926       24.847      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 1.5764     1.5764        2.729     364.753       367.482    5.9048   512.230      8.179      18.599    18.599 at Jmat =   2.359     kips/in,         Tmat =     82.380 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors         KI*p         KI*s         KI*(a)      ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00         2.596     231.385       233.982    4.2009   275.092      2.359      2.474      Yes Page 68

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure A-3: J-T Diagram for Uphill Side - LLOCA 10 9
Instablility Point 8
7 J-T Applied                        J-T Material 6
J-Integral (kips/in) 5 4
3 2                 SF = 1.5 & 1 1
0 0      5       10         15   20         25          30      35     40      45      50 Tearing Modulus APPENDIX B:                             DETAILED FLAW EVALUATIONS FOR DOWNHILL SIDE Page 69

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
This appendix presents the fatigue crack growth tables and the elastic-plastic fracture mechanics flaw evaluations for the downhill side of the CRDM penetration.
Table B-1: Stress Intensification Factors for Downhill Side - Welding Residual Stress Condition   WRS Temperature    70.0   F Pressure      n/a   psig Sy        50.0   ksi KIc       98.0   ksiin KIa       55.2   ksiin Crack Front    KI Position   (ksiin) 1       -1.701 2      13.932 3      15.717 4      27.178 5      33.890 6      37.604 7      40.501 8      40.098 9      37.638 10      33.447 11      24.673 12      27.528 13      26.926 14      24.389 15      21.701 16      16.768 17       5.776 Page 70

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-2: Fatigue Crack Growth for Downhill Side - Heatup/Cooldown STRESS INTENSITY FACTORS                                                                   FATIGUE CRACK GROWTH Condition*     HU1         HU2         CD          SD                Transient

== Description:==
200   cycles        over      40      years Temperature    557.0        349.0      120.0       70.0   F Pressure      2317          467        467          0    psig                         N =    5.0  cycles/year Sy          42.6        44.9       49.2        50.0   ksi KIc        200.0        200.0      200.0       98.0   ksiin                                                         Position 7 KIa        200.0        200.0      85.5        55.2   ksiin       Operating                       HU1        HU2                          CD       SD Crack Front           Stress Intensity Factor, KI                        Time      Cycle        a     KI(a)      KI(a)      KI         a    KI(a)    KI(a)
Position    (ksiin)    (ksiin)   (ksiin)    (ksiin)             (end of yr.)            (in.)  (ksiin)   (ksiin)  (ksiin)     (in.) (ksiin) (ksiin) 1         0.943        1.525     -0.207      0.000                    0         0.0             55.207     31.286    23.921             22.094   16.768 2         2.680       -5.311     2.591       0.000                    1         5.0             55.214     31.290    23.924             22.097   16.770 3         3.692       -5.535     2.956       0.000                    2        10.0             55.247     31.309    23.938             22.110   16.780 4         7.332       -8.637     5.117       0.000                    3        15.0             55.280     31.327    23.953             22.123   16.790 5        10.761       -9.272     6.370       0.000                    4        20.0             55.313     31.346    23.967             22.137   16.800 6        12.898       -9.294     6.973       0.000                    5        25.0             55.347     31.365    23.982             22.150   16.810 7        14.706       -9.215     7.386       0.000                    6        30.0             55.380     31.384    23.996             22.163   16.821 8        15.467       -8.853     7.381       0.000                    7        35.0             55.414     31.403    24.011             22.177   16.831 9        15.906       -8.287     7.265       0.000                    8        40.0             55.447     31.422    24.025             22.190   16.841 10        15.601       -7.685     6.943       0.000                    9        45.0             55.481     31.441    24.040             22.204   16.851 11        12.347       -6.288     5.571       0.000                   10        50.0             55.514     31.460    24.054             22.217   16.861 12        14.585       -7.340     6.566       0.000                   11        55.0             55.548     31.479    24.069             22.230   16.872 13        15.201       -7.848     6.962       0.000                   12        60.0             55.582     31.498    24.083             22.244   16.882 14        14.925       -7.826     6.945       0.000                   13        65.0             55.615     31.517    24.098             22.257   16.892 15        14.388       -7.578     6.747       0.000                   14        70.0             55.649     31.536    24.112             22.271   16.902 16        11.322       -5.983     5.326       0.000                   15        75.0             55.683     31.556    24.127             22.284   16.912 17         2.718       -1.762     1.368       0.000                   16        80.0             55.716     31.575    24.142             22.298   16.923 17        85.0             55.750     31.594    24.156             22.311   16.933
* Condition  Description                                                   18        90.0             55.784     31.613    24.171             22.325   16.943 HU1      Time step 6 at 7.67 hr. (Heatup) - Maximum KI                 19        95.0             55.818     31.632    24.186             22.338   16.954 HU2      Time step 3 at 2.29 hr. (Heatup) - Minimum KI                 20       100.0             55.852     31.651    24.200             22.352   16.964 CD      Time step 15 at 14.37 hr. - Maximum KI at Low Temperature     21       105.0             55.886     31.671    24.215             22.366   16.974 SD      Shutdown at Ambient Conditions                                22       110.0             55.920     31.690    24.230             22.379   16.984 23       115.0             55.953     31.709    24.244             22.393   16.995 24       120.0             55.988     31.728    24.259             22.406   17.005 25       125.0             56.022     31.748    24.274             22.420   17.015 26       130.0             56.056     31.767    24.289             22.434   17.026 27       135.0             56.090     31.786    24.303             22.447   17.036 28       140.0             56.124     31.806    24.318             22.461   17.046 29       145.0             56.158     31.825    24.333             22.475   17.057 30       150.0             56.192     31.844    24.348             22.488   17.067 Page 71

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-3: Fatigue Crack Growth for Downhill Side - Unit Loading/Unloading STRESS INTENSITY FACTORS                                                          FATIGUE CRACK GROWTH Condition*      UL          UU                              Transient

== Description:==
18300   cycles        over        40    years Temperature    533.8       574.3   F Pressure      2265        2209    psig                                       N =   457.5  cycles/year Sy          42.9        42.4   ksi KIc        200.0       200.0   ksiin                                                                   Position 7 KIa        200.0       200.0   ksiin                     Operating                        UL         UU Crack Front            KI                                       Time       Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                           (end of yr.)             (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         0.746       1.229                                  0         0.0              57.263     50.968      6.295 2         3.671       0.911                                  1        457.5             57.277     50.980      6.297 3         4.755       1.748                                  2        915.0             57.311     51.011      6.300 4         9.072       4.086                                  3       1372.5             57.346     51.042      6.304 5        12.751       6.918                                  4       1830.0             57.381     51.073      6.308 6        14.950       8.813                                  5       2287.5             57.415     51.104      6.312 7        16.762      10.467                                  6       2745.0             57.450     51.134      6.316 8        17.430      11.286                                  7       3202.5             57.485     51.165      6.319 9        17.756      11.855                                  8       3660.0             57.519     51.196      6.323 10        17.317      11.772                                  9       4117.5             57.554     51.227      6.327 11        13.737       9.268                                 10       4575.0             57.589     51.258      6.331 12        16.213      10.975                                 11       5032.5             57.624     51.289      6.335 13        16.951      11.372                                 12       5490.0             57.659     51.320      6.339 14        16.691      11.113                                 13       5947.5             57.694     51.351      6.342 15        16.112      10.692                                 14       6405.0             57.729     51.382      6.346 16        12.687       8.404                                 15       6862.5             57.764     51.414      6.350 17         3.091       1.937                                 16       7320.0             57.799     51.445      6.354 17       7777.5             57.834     51.476      6.358
* Condition  Description                                          18       8235.0             57.869     51.507      6.362 UL      Time step 12 at 0.29 hr. - Maximum KI                19       8692.5             57.904     51.538      6.365 UU      Time step 11 at 0.29 hr. - Minimum KI                20       9150.0             57.939     51.570      6.369 21       9607.5             57.974     51.601      6.373 22       10065.0            58.009     51.632      6.377 23       10522.5            58.045     51.664      6.381 24       10980.0            58.080     51.695      6.385 25       11437.5            58.115     51.726      6.389 26       11895.0            58.151     51.758      6.393 27       12352.5            58.186     51.789      6.396 28       12810.0            58.221     51.821      6.400 29       13267.5            58.257     51.853      6.404 30       13725.0            58.292     51.884      6.408 Page 72

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-4: Fatigue Crack Growth for Downhill Side - Step Load Increase/Decrease STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      SLI         SLD                              Transient

