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Areva Calculation 32-9135800-001, DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of Idtb Repair, Enclosure C
	ML101400407
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Site:	Davis Besse
Issue date:	05/07/2010
From:	Noronha S, Wiger T, Xu H; AREVA NP
To:	; Office of Nuclear Reactor Regulation
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	L-10-143, TAC ME3703 32-9135800-001
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ENCLOSURE C DB-1 CRDM NOZZLE WELD ANOMALY FLAW EVALUATION OF IDTB REPAIR (NONPROPRIETARY VERSION)

AREVA CALCULATION 32-9135800-001 Forty-Four Pages Follow

uontrolled locument 0402-01-FOl (20697) (Rev. 014, 04/13/2009)'

A CALCULATION

SUMMARY

SHEET (CSS)

AR EVA Document No. 32 - 9135800 - 001 Safety Related: E Yes FI] No Title DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair PURPOSE AND

SUMMARY

OF RESULTS:

This document is a non-proprietary version of AREVA NP Document number 32-9134666-003. The AREVA NP proprietary information removed from 32-9134666-003 is indicated by a pair of braces "{ }".

The purpose of this analysis is to perform a fracture mechanics evaluation of a postulated anomaly in the Davis-Besse Unit 1 (DB-1) Control Rod Drive Mechanism (CRDM) nozzle IDtemper bead weld. For information, the qualification for IDTB alternate repair with Alloy 52M/82 is documented separately in 32-9136807.

This anomaly is assumed to be a 0.1 inch semi-circular flaw extending 360 degrees around the circumference at the "triple point" location where there is a confluence of three materials; the Alloy 600 nozzle, the Alloy 52M weld, and low alloy steel head. Two potential flaw propagation paths are considered in the flaw evaluations. The analysis includes prediction of fatigue crack growth in an air environment since the anomaly is located on the outside surface of the new weld, just below the bottom of the severed nozzle. Flaw acceptance is based on the 1995 through 1996 ASME Code Section Xl criteria for applied stress intensity factor (IWB-3612) and limit load (IWB-3642).

The purpose of Revision 001 is: (1) to change the indicator of AREVA NP proprietary information from square brackets ("[ ]") to braces ("{ }"), (2) to use fatigue crack growth laws of Alloy 52M for the analysis of crack growth in Alloy 52M, and (3) to perform the analysis based on the updated steady state condition operating temperature of { }0F.

The results of the analysis demonstrate that the 0.1 inch weld anomaly is acceptable for a 25 year evaluation life of the CRDM nozzle ID temper bead weld repair. However, note that the design life of the RVCH, as per the design specification is 4 years (Ref.2). Significant fracture toughness margins have been demonstrated for each of the two flaw propagation paths considered in the analysis. The minimum fracture toughness margin is 3.88, compared to the required margins of 4/10 for normal/upset conditions and /2 for emergency/faulted conditions per IWB-3612. Fatigue crack growth is minimal since the maximum final flaw size is { } inch. The margin on limit load is 10.44 for normal/upset conditions and 7.38 for emergency/faulted conditions, compared to the required margins of 3.0 and 1.5, respectively, per IWB-3642.

THE DOCUMENT CONTAINS ASSUMPTIONS THAT SHALL BE, THE FOLLOWING COMPUTER CODES HAVE BEEN USED INTHIS DOCUMENT: VERIFIED PRIOR TO USE CODENVERSIONIREV CODENERSIONIREV E YS YES ZINO AREVA NP Inc., an AREVA and Siemens company Paige1 0f,44

Controlled Document A 0402-01-FOI (20697). (Rev. 014, 04/13/2009)

AREVA AREVA NP Inc.,

Document No. 32-9135800-001 an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation Of IDTB Repair Review Method: ' Design Review (Detailed Check)

El Altemate Calculation Signature Block P/RIA Name and Title and Pages/Sections (printed or typed) Signature LP/LR Date Prepared/ReviewedlApproved S. J. Noronha All Pages Engineer'N ~ cV Heqin Xu LR All (Detailed check)