== Description:==
4000  cycles        over        40    years Temperature     546.7       577.3   F Pressure       2300        2290    psig                                       N =  100.0  cycles/year Sy           42.7        42.4   ksi KIc         200.0       200.0   ksiin                                                                  Position 7 KIa         200.0       200.0   ksiin                     Operating                       SLI        SLD Crack Front             KI                                       Time      Cycle        a     KI(a)      KI(a)       KI        a Position     (ksiin)    (ksiin)                           (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1          0.772       1.285                                  0         0.0             57.658     51.114      6.544 2          3.722       0.748                                  1        100.0            57.676     51.130      6.546 3          4.835       1.591                                  2        200.0            57.711     51.161      6.550 4          9.238       3.871                                  3        300.0            57.746     51.192      6.554 5         13.010       6.778                                  4        400.0            57.781     51.223      6.558 6         15.276       8.792                                  5        500.0            57.816     51.254      6.562 7         17.157      10.613                                  6        600.0            57.851     51.285      6.566 8         17.864      11.582                                  7        700.0            57.885     51.316      6.570 9         18.206      12.260                                  8        800.0            57.920     51.347      6.574 10         17.751      12.215                                  9        900.0            57.955     51.378      6.578 11         14.072       9.584                                 10       1000.0            57.991     51.409      6.582 12         16.598      11.333                                 11       1100.0            58.026     51.440      6.586 13         17.336      11.683                                 12       1200.0            58.061     51.471      6.590 14         17.050      11.350                                 13       1300.0            58.096     51.502      6.594 15         16.440      10.878                                 14       1400.0            58.131     51.533      6.598 16         12.943       8.536                                 15       1500.0            58.166     51.565      6.602 17          3.170       1.973                                 16       1600.0            58.202     51.596      6.606 17       1700.0            58.237     51.627      6.610
* Condition   Description                                          18       1800.0            58.272     51.659      6.614 SLI      Time step 9 at 0.041 hr. - Maximum KI                19       1900.0            58.308     51.690      6.618 SLD       Time step 9 at 0.028 hr. - Minimum KI                20       2000.0            58.343     51.721      6.622 21       2100.0            58.378     51.753      6.626 22       2200.0            58.414     51.784      6.630 23       2300.0            58.449     51.816      6.634 24       2400.0            58.485     51.847      6.638 25       2500.0            58.521     51.879      6.642 26       2600.0            58.556     51.910      6.646 27       2700.0            58.592     51.942      6.650 28       2800.0            58.627     51.973      6.654 29       2900.0            58.663     52.005      6.658 30       3000.0            58.699     52.037      6.662 Page 73

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-5: Fatigue Crack Growth for Downhill Side - Turbine Roll Test STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*     TRT1       TRT2                               Transient

== Description:==
80   cycles        over       40     years Temperature     443.4      557.4   F Pressure       1692       2317    psig                                        N =    2.0  cycles/year Sy          43.8        42.6   ksi KIc         200.0      200.0   ksiin                                                                   Position 7 KIa         200.0      200.0   ksiin                      Operating                      TRT1       TRT2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         -0.097      1.296                                   0         0.0             64.359     49.628     14.731 2          7.596      0.314                                   1         2.0             64.381     49.645     14.736 3          8.926      1.073                                   2         4.0             64.419     49.675     14.745 4        15.799       2.965                                   3         6.0             64.458     49.705     14.754 5        20.199       5.609                                   4         8.0             64.497     49.735     14.763 6        22.374       7.456                                   5        10.0             64.536     49.765     14.772 7        23.858       9.127                                   6        12.0             64.575     49.795     14.780 8        23.895      10.028                                   7        14.0             64.614     49.825     14.789 9        23.591      10.686                                   8        16.0             64.653     49.855     14.798 10        22.575      10.691                                   9        18.0             64.692     49.885     14.807 11        18.078       8.372                                  10        20.0             64.732     49.915     14.816 12        21.311       9.916                                  11        22.0             64.771     49.945     14.825 13        22.588      10.205                                  12        24.0             64.810     49.976     14.834 14        22.546       9.905                                  13        26.0             64.849     50.006     14.843 15        21.928       9.491                                  14        28.0             64.888     50.036     14.852 16        17.326       7.446                                  15        30.0             64.928     50.067     14.861 17          4.367      1.684                                  16        32.0             64.967     50.097     14.870 17        34.0             65.007     50.127     14.879
* Condition  Description                                           18        36.0             65.046     50.158     14.888 TRT1     Time step 5 at 0.278 hr. - Maximum KI                 19        38.0             65.085     50.188     14.897 TRT2     Time step 8 at 1.418 hr. - Minimum KI                 20        40.0             65.125     50.219     14.906 21        42.0             65.165     50.249     14.915 22        44.0             65.204     50.280     14.924 23        46.0             65.244     50.310     14.934 24        48.0             65.283     50.341     14.943 25        50.0             65.323     50.371     14.952 26        52.0             65.363     50.402     14.961 27        54.0             65.403     50.433     14.970 28        56.0             65.443     50.464     14.979 29        58.0             65.482     50.494     14.988 30        60.0             65.522     50.525     14.997 Page 74

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-6: Fatigue Crack Growth for Downhill Side - Refueling STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      RF1         RF2                              Transient

== Description:==
80   cycles        over       40     years Temperature     32.0        140.0  F Pressure         0           0    psig                                        N =    2.0  cycles/year Sy          50.0        48.5   ksi KIc         63.5        200.0  ksiin                                                                   Position 7 KIa         43.2        105.3  ksiin                      Operating                       RF1        RF2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         -1.034       0.410                                  0         0.0             54.137     37.685     16.452 2          6.136      -1.478                                  1         2.0             54.156     37.698     16.458 3          6.728      -1.554                                  2         4.0             54.189     37.721     16.468 4        11.118       -2.447                                  3         6.0             54.222     37.744     16.478 5        12.933       -2.684                                  4         8.0             54.254     37.767     16.488 6        13.508       -2.754                                  5        10.0             54.287     37.790     16.498 7        13.636       -2.816                                  6        12.0             54.320     37.812     16.508 8        13.111       -2.783                                  7        14.0             54.353     37.835     16.518 9        12.453       -2.669                                  8        16.0             54.386     37.858     16.528 10        11.656       -2.515                                  9        18.0             54.419     37.881     16.538 11          9.511      -2.035                                 10        20.0             54.452     37.904     16.548 12        11.218       -2.375                                 11        22.0             54.485     37.927     16.558 13        12.125       -2.502                                 12        24.0             54.517     37.950     16.568 14        12.312       -2.456                                 13        26.0             54.551     37.973     16.578 15        12.086       -2.355                                 14        28.0             54.584     37.996     16.588 16          9.579      -1.852                                 15        30.0             54.617     38.019     16.598 17          2.556      -0.538                                 16        32.0             54.650     38.042     16.608 17        34.0             54.683     38.065     16.618
* Condition  Description                                           18        36.0             54.716     38.088     16.628 RF1      Time step 7 at 0.171 hr. - Maximum KI                 19        38.0             54.749     38.111     16.638 RF2      Time step 1 at 0.0001 hr. - Minimum KI                20        40.0             54.783     38.134     16.648 21        42.0             54.816     38.158     16.658 22        44.0             54.849     38.181     16.668 23        46.0             54.882     38.204     16.679 24        48.0             54.916     38.227     16.689 25        50.0             54.949     38.250     16.699 26        52.0             54.983     38.274     16.709 27        54.0             55.016     38.297     16.719 28        56.0             55.050     38.320     16.729 29        58.0             55.083     38.344     16.740 30        60.0             55.117     38.367     16.750 Page 75

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-7: Fatigue Crack Growth for Downhill Side - Loss of Load STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*     LL1          LL2                              Transient