Engineer IV U(T-lV T. M. Wiger A './- All Pages Manager __._

Note: P/R/A designates Preparer (P), Reviewer (R), Approver (A);

LP/LR designates Lead Preparer (LP), Lead Reviewer (LR)

Project Manager Approval of Customer References (NIA if not applicable)

Name Title (printed ortyped) (printed or typed) Signature Date N/A Mentoring Information (not required per 0402-01)

Name Title Mentor to:

(printed or typed) (printed or typed) (PIR) Signature Datel N/A Page 2

Controlled Document A 0402-01-FO1 (20697) (Rev. 014, 04/13/2009)

AREVA AREVA NP Inc.,

Document No. 32-9135800-001 an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Record of Revision Revision Pages!Sectionsi No. Date Paragraphs Changed Brief Description I Change Authorization 000 04/2010 ALL Original 001 05/2010 ALL Changed indicator for proprietary information from

_ square brackets ("[ ]") to braces ("{ }").

CSS, Page 1 Added purpose of this revision Section 2.2 Added fatigue crack growth laws of Alloy 600 and Alloy 52/82.

Section 3.0 Added another minor assumption related to updated temperature Section 4.0 Updated the steady state operating temperature to

{ }°F Section 4.1 Updated the code minimum yield strength values based on the operating temperature { } 'F Section 4.3.2 Updated the fracture toughness estimation Section 5.0 Revised calculations based on the updated operating head temperature.

Section 6.0 Updated the results Section 7.0 Updated the Reference list Appendix B Removed

4. + .1.

+ 4. .1.

+ 4 4 4 4 4

I. + +

4. .5. .5.

Page 3

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company:

DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table of Contents Page SIGNATURE BLOCK ............................................. ............................................................................... 2 RECORD OF REVISION ........................................................................ 3....................

3 LIST OF TABLES .................................................................................................................................. 6 LIST OF FIGURES ......................................... ............................................................................... ..... 7

1.0 INTRODUCTION

...... I..................................... ..................................... .8&

1.1 CRDM Nozzle IDTB.W eld Repair ................................................................................................ 8 1.2 Potential W eld Anomaly ............................................................................................................ 8 1.3 Postulated Flaws ................................................................. !............................................................ 10.

2.0 ANALYTICAL METHODOLOGY ............................................................................................ 11 2.1 SIF Solutions ................................................................................................................................... 11 2.2 Fatigue Crack Growth ..................................................................................................................... 13 2.3 Acceptance Criteria ............................ .............................................................. 1.....................

14 3.0 ASSUMPTIONS ..................................................... ............ ......................... 15 4.0 DESIGN INPUTS ................................. a................................................................................... 15 4.1 Code Minimum Yield Strength ................................................................................................. 15 4.2 Applied Stresses ............................................................................................................................. 16 4.2.1 Fatigue Stresses .......................................................................................................... 16 4.2.2 Residual Stresses ........................................................................................................ 19 4.3 Fracture Toughness ........................................................................................................................ 24 4.3.1 Low Alloy Steel RV Head Material .............................................................................. 24 4.3.2 Alloy 600 and Alloy 690 Materials ............................................................................... 24 5.0 CALCULATIONS ...................................................................................................................... 25 6.0 RESULTS ................................................................................................................................. 40 6.1 Propagation of a Continuous External Circumferential Flaw along Path 1 ................................ 40 6.2 Fatigue Crack Growth of a Semi-Circular External Axial Flaw along Path 1 ............................. 40 6.3 Fatigue Crack Growth of a Continuous Cylindrical Flaw along Path 2 ...................................... 40

7.0 REFERENCES

...................... ................................................................... 42 Page-4

Controlled Document A Document No. 32-9135800-001 AR EVA ARmVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table of Contents (continued)