== Description:==
210   cycles        over       40     years Temperature    575.8        588.8  F Pressure      2710         1844   psig                                        N =   5.25  cycles/year Sy          42.4        42.2   ksi KIc        200.0        200.0  ksiin                                                                   Position 7 KIa        200.0        200.0  ksiin                      Operating                       LL1        LL2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         0.950        1.766                                  0         0.0             58.834     42.239     16.595 2         3.481       -2.663                                  1         5.3             58.857     42.255     16.601 3         4.682       -2.204                                  2        10.5             58.892     42.281     16.611 4         9.183       -2.532                                  3        15.8             58.928     42.306     16.621 5        13.346       -0.958                                  4        21.0             58.963     42.332     16.631 6        15.991        0.418                                  5        26.3             58.999     42.357     16.642 7        18.333        1.738                                  6        31.5             59.035     42.383     16.652 8        19.392        2.668                                  7        36.8             59.070     42.409     16.662 9        19.973        3.496                                  8        42.0             59.106     42.434     16.672 10       19.585        3.858                                  9        47.3             59.142     42.460     16.682 11       15.468        2.902                                 10        52.5             59.177     42.486     16.692 12       18.216        3.502                                 11        57.8             59.213     42.511     16.702 13       18.870        3.448                                 12        63.0             59.249     42.537     16.712 14       18.370        3.223                                 13        68.3             59.285     42.563     16.722 15       17.573        3.041                                 14        73.5             59.321     42.589     16.732 16       13.802        2.360                                 15        78.8             59.357     42.614     16.742 17        3.440        0.326                                 16        84.0             59.393     42.640     16.753 17        89.3             59.429     42.666     16.763
* Condition  Description                                           18        94.5             59.465     42.692     16.773 LL1     Time step 2 at 0.003 hr. - Maximum KI                 19        99.8             59.501     42.718     16.783 LL2     Time step 12 at 0.033 hr. - Minimum KI                20       105.0             59.537     42.744     16.793 21       110.3             59.573     42.770     16.804 22       115.5             59.610     42.796     16.814 23       120.8             59.646     42.822     16.824 24       126.0             59.682     42.848     16.834 25       131.3             59.718     42.874     16.844 26       136.5             59.755     42.900     16.855 27       141.8             59.791     42.926     16.865 28       147.0             59.828     42.952     16.875 29       152.3             59.864     42.978     16.886 30       157.5             59.900     43.005     16.896 Page 76

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-8: Fatigue Crack Growth for Downhill Side - Loss of Power STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*     LP1          LP2                              Transient

== Description:==
100   cycles        over        40    years Temperature    553.8        600.5  F Pressure      2295         2464   psig                                        N =    2.5  cycles/year Sy          42.7        42.1   ksi KIc        200.0        200.0  ksiin                                                                   Position 7 KIa        200.0        200.0  ksiin                      Operating                       LP1        LP2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         0.946        1.583                                  0         0.0             54.961     47.394      7.567 2         2.604       -0.933                                  1         2.5             54.986     47.416      7.570 3         3.602       -0.235                                  2         5.0             55.019     47.444      7.575 4         7.174        0.851                                  3         7.5             55.053     47.473      7.580 5        10.560       3.271                                   4        10.0             55.086     47.502      7.584 6        12.672       5.130                                   5        12.5             55.119     47.530      7.589 7        14.460       6.893                                   6        15.0             55.152     47.559      7.593 8        15.213       7.988                                   7        17.5             55.186     47.588      7.598 9        15.652       8.849                                   8        20.0             55.219     47.617      7.603 10        15.355        9.056                                  9        22.5             55.253     47.645      7.607 11        12.150        7.048                                 10        25.0             55.286     47.674      7.612 12        14.353        8.381                                 11        27.5             55.319     47.703      7.616 13        14.958        8.536                                 12        30.0             55.353     47.732      7.621 14        14.686        8.199                                 13        32.5             55.386     47.761      7.626 15        14.157        7.823                                 14        35.0             55.420     47.790      7.630 16        11.141        6.120                                 15        37.5             55.454     47.819      7.635 17         2.671        1.294                                 16        40.0             55.487     47.848      7.639 17        42.5             55.521     47.877      7.644
* Condition  Description                                           18        45.0             55.555     47.906      7.649 LP1      Time step 2 at 0.003 hr. - Maximum KI                 19        47.5             55.588     47.935      7.653 LP2      Time step 11 at 0.053 hr. - Minimum KI                20        50.0             55.622     47.964      7.658 21        52.5             55.656     47.993      7.663 22        55.0             55.690     48.022      7.667 23        57.5             55.723     48.052      7.672 24        60.0             55.757     48.081      7.677 25        62.5             55.791     48.110      7.681 26        65.0             55.825     48.139      7.686 27        67.5             55.859     48.169      7.691 28        70.0             55.893     48.198      7.695 29        72.5             55.927     48.227      7.700 30        75.0             55.961     48.257      7.705 Page 77

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-9: Fatigue Crack Growth for Downhill Side - Reactor Trip STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      RT1        RT2                               Transient

== Description:==
250   cycles        over       40     years Temperature     457.4      537.4   F Pressure       2205       1803    psig                                        N =   6.25  cycles/year Sy          43.6        42.8   ksi KIc         200.0      200.0   ksiin                                                                   Position 7 KIa         200.0      200.0   ksiin                      Operating                       RT1        RT2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         -0.344      0.927                                   0         0.0             70.741     52.016     18.725 2          9.813      2.017                                   1         6.3             70.774     52.040     18.734 3        11.437       2.874                                   2        12.5             70.816     52.071     18.745 4        20.106       5.810                                   3        18.8             70.859     52.103     18.756 5        25.541       8.607                                   4        25.0             70.902     52.134     18.768 6        28.273      10.252                                   5        31.3             70.945     52.166     18.779 7        30.240      11.515                                   6        37.5             70.987     52.197     18.790 8        30.411      11.924                                   7        43.8             71.030     52.229     18.802 9        30.082      12.163                                   8        50.0             71.073     52.260     18.813 10        28.819      11.886                                   9        56.3             71.116     52.292     18.824 11        23.051       9.451                                  10        62.5             71.159     52.324     18.836 12        27.143      11.204                                  11        68.8             71.202     52.355     18.847 13        28.677      11.791                                  12        75.0             71.246     52.387     18.859 14        28.509      11.714                                  13        81.3             71.289     52.419     18.870 15        27.648      11.387                                  14        87.5             71.332     52.450     18.881 16        21.824       8.989                                  15        93.8             71.375     52.482     18.893 17          5.557      2.099                                  16       100.0             71.418     52.514     18.904 17       106.3             71.462     52.546     18.916
* Condition  Description                                           18       112.5             71.505     52.578     18.927 RT1      Time step 13 at 0.171 hr. - Maximum KI                19       118.8             71.548     52.610     18.939 RT2      Time step 8 at 0.025 hr. - Minimum KI                 20       125.0             71.592     52.642     18.950 21       131.3             71.635     52.674     18.962 22       137.5             71.679     52.706     18.973 23       143.8             71.722     52.738     18.985 24       150.0             71.766     52.770     18.996 25       156.3             71.810     52.802     19.008 26       162.5             71.853     52.834     19.019 27       168.8             71.897     52.866     19.031 28       175.0             71.941     52.898     19.043 29       181.3             71.985     52.931     19.054 30       187.5             72.029     52.963     19.066 Page 78

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-10: Fatigue Crack Growth for Downhill Side - Inadvertent Depressurization STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*     ID1          ID2                              Transient

== Description:==
100   cycles        over       40     years Temperature    557.4        556.6  F Pressure      2317         1161   psig                                        N =    2.5  cycles/year Sy         42.6        42.6   ksi KIc        200.0        200.0  ksiin                                                                   Position 7 KIa        200.0        200.0  ksiin                      Operating                       ID1        ID2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         0.944        1.606                                  0         0.0             55.203     40.508     14.695 2         2.677       -2.583                                  1         2.5             55.235     40.531     14.703 3         3.690       -2.226                                  2         5.0             55.268     40.556     14.712 4         7.328       -2.753                                  3         7.5             55.301     40.580     14.721 5        10.757       -1.643                                  4        10.0             55.335     40.605     14.730 6        12.894       -0.738                                  5        12.5             55.368     40.629     14.739 7        14.702        0.007                                  6        15.0             55.402     40.654     14.748 8        15.463        0.486                                  7        17.5             55.435     40.678     14.757 9        15.902        1.001                                  8        20.0             55.468     40.703     14.766 10       15.598        1.266                                  9        22.5             55.502     40.727     14.775 11       12.345        0.914                                 10        25.0             55.536     40.752     14.784 12       14.583        1.172                                 11        27.5             55.569     40.777     14.792 13       15.199        1.177                                 12        30.0             55.603     40.801     14.801 14       14.922        1.172                                 13        32.5             55.637     40.826     14.810 15       14.385        1.175                                 14        35.0             55.670     40.851     14.819 16       11.320        0.928                                 15        37.5             55.704     40.876     14.828 17        2.717       -0.029                                 16        40.0             55.738     40.900     14.837 17        42.5             55.772     40.925     14.846
* Condition  Description                                           18        45.0             55.805     40.950     14.855 ID1     Time step 1 at 0.0001 hr. - Maximum KI                19        47.5             55.839     40.975     14.864 ID2     Time step 9 at 0.022 hr. - Minimum KI                 20        50.0             55.873     41.000     14.873 21        52.5             55.907     41.025     14.882 22        55.0             55.941     41.050     14.891 23        57.5             55.975     41.075     14.901 24        60.0             56.009     41.100     14.910 25        62.5             56.043     41.125     14.919 26        65.0             56.077     41.150     14.928 27        67.5             56.111     41.175     14.937 28        70.0             56.146     41.200     14.946 29        72.5             56.180     41.225     14.955 30        75.0             56.214     41.250     14.964 Page 79

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-11: Fatigue Crack Growth for Downhill Side - Excessive Feedwater Flow STRESS INTENSITY FACTORS                                                            FATIGUE CRACK GROWTH Condition*      EFF1       EFF2                               Transient

== Description:==
40   cycles        over       40     years Temperature      448.6      557.4   F Pressure        1809       2317    psig                                        N =    1.0  cycles/year Sy           43.7        42.6   ksi KIc          200.0      200.0   ksiin                                                                   Position 7 KIa          200.0      200.0   ksiin                      Operating                      EFF1       EFF2 Crack Front             KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position     (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1          -0.519      0.944                                   0         0.0             65.553     55.203     10.350 2           9.452      2.677                                   1         1.0             65.592     55.236     10.356 3         10.871       3.690                                   2         2.0             65.632     55.269     10.362 4         18.778       7.328                                   3         3.0             65.672     55.303     10.369 5         23.040      10.757                                   4         4.0             65.711     55.336     10.375 6         24.576      12.894                                   5         5.0             65.751     55.370     10.381 7         25.052      14.702                                   6         6.0             65.791     55.403     10.388 8         24.101      15.463                                   7         7.0             65.830     55.437     10.394 9         23.123      15.902                                   8         8.0             65.870     55.470     10.400 10         21.900      15.598                                   9         9.0             65.910     55.504     10.406 11         17.871      12.345                                  10        10.0             65.950     55.537     10.413 12         21.256      14.583                                  11        11.0             65.990     55.571     10.419 13         23.048      15.199                                  12        12.0             66.030     55.604     10.425 14         23.529      14.922                                  13        13.0             66.070     55.638     10.432 15         23.259      14.385                                  14        14.0             66.110     55.672     10.438 16         18.487      11.320                                  15        15.0             66.150     55.706     10.444 17           4.524      2.717                                  16        16.0             66.190     55.739     10.451 17        17.0             66.230     55.773     10.457
* Condition   Description                                           18        18.0             66.270     55.807     10.463 EFF1      Time step 4 at 0.013 hr. - Maximum KI                 19        19.0             66.310     55.841     10.470 EFF2      Time step 1 at 0.0001 hr. - Minimum KI                20        20.0             66.351     55.875     10.476 21        21.0             66.391     55.909     10.482 22        22.0             66.431     55.943     10.489 23        23.0             66.472     55.977     10.495 24        24.0             66.512     56.011     10.501 25        25.0             66.553     56.045     10.508 26        26.0             66.593     56.079     10.514 27        27.0             66.634     56.113     10.521 28        28.0             66.674     56.147     10.527 29        29.0             66.715     56.181     10.533 30        30.0             66.756     56.216     10.540 Page 80

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-12: Fatigue Crack Growth for Downhill Side - Leak Test STRESS INTENSITY FACTORS                                                           FATIGUE CRACK GROWTH Condition*      LT1         LT2                              Transient

== Description:==
280   cycles        over       40     years Temperature     238.0       82.0   F Pressure       2351         602   psig                                        N =    7.0  cycles/year Sy          46.4        50.0   ksi KIc         200.0       115.6  ksiin                                                                   Position 7 KIa         200.0       60.6   ksiin                      Operating                       LT1        LT2 Crack Front            KI                                        Time      Cycle        a     KI(a)      KI(a)       KI        a Position    (ksiin)    (ksiin)                            (end of yr.)            (in.)  (ksiin)   (ksiin)   (ksiin)    (in.)
1         -0.484      -0.180                                  0         0.0             64.403     46.197     18.206 2          7.656       1.843                                  1         7.0             64.442     46.225     18.217 3          8.820       2.100                                  2        14.0             64.481     46.253     18.228 4        15.468       3.646                                   3        21.0             64.520     46.281     18.239 5        19.687       4.609                                   4        28.0             64.559     46.309     18.250 6        21.987       5.170                                   5        35.0             64.598     46.337     18.261 7        23.902       5.696                                   6        42.0             64.637     46.365     18.272 8        24.423       5.902                                   7        49.0             64.676     46.393     18.283 9        24.437       5.952                                   8        56.0             64.715     46.421     18.294 10       23.571        5.765                                  9        63.0             64.754     46.449     18.305 11       18.741        4.566                                 10        70.0             64.793     46.477     18.316 12       22.027        5.351                                 11        77.0             64.832     46.505     18.327 13       23.041        5.545                                 12        84.0             64.872     46.533     18.338 14       22.643        5.386                                 13        91.0             64.911     46.561     18.350 15       21.785        5.139                                 14        98.0             64.950     46.589     18.361 16       17.137        4.030                                 15       105.0             64.990     46.618     18.372 17         4.398       1.055                                 16       112.0             65.029     46.646     18.383 17       119.0             65.068     46.674     18.394
* Condition  Description                                           18       126.0             65.108     46.703     18.405 LT1     Time step 6 at 3.92 hr. - Maximum KI                  19       133.0             65.147     46.731     18.416 LT2     Time step 2 at 0.12 hr. - Minimum KI                  20       140.0             65.187     46.759     18.428 21       147.0             65.227     46.788     18.439 22       154.0             65.266     46.816     18.450 23       161.0             65.306     46.845     18.461 24       168.0             65.346     46.873     18.472 25       175.0             65.385     46.902     18.484 26       182.0             65.425     46.930     18.495 27       189.0             65.465     46.959     18.506 28       196.0             65.505     46.987     18.517 29       203.0             65.545     47.016     18.529 30       210.0             65.585     47.045     18.540 Page 81

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-13: Stress Intensification Factors for Downhill Side - Faulted Conditions STRESS INTENSITY FACTORS                             TOTAL STRESS INTENSITY FACTORS FOR OPERATING CONDITIONS                                   WITH RESIDUAL STRESS Condition*   LLOCA        LSLB Temperature     32.0       207.8 F Pressure        60         1316   psig                          ao = 2.1482    in.
Sy          50.0        46.9   ksi KIc         63.5       200.0 ksiin KIa         43.2       200.0 ksiin                  Condition*   LLOCA         LSLB Crack Front            KI                                Crack Front           KI Position    (ksiin)    (ksiin)                        Position    (ksiin)    (ksiin) 1         -6.103      -3.533                            1         -7.804      -5.234 2        38.630      26.671                             2        52.562      40.603 3        42.411      29.689                             3        58.128      45.406 4        70.343      50.026                             4        97.521      77.204 5        81.924      59.828                             5        115.814     93.718 6        85.195      63.651                             6        122.799     101.255 7        85.364      65.558                             7        125.865     106.059 8        81.305      64.020                             8        121.403     104.118 9        76.653      61.644                             9        114.291     99.282 10        71.333      58.060                             10       104.780     91.507 11        58.183      46.864                             11       82.856      71.537 12        68.598      55.118                             12       96.126      82.646 13        74.395      58.941                             13       101.321     85.867 14        75.853      59.256                             14       100.242     83.645 15        74.663      57.792                             15       96.364      79.493 16        59.246      45.712                             16       76.014      62.480 17        15.675      12.059                             17       21.451      17.835
* Condition  Description LLOCA     Time step 15 at 0.03889 hr. (140 sec.) - Maximum KI LSLB     Time step 9 at 0.09222 hr. (332 sec.) - Maximum KI Page 82

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-14: EPFM Evaluations for Downhill Side - Reactor Trip EPFM Equations:                          Jmat = C(a)m                           C=
Tmat = (E/f 2)*Cm(a)m-1               m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00        28.672       43.367       72.039    2.3726    74.344      0.185        0.591    Yes 2.00       1.00        57.345       43.367      100.711    2.5108   106.918      0.382        1.223    Yes 3.00       1.50        86.017       65.050      151.067    2.8646   171.305      0.982        3.139    Yes 8.00       1.00       229.378       43.367      272.745    4.3038   379.096      4.808      15.371     Yes 15.00      1.00       430.084       43.367      473.451    8.4835   923.906    28.558       91.296      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 4.3064     4.3064      123.476     186.756       310.232    4.9137   460.742      7.102      22.705    22.705 at Jmat =   0.982     kips/in,         Tmat = 242.047 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00        43.008       43.367       86.375    2.4360    90.321      0.273      2.473      Yes Page 83

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure B-1: J-T Diagram for Downhill Side - Reactor Trip 10 9
8 Instablility Point 7
J-T Material 6
J-Integral (kips/in)
J-T Applied 5
4 3
2 1
SF = 3 & 1.5 0
0      5       10         15      20         25          30       35       40      45      50 Tearing Modulus Page 84