Page APPENDIX A: COMPARISION OF-DB-1 AND ANO-1 REACTOR VESSEL CLOSURE HEADS .................... 43 Page 5

Luontrollea uocument A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair List of Tables Page Table 4-1: Stresses for Flaw Evaluations along Path 1 (Ref.16) ...................................................... 17 Table 4-2: Stresses for Flaw Evaluations along Path 2 (Ref.16) ...................................................... 18 Table 4-3: Residual Stresses in Repair Weld after Chamfering* J-Weld ..................... 22 Table 4-4: Residual Stresses in Repair weld after Chamfering* J-weld (Cont'd) ........................ ......... 23 Table 5-1: Evaluation of Continuous External Circumferential Flaw for Fatigue Crack Growth along P a th 1 ............................................................................................................................................ 25 Table 5-2: Limit Load Analysis for a Continuous External Circumferential Flaw .............................. 29 Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path 1 ...................... 29 Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 ..................................................................................................................................................... 35 Table A-i: Comparison of Critical Dimensions of DB-1 and ANO-1 .............................................. 43 Table A-2: Comparison of IDTB Materials of DB-1 and ANO-1 ................................................... 43 Page 6

uontrolled Locument A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair List of Figures Page Figure 1-1: W eld Anomaly in Temper Bead W eld Repair ................................................................. 9 Figure, 1-2: Illustration of Crack Propagation Paths on the Finite Element Stress Model ................. 11 Figure 4-1: FEA Model for Center CRDM Nozzle with Weld. Repair ............................................ 20 Figure 4-2: FEA Model for Center CRDM Nozzle after Weld Repair and Chamfer*................ ,.......... 21 Page.7

uontrolled Locument A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair

1.0 INTRODUCTION

The purpose of this analysis is to perform a fracture mechanics evaluation of a postulated anomaly in the Davis-Besse Unit 1 (DB-1) Control Rod Drive Mechanism (CRDM) nozzle ID temper bead weld. This anomaly is assumed to be a 0.1 inch semi-circular flaw extending 360 degrees around the circumference at the "triple point" location where there is a confluence of three materials; the Alloy 600 nozzle, the Alloy 52M weld, and low alloy steel head. Two potential flaw propagation paths are considered in the flaw evaluations.

1.1 CRDM Nozzle IDTB Weld Repair The CRDM nozzle ID temper bead (IDTB) weld repair is described by the design drawing (Ref.1). This weld repair establishes a new pressure boundary above the original J-groove weld. The five steps involved in the repair design are listed below.

1) Roll Expansion

2) Nozzle Removal and Weld Prep Machining

3) Welding

4) Grinding/Machining and NDE

5) Original Weld Grinding During the welding process (step 3), a maximum 0.1 inch weld anomaly may be formed due to lack of fusionat the "triple point", as shown in Figure 1-1. The anomaly is conservatively assumed to be a "crack-like" defect 3600 around the circumference at the "triple point" location. The technical requirements document (Ref.2) provides additional' details of the ID temper bead weld repair procedure. The purpose of the present fracture mechanics analysis is to provide justification, in accordance with Section XI of the ASME Code (Ref.3), for operating with the postulated weld anomaly at the triple point. Predictions of fatigue crack growth are based on an evaluation life of 25 years.

1.2 Potential Weld Anomaly The anomaly could be located in the triple point region as shown in Figure 1-1. The region is called a "triple point" since three materials intersect at this location. The materials are:

a) the Alloy 600 CRDM nozzle material, b) the new ERNiCrFe-7A filler weld material,* and c) the low alloy steel RV head material.

Per Ref. 4, Specification 5.14, Par. A7.4.3, "Filler metal of this classification is used for~welding nickel-chromium-iron alloy (ASTM B163, B166, B167, and B168 having UNS Number N06690)." This UNS number is associatedwith Alloy 690material.

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uontrolled uocument

'A nAREVAn e Document No. 32-9135800-001 AREVA NP Inc.,

an ARE VAand Siemnens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 1MAX TRIPLE POINT

.1 20° MIN

(.10 MAX POSSIBLE LACK OF FUSION ANOMALY)

AS-WELDED SURFACE