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-15: EPFM Evaluations for Downhill Side - Refueling EPFM Equations:                          Jmat = C(a)m                           C=
Tmat = (E/f 2)*Cm(a)m-1               m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00         0.000       55.130       55.130    2.2923    55.923      0.097        0.302    Yes 3.00       1.50         0.000       82.695       82.695    2.3729    85.346      0.227        0.704    Yes 10.00      3.00         0.000     165.391       165.391    2.8082   185.692      1.075        3.335    Yes 10.00      4.00         0.000     220.521       220.521    3.2597   266.751      2.218        6.881    Yes 10.00      7.00         0.000     385.912       385.912    5.3881   600.168    11.228       34.834      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 6.0382     6.0382        0.000     332.889       332.889    4.5793   477.273      7.101      22.029    22.029 at Jmat =   0.227     kips/in,         Tmat = 1357.163 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors         KI*p         KI*s        KI*(a)       ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00         0.000       55.130       55.130    2.2923    55.923      0.097      2.474      Yes Page 85

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure B-2: J-T Diagram for Downhill Side - Refueling 10 9
8 Instablility Point 7
J-T Material 6
J-T Applied J-Integral (kips/in) 5 4
3 2
1 SF = 3 & 1.5 0
0      5          10       15     20         25          30        35      40      45      50 Tearing Modulus Page 86

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table B-16: EPFM Evaluations for Downhill Side - LLOCA EPFM Equations:                           Jmat = C(a)m                          C=
Tmat = (E/f 2)*Cm(a)m-1              m=
Japp = [KI'(ae)] 2/E' Tapp = (E/f 2)*(dJapp/da)
Ductile Crack Growth Stability Criterion:             Tapp < Tmat At instability:                                       Tapp = Tmat Safety Factors          KI*p        KI*s        KI*(a)       ae     KI'(ae)     Japp        Tapp    Stable?
Primary Secondary        (ksiin)    (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in) 1.00       1.00          0.780      76.629       77.409    2.3549    79.587      0.197        0.613    Yes 1.50       1.00          1.170      76.629       77.799    2.3562    80.010      0.200        0.619    Yes 200.00      1.00       156.040       76.629      232.668    3.3765   286.443      2.558        7.935    Yes 300.00      1.00       234.059       76.629      310.688    4.2761   430.443      5.776      17.918     Yes 400.00      1.00       312.079       76.629      388.708    5.4341   607.088    11.489       35.642      No Iterate on safety factor until Tapp = Tmat to determine Jinstability :
Jinstability   Tapp      Tmat 4.3004     4.3004         3.355    329.534       332.889    4.5793   477.273      7.101      22.029    22.029 at Jmat =   0.200     kips/in,         Tmat = 1584.010 Applied J-Integral Criterion:                          Japp < J0.1 where,            J0.1 = Jmat at a = 0.1 in.
Safety Factors          KI*p        KI*s        KI*(a)       ae     KI'(ae)     Japp         J0.1     OK?
Primary Secondary (ksiin)           (ksiin)     (ksiin)     (in.)  (ksiin)  (kips/in)    (kips/in) 1.50       1.00          1.170      76.629       77.799    2.3562    80.010      0.200      2.474      Yes Page 87

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure B-3: J-T Diagram for Downhill Side - LLOCA 10 9
8 Instablility Point 7
J-T Material 6
J-Integral (kips/in) 5 J-T Applied 4
3 2
1 SF = 1.5 & 1 0
0      5        10        15   20         25          30       35      40      45      50 Tearing Modulus Page 88

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
APPENDIX C: CALCULATION OF AVAILABLE YEARS OF SERVICE BASED ON AVAILABLE REINFORCEMENT AREA DUE TO CRACK GROWTH C.1   Purpose The purpose of this appendix is to demonstrate that the as-repaired RVCH continues to satisfy the primary stress limits of NB-3000, considering postulated flaws emanating from the original J-groove weld. This is accomplished by comparing the available reinforcement areas in the vicinity of the repaired nozzles with the areas removed from consideration of carrying primary load, in accordance with NB-3330. The acceptable life for crack growth is determined, and the limiting case is reported.
C.2    Analytical Methodology The approach of calculating available years of service is based on determining the available area of reinforcement as required per NB-3330 Reference [C1]. The repair results in removal of the structural material. In addition for repaired nozzles, as left Alloy 600 region of the original J-groove weld is not considered as structural material as it contains flaws.
Finally, additional area due to postulated crack growth into the carbon steel of the head is also discounted from the available structural area.
Analyzed nozzles are those already repaired and in operation as well as those being repaired. Nozzles previously repaired and in operation are: # 5, #14, #17, #18, #23, #37,
      #38, #49 and #63 (Reference [C11]). Nozzles being repaired in the 2016 outage are #30,
      #40 and #51 (References [C14] to [C16]). The dates for these repairs are listed as follows:
Nozzle     Repair Date 5      May 2012 14      May 2015 17      May 2012 18      May 2015 23      May 2015 30      Current Oct-2016 Outage 37      Nov 2013 38      May 2012 40      Current Oct-2016 Outage 49      May 2013 51      Current Oct-2016 Outage 63      May 2012 Note that for the previously repaired nozzles the detailed evaluations are contained in Sub-Sections C.3.6, C.4 to C.6, while for the current (2016) nozzle repairs the detailed evaluations are provided in Sub-Section C.7.
The calculation of the available years of service is performed in MS Excel spread sheet Harris_Sizing_Tables.xlsx.
There are two approaches which are used in this calculation. Both of them follow the guidelines of NB-3330 Reference [C1]. These approaches are described below:
Page 89

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Approach 1 is the more conservative approach and evaluates each repaired nozzle on an individual basis by imposing a limit of reinforcement equal to half the distance to the nearest nozzle. This is roughly equivalent to assuming that the repaired nozzle is surrounded by other nozzles that have been repaired. This approach is described below:
: 1) Calculation of structural area removed due to nozzle bore, repair and corrosion
: 2) Structural area of flawed J-groove weld is determined and considered as area removed
: 3) Calculation of limits of reinforcement for determination of area of reinforcement
: 4) Calculation of available head area of reinforcement
: 5) Calculation of reinforcement area of portion of the IDTB weld
: 6) Determination of structural area lost due to postulated crack growth in Alloy 600 and into the carbon steel of the head
: 7) Calculation of available area of reinforcement by adding all areas of reinforcement and subtracting areas lost due to bore and crack growth
: 8) Available years of service is determined as an iterative process by calculating loss of structural area due to corrosion and postulated crack growth until area of reinforcement is exhausted.
Approach 2 removes some of the conservatism of Approach 1 and was used to examine the bounding case as determined by Approach 1. This approach analyzes the ligament between adjacent nozzles, where one nozzle is in the repaired condition and one nozzle is unrepaired. This approach is appropriate for use as long as there are no repaired nozzles in neighboring penetrations. This approach is described below:
: 1) Calculation of structural area removed due to nozzle bore, repair and corrosion
: 2) Structural area of flawed J-groove weld (i.e. repaired nozzle) is determined and considered as area removed; the structural area of the unflawed J-groove weld (i.e.
unrepaired nozzle) is determined and discounted based upon the material strength ratio
: 3) Calculation of limits of reinforcement for determination of area of reinforcement
: 4) Calculation of available head area of reinforcement
: 5) Calculation of reinforcement area of portion of the IDTB weld for the repaired nozzle only
: 6) Determination of structural area lost due to postulated crack growth in Alloy 600 and into the carbon steel of the head for the repaired nozzle location
: 7) Calculation of available area of reinforcement by adding all areas of reinforcement and subtracting areas lost due to bore, crack growth, and a portion of the unflawed J-groove area as determined by material strength ratio Page 90

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
: 8) Available years of service is determined as an iterative process by calculating loss of structural area due to corrosion and postulated crack growth until area of reinforcement is exhausted.
C.2.1      Conservatisms
* Crack growth is considered to be linear over the course of 30 years. This slightly overestimates flaw growth in the early years.
* The crack growth area at the IDTB weld anomaly was conservatively taken as
[             ] . This crack is specified to have a maximum flaw radius of [              ],
2 which would produce a smaller area when calculated (maximum flaw depth x / 4)
[C6].
* For the IDTB Weld, the area is calculated assuming machining to remove IDTB overlap onto the original weld (Detail D, Ref. [C2], conservatively, doubled to account for the larger side of the weld in Approach 1.
* This method does not account for load distribution from weak ligament to stronger/larger structural area, compared to detailed limit load analysis.
* For Nozzle 23 Overbore, the diameter of the overbore is considered for the entire length of the opening. For all other repaired openings, the diameter is conservatively considered to be [                  ] . This accounts for the counterbore from the outer surface of the head.
* In Section C.4, using Approach 2, the downhill J-groove weld for Nozzle 7 is conservatively considered to be 1.15 times larger than the value of the downhill J-groove weld for Nozzle 14 Minimum. This is conservative because J-groove weld areas should increase as the nozzle moves further from the head center and Nozzle 14 Minimum is further from center than Nozzle 7.
* Approach 2 uses the minimum design thickness for the head at the unrepaired nozzle.
C.3     Calculation of Available Reinforcement Areas using Approach 1 The following approach is used for calculation of the available reinforcement area.
C.3.1      Tentative Thickness Calculation The tentative thickness of the Reactor Vessel Closure Head (RVCH) is determined by the approach specified in NB-3324 of the ASME Boiler and Pressure Vessel Code Reference
[C1]. As stated in the article, except in local areas, the wall thickness of a vessel shall never be less than that obtained from the formula in NB-3324.2 for spherical shells.
Formula NB-3324.2 (Spherical Shells):
PR (Equation 1)                      t=
2S m  P Page 91

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Where:
t = Tentative thickness of shell or head, in.
P = Design Pressure, psi R = Inside radius of shell or head, in.
Sm = Design stress intensity values, psi C.3.1.1           Closure Head (Spherical Head)
[                 ] Reference [C3]
[                ]  Reference [C2]
Temperature, design      [          ] Reference [C3]
Sm = 26,700 psi at the design temperature for SA-533 Grade B Class 1, Reference [C1]
Substituting these values into Equation (1) yields the tentative thickness (tt) of the RVCH to be:
C.3.2         Calculation of Structural area removed due to nozzle bore The following table shows the calculation of area lost due to nozzle bore used in MS Excel spread sheet Harris_Sizing_Tables.xlsx. Figure C1 shows used parameters.
Table C1: Area Removed from Selected Nozzles Parameter                                 Reference Nozzle Plane Coordinate x, in.              [                   ]            [C10]
Nozzle Plane Coordinate y, in.              [                   ]            [C10]
(1)
Opening Diameter, do, in.
[                             [C5][C4][C13]
                                                                      ]
Plane Distance of center of nozzle, C,
                                                            =  +                      [C10]
in.
Inside radius of the head, Ri, in.                 [    ]                     [C2]
Tentative thickness of RVCH, tt, in.          [               ]            Calculated Tentative outside radius of head, Rt, in.                                             [          ]               Calculated Vertical Distance to inside radius, Hi,
                                                            =                      Calculated in.
Vertical Distance to outer tentative
                                                            =                      Calculated thickness, Ht, in.
Depth of opening, to, in.                        [        ]                Calculated Opening area removed Armv, in    2
[          ]               Calculated Page 92

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Note(s):
(1) The corrosion rate is considered to [                   ] , reference [C4]. This is multiplied by 2 to account for corrosion on both sides of the diameter.
C.3.3     Minimum Reinforcement Area The following calculations for the minimum required reinforcement are based on the approach listed in ASME Boiler and Pressure Code, Reference [C1].
Per NB-3334, the boundaries of the cross-sectional area in any plane normal to the vessel wall and passing through the center of the opening and within which metal shall be located in order to have value as reinforcement are designated as the limits of reinforcement for that plane.
First, metal will be identified that may be considered for reinforcement:
NB-3335 (b) and (e) of the ASME code require that the reinforcing metal be continuous with vessel wall metal or joined to it by full penetration weld. Since the nozzles are joined by partial penetration welds, the nozzle wall metal is not considered for reinforcement.
NB-3335 (c) states that weld metal which is fully continuous with the vessel wall may be considered for reinforcement. The IDTB weld satisfies this criterion and can contribute towards reinforcement; the j-groove weld and buttering do not satisfy this criterion under cracked conditions and therefore will not be considered as contributing towards reinforcement. NB-3335 (d) of the ASME Code requires that the mean coefficient of thermal expansion of the reinforcing metal (including weld metal) be within 15% of the value of the vessel wall material.
Second, the limits of reinforcement will be calculated:
NB-3334 establishes the limits of reinforcement area along and normal to the vessel surface. Since the nozzle wall metal is not considered for reinforcement, only the limit along the surface of the head mean radius (Lw) is relevant for this calculation. For the limit of reinforcement measured along the mid-surface of the nominal vessel wall thickness, NB-3334.1 requires:
a) One hundred percent of the required reinforcement shall be within a distance on each side of the axis of the opening equal to the greater of the following:
: 1) The diameter of finished opening in the corroded condition, Lw1
: 2) The sum of the radius of the finished opening in the corroded condition, the thickness of the nozzle wall, and the thickness of the vessel wall, Lw2 b) Two-thirds of the required reinforcement shall be within a distance on each side of the axis of the opening equal to the greater of the following:
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
: 1)   + .  , where R is the mean radius of the shell or head, t is the nominal vessel wall thickness, and r is the radius of the finished opening in the corroded condition
: 2) The radius of the finished opening in the corroded condition plus two-thirds the sum of the thicknesses of the vessel wall and the nozzle wall Furthermore, the ASME Code prohibits the same reinforcing material from being applied to more than one opening and requires that one half of the reinforcing material lie on each side of the opening.
These conditions restrict Lw to one-half of the distance between similar adjacent penetrations less the radius of the opening. Axis-to-axis distances between adjacent nozzles are considered rather than distances along the curved surface of the RVCH mean radius.
The following table shows the calculation of limits of reinforcement used in MS Excel spread sheet Harris_Sizing_Tables.xlsx. Figure C1 shows used parameters.
Table C2: Limits of Reinforcement for Selected Openings Parameter                               References Diameter do, in. (upper)                 Specific for each nozzle    [C5][C13]
Radius, r, in. (upper)                            r = do/2           Calculated RVCH wall thickness, t, in.              Specific for each nozzle     [C5][C4]
Nozzle wall thickness, tn, in.               No credit taken              -
Inside radius of RVCH, Ri, in.                  [          ]            [C2]
Mean radius of RVCH, Rm, in.                      = + 2             Calculated Distance to     NB-3334.1 (a)(1)              Lw1 = 2r           Calculated accommodate 100%         NB-3334.1 (a)(2)            Lw2 = r+t+tn         Calculated reinforcement > of Lw & Lw                                         Calculated 1      2 Distance to     NB-3334.1 (b)(1)              + 0.5              Calculated accommodate 2( +     )
2/3         NB-3334.1 (b)(2)            +             3      Calculated reinforcement     > of (b)(1) & (b)(2)                             Calculated Grid distance for nozzles, in.            [            ]          [C10]
Center line distance between this opening and the nearest CRDM                  [              ]         [C10]
opening, in.
Max. length available for (see note below)         Calculated reinforcement, Lr, in.
The following considerations were taken in Table C2:
* Since the nozzle wall is not fully continuous with the head, the metal cannot be counted as contributing to the area of reinforcement per NB-3335. Therefore, the nozzle wall thickness is considered to be zero (tn = 0 in.).
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
* The reinforcement limit (Lr) for the CRDM nozzle is calculated by one half of the centerline distance between the two nearest consecutive openings
( [                           ] ).
C.3.4     Required Area of Reinforcement NB-3332.2 indicates that reinforcement is required for the RVCH with the tentative thickness calculated in C.3.1 By NB-3332.2, the total cross-sectional area of reinforcement, A, shall not be less than:
                                                  =
Where d = finished diameter of a circular opening (or chord of an elliptical opening) in the corroded condition, F = a correction factor which compensates for the variation in pressure stresses on different planes with respect to the axis of a vessel (correlates to F
          = 1.00 with a 0.00&deg; angle of the plane with the longitudinal axis), and tr (in this case) is the minimum required thickness in the absence of the opening. The body of this calculation will refer to do as the diameter of the circular opening and tr as the depth of reinforcement. Not less than half the required material shall be on each side of the center line. Figure C1 diagrams the reinforcement area above the tentative thickness.
Figure C1: Reinforcement Area Diagram Page 95

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C2: Overview of Approach 1 Page 96

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
The following table shows calculation of IDTB weld reinforcement area used in MS Excel spread sheet Harris_Sizing_Tables.xlsx.
Table C3: IDTB Weld Reinforcement Parameter                                           Reference Outside Diameter at IDTB Weld, dwo in.                                               [C2]
[       ]
Inside Diameter at IDTB Weld, dwi in.                                                [C2]
[        ]
Width of IDTB Weld, w in.                         [               ]             Calculated Min. Ligament Thickness, tlig in.                                                    [C2]
[      ]
Area of IDTB Weld Anamoly, Aanamoly in2             [          ]                Section C.2.1 Area of IDTB Weld for Reinforcement,            [                                Calculated AIDTB in2
                                                                  ]
Note 1:   [                                                                     ]  The mean coefficient of thermal expansion at [              ] of the reinforcing metal of the IDTB weld ( [                ]
per Reference [C3]) is within of 15% of the mean coefficient of thermal expansion at 650 F of the head material. The ASME requirement is satisfied. Values are taken from the ASME code, Reference [C12].
Note 2: Reduction coefficient of [             ] for the IDTB weld area of reinforcement used in Table C3 is calculated as SmIDTB /Smvessel = [                             ] . Values are taken from the ASME code, Reference [C1].
Note 3: Nozzle 23 Over Bore conservatively uses the smaller geometry for the standard IDTB welds.
The following table shows the calculation of head reinforcement area used in MS Excel spread sheet Harris_Sizing_Tables.xlsx. Figure C1 shows used parameters.
Table C4: Actual Reinforcement Margin Parameter Opening Diameter, do, in.                   [                         ]
Reinforcement limit, Lr, in.                         [        ]
Outer RVCH surface radius, Ro, in.                  [          ]
Plane Distance of center of nozzle
                                                                      =   +
C, in.
Vertical Distance to outer tentative
                                                                      =
thickness, Ht, in.
Vertical Distance to outer RVCH
                                                                      =
surface, H, in.
Depth of reinforcement, tr, in.                      [        ]
Head reinforcement area, Ah, in.2             [       ] =2 (      2)
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
C.3.5     Calculation of area lost due to crack growth The entire area of Alloy 600 is considered removed due to presence of flaws for repaired nozzles. In addition, area lost due to postulated crack growth into the carbon steel is considered. Area removed of the Alloy 600 is taken from Reference [C5]. These drawings give as-built areas of the uphill and downhill J-groove welds for each nozzle of interest. Those numbers are tabulated below in Table C5.
Table C5: Alloy 600 weld area lost J-Groove Weld Area Uphill                  Downhill Min          Max        Min          Max Nozzle    Condition Condition Condition Condition In2          In2        In2          In2 5
14 17 18 23 23 OB 37 38 49 63 Area lost due to postulated crack growth is determined using a CAD feature of the Workbench program. The weld profiles of the uphill and downhill side taken from Reference [C5] are used and offset by the postulated crack growth. The area of the cracked carbon steel section is taken from the ANSYS Workbench program. The crack growth on the uphill side is [                ] for [ ] years of service and the downhill crack growth is [          ] inches for [ ] years of service taken from Section 6.3.1. Conservatively, crack growth per year is calculated as [              ] for the uphill side and [             ] for the downhill side. This growth is conservative for service that is less than 30 years since the crack propagates with slower rate at the beginning of the repair service.
In addition, the reinforcement area lost due to crack growth at the weld anomaly in the IDTB weld is also accounted for and reduced based upon a ratio of material strength.
Min and Max Conditions refer to minimum and maximum head thickness configurations.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
QA Note: The crack growth areas have been checked with approximate hand calculations to verify the Workbench computer program results, based on the weld profiles give in Ref. [C5].
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
C.3.6         Calculation of available area of reinforcement The total remaining reinforcement area is calculated by adding Ah (see Table C4), area of reinforcement available in the carbon steel head portion, to area of reinforcement due to portion of the IDTB weld (AIDTB - see Table C3) and subtracting areas lost due to nozzle bore (Armv - see Table C1), Alloy 600 J-groove weld area (see Table C5), and crack growth at the weld anomaly point. This is calculated in MS Excel spread sheet Harris_Sizing_Tables.xlsx without corrosion and without J-groove crack growth, initially to identify limiting nozzles (i.e. for screening purposes).
Table C6: Initial Calculation of Reinforcement Area Remaining Total Area of                Total Area Removed, in2   Total Remaining Reinforcement, in2                                     Reinforcement, in2 Nozzle 5 Minimum            (Special Case - See          (Special Case - See       (Special Case - See Section C.4)                 Section C.4)              Section C.4)
Nozzle 14 Minimum Nozzle 14 Maximum Nozzle 17 Minimum Nozzle 18 Minimum Nozzle 18 Maximum Nozzle 23 Minimum OB Nozzle 23 Minimum Nozzle 37 Minimum Nozzle 37 Maximum Nozzle 38 Minimum Nozzle 38 Maximum Nozzle 49 Minimum Nozzle 49 Maximum Nozzle 63 Minimum Based on Table C6, Nozzle 14 Minimum and Nozzle 37 Minimum are identified as potential limiting cases. Since neither of these nozzles have an adjacent nozzle in the repaired configuration, they will be analyzed using Approach 2.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Since Nozzle 17 Minimum and 18 Minimum are adjacent and each nozzle is in the repaired configuration, these nozzles are analyzed using Approach 1 considering corrosion and crack growth for [     ] years. The J-groove weld crack growth areas are documented in Figures C3 - C6.
Figure C3: Nozzle 17 Minimum Uphill J-groove Weld Crack Growth Area for 30 Years Page 101

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C4: Nozzle 17 Minimum Downhill J-groove Weld Crack Growth Area for 30 Years Page 102

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C5: Nozzle 18 Minimum Uphill J-groove Weld Crack Growth Area for 30 Years Page 103

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C6: Nozzle 18 Minimum Downhill J-groove Weld Crack Growth Area for 30 Years Page 104

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
The calculation for Nozzle 17 Minimum and 18 Minimum is documented in MS Excel spread sheet Harris_Sizing_Tables.xlsx and the results are represented below in Table C7 for [      ] years of operation.
Table C7: Nozzle 17 Minimum and 18 Minimum Results for 30 Years of Operation Total Area of               Total Area Removed, in2     Total Remaining Reinforcement, in2                                      Reinforcement, in2 Nozzle 17 Minimum Nozzle 18 Minimum As shown above in Table C7, the area of reinforcement exceeds the area removed for the limiting case (Nozzle 17 Minimum) and therefore since Nozzle 17 was repaired in May 2012, this nozzle is acceptable for an additional [        ] years beyond this date to May [          ].
C.4       Calculation of Remaining Years of Service using Approach 2 The purpose of this section is to remove some of the conservatisms presented in Section C.3 for the reinforcement calculation when a repaired nozzle is not adjacent to another repaired nozzle. Section C.3 looked at each nozzle individually without considering additional reinforcement that could be gained from neighboring nozzles. This approach is overly conservative when no neighboring nozzles have been repaired.
To remove some conservatism, a second approach was taken to calculate the available reinforcement area and area removed for a repaired nozzle neighboring an unrepaired nozzle. This approach will utilize an iterative process to determine when reinforcement area is exhausted. The limiting condition will occur on the uphill side of the repaired nozzle as a result of the significantly greater crack growth rate on the uphill J-groove weld side. Nozzle 14 Minimum was chosen as the limiting case based upon information from Table C6, and by comparing the growth in the J-Groove uphill weld between Nozzle 14 Minimum and Nozzle 37 Minimum. Since Nozzle 14 Minimum has a greater growth in the area of the uphill weld ( [        ] in2 - see Figure C8) as opposed to Nozzle 37 Minimum ( [           ] in2 - see Figure C10), Nozzle 14 Minimum is still the bounding location. For this analysis, Nozzle 14 Minimum is paired with its uphill neighbor Nozzle 7.
Nozzle 5 Minimum will also be evaluated since this nozzle has close proximity to the vent pipe.
The area removed was calculated by determining the area below the tentative thickness between each nozzles respective axis and the outside of the nozzle wall in the corroded condition. The J-groove weld area with crack propagation area (shown in Figure C8) was removed for the uphill weld at Nozzle 14 Minimum. In addition, the J-groove weld area was discounted for Nozzle 7 downhill based upon the material strength in comparison with the RVCH, as specified in NB-3330 [C1]. The downhill J-groove weld for Nozzle 7 was conservatively considered to be [            ] times larger than the value of the downhill J-groove weld for Nozzle 14 Minimum (Figure C9). This is conservative Page 105

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) because J-groove weld areas should increase as the nozzle moves further from the center and Nozzle 14 Minimum is further from center than Nozzle 7.
Figure C7: Overview of Approach 2 The length for the area of reinforcement was calculated by determining the distance between the two nozzles and subtracting the radius of each nozzle. This value was multiplied by the average thickness between the tentative thickness and the outer radius of the RVCH measured at each location. Since the as-built thickness was not available for Nozzle 7, the design minimum thickness was conservatively used ( [           ] in [C2]).
In addition to this reinforcement area, the IDTB weld on the uphill side was credited for reinforcement on Nozzle 14 Minimum. The IDTB weld was discounted for material strength and the weld anomaly, as described in Note 2 of Table C3.
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C8: Nozzle 14 Minimum Uphill J-groove Weld Crack Growth Area for 15 Years Page 107

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C9: Nozzle 14 Minimum Downhill J-groove Weld Crack Growth Area for 15 Years Page 108

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Figure C10: Nozzle 37 Minimum Uphill J-groove Weld Crack Growth Area for 15 Years Page 109

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
The available years of service are calculated using an iterative process utilizing Approach 2. Area lost due to crack growth into the carbon steel is calculated for each year of service. The maximum number of years is determined at the point when the available reinforcement area is exhausted.
The calculation for Nozzle 14 Minimum and Nozzle 7 is documented in MS Excel spread sheet Harris_Sizing_Tables.xlsx and the results are represented below in Table C8 for 15 years of operation.
Table C8: Nozzle 14 Minimum and Nozzle 7 Results for 15 Years of Operation Ligament between Nozzle 14 Min / Nozzle 7 Total Area of Reinforcement, in2 Total Area Removed, in2 Reinforcement Remaining, in2 A special case exists for Nozzle 5, and therefore the lifetime of Nozzle 5 will be verified separately below. Nozzle 5 does not border any repaired nozzles, but it lies within a closer proximity to an opening than the other cases as a result of the placement of the vent line. The Nozzle 5 Minimum case was modeled using Approach 2 in which the ligament between Nozzle 5 Minimum and the vent line was examined. The Nozzle 5 Uphill weld was used for this analysis, because the crack growth on the uphill weld produces a larger area which requires reinforcement. For conservatism, the minimum design thickness was used for the vent line and a [        ] in2 weld was conservatively used for the vent line J-groove weld. This J-groove weld area is conservative because it is larger than the J-groove weld areas on Nozzle 5 Minimum and the vent line does not require as large of a J-groove weld as the CRDM nozzles [C10]. In addition, corrosion was applied to the penetration diameter of the vent line to calculate area removed, despite the knowledge that this area would be protected by the vent line pipe. The calculation for Nozzle 5 Minimum and the vent line is documented in MS Excel spread sheet Harris_Sizing_Tables.xlsx and the results are represented below in Table C9 for 15 years of operation. This calculation uses the crack growth area for the uphill J-groove weld after 15 years for Nozzle 5 Minimum as shown in Figure C11.
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Figure C11: Nozzle 5 Minimum Uphill J-groove Weld Crack Growth Area for 15 Years Page 111

Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary)
Table C9: Nozzle 5 Minimum and Vent Pipe Results for 15 Years of Operation Ligament between Nozzle 5 Min / Vent Pipe Total Area of Reinforcement, in2               [           ]
Total Area Removed, in2                        [           ]
Reinforcement Remaining, in2                   [         ]
Based upon the results represented in Table C9, it can still be concluded that Nozzle 14 Minimum is the bounding case for 15 years of operation.
C.5  Results/Conclusion After analyzing all the critical nozzle locations, Nozzle 14 was identified as the limiting condition. Table C8 displays that Nozzle 14 is acceptable for 15 years of service from the date of the repair. Since this value is bounding for the other nozzles, this conclusion is applicable to all other cases. By this conclusion, and since the earliest repairs were performed in May 2012, the RVCH nozzles are acceptable for 12 years of additional operation, from April 2015.
C.6  Computer File(s)
Table C10: COLDStor - Official Computer Files
                       \cold\General-Access\32\32-9000000\32-9176350-002\
Date                Time              Size                       File Name 4/29/15           14:47:22(EST)      36172 Bytes            Harris_Sizing_Tables.xlsx This computer file inputs dimensions from References [C2], [C4], [C5], [C6], and [C10].
C.7  Additional Evaluation at Penetrations #30, #40 and #51 for 5 years operation During the recent outage inspection according to References [C14], [C15] and [C16],
additional nozzle repair is needed for nozzles 30, 40 and 51. However, no original J-groove weld dimensions nor RV head thickness at the three nozzle penetrations are available for a complete evaluation at the time this revision is prepared. The results presented in the Sections C.1 to C.6 for the nine repaired nozzles are then used as the basis to justify a 5-year operation for the three nozzle repairs.
RV head thickness at the nozzle:
As shown in previous sections, the head thickness is the most critical parameter in the evaluation. The following analysis is based on the assumption that the RV head wall thickness (t in Table C2) is no less than [         ] inches, i.e.,
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Controlled Document Document No. 32-9215680-002 Shearon Harris Unit 1 CRDM/CET Nozzle As-Left J-groove Weld Analysis (Non Proprietary) t[       ] in.
J-groove weld size:
Table C6 indicates that the total remaining reinforcement area for a particular nozzle of the minimum condition is always less than that of the maximum condition. Therefore the J- groove weld size of the minimum condition is considered herein. Furthermore, the geometric symmetry of the nozzle penetrations indicates that the J- groove weld size of Nozzle 37 may be assumed for Nozzle 40, and that of Nozzle 49 for Nozzle 51; J-groove weld size of Nozzle 37 may be assumed for Nozzle 30.
Crack growth area:
Since no detailed J-groove weld dimensions are available, crack growth areas at the three nozzle penetrations are estimated by the crack growth areas at Nozzles 14 and 37 (Figures C8 to C10). A review of Figures C8 to C10 indicates that closer the nozzle to the head center higher the crack growth area results (in contrast to that away from the center the J-groove weld size is larger). Therefore the crack growth area of Nozzle 14 for 15 years operation is taken as the bounding case for the three nozzles. A linear crack grown is assumed in the 15 years which is conservative, as the crack growth area in earlier years is less than that in later years. The crack growth area of 5 years is estimated as follows in Table C11:
Table C11: Estimate of Crack Growth area at Penetrations 30, 40 and 51 for 5 Years of Operation Crack growth area (in2)                      Area in in2        Eq.
Crack growth area of Nozzle 14 (15 years), upper hill Crack growth area of Nozzle 14 (15 years), down hill Total crack growth area of 15 years Crack growth area of 5 years Nozzle 30 is adjacent to Nozzle 38, and Nozzle 51 is adjacent to Nozzle 63. Approach 1 mentioned in Section C.2 is used. The calculation procedure is the same as in Section C.3.6 for Nozzles 17 and 18.
MS Excel spread sheet Harris_Sizing_Tables.xlsx from Rev. 002 is used in the calculation, and the results are presented in Table C12.
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Table C12: Results of Nozzle Repair at Penetrations 30, 40 and 51 for 5 Years of Operation Penetration area (in2)               30          40        51                  Eq.
Head reinforcement area IDTB weld reinforcement area Total area of reinforcement J-groove weld area before crack growth J-groove weld area after crack growth Area removed due to opening and corrosion Total area removed Total area remaining Computer File:
Updated MS Excel spread sheet of the same file name is uploaded to the COLDStor at
            \cold\General-Access\32\32-9000000\32-9176350-003\:
Table C13: COLDStor - Official Computer File of Rev. 003 Date               Time              Size                         File Name 10/17/2016       1:35 PM (CT)       43026 Bytes             Harris_Sizing_Tables.xlsx Page 114

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C.8      Appendix References References identified with an (*) are maintained within Duke Energy Records System and are not retrievable from AREVA Records Management. These are acceptable references per AREVA Administrative Procedure 0402-01, Attachment 8. See page 2 for Project Manager Approval of customer references C1  ASME Boiler and Pressure Vessel Code, Section III, Rules for Construction of Nuclear Facility Components, 2001 Edition with Addenda through 2003.
C2  AREVA Drawing 02-9175500E-007, Shearon Harris CRDM ID Temper Bead Weld Repair C3  AREVA Document 08-9172870-003, Design Specification for Shearon Harris RVCH CRDM and CET Nozzle Penetration Modification C4  AREVA Document 51-9176114-002, Corrosion Evaluation of Shearon Harris RV Head Penetration IDTB Weld Repair.
C5  AREVA Drawing 02-9239552B-001, Shearon Harris RVCH Repaired Penetration J-Groove Details C6  AREVA Document 32-9176345-002, Shearon Harris Unit 1 RVCH CRDM/CET Nozzle IDTB Repair Weld Anomaly C7  Reference Removed C8  Reference Removed C9  ANSYS/Workbench Finite Element Computer Code, Version 15.0, ANSYS Inc. Canonsburg, P.A.
C10 AREVA Document 38-2200979-000, Shearon Harris - Proprietary Document LTR-MRCDA-12-8 C11 AREVA Document 50-9176411-005, Shearon Harris CRDM Nozzle IDTB Weld Repair Traveler C12 ASME Boiler and Pressure Vessel Code, Section II, Rules for Construction of Nuclear Facility Components, 2001 Edition with Addenda through 2003.
C13 CR 2015-3494 C14 *Duke Energy NCR #02070424 C15 *Duke Energy NCR #02070179 C16 *Duke Energy NCR #02070259 Page 115}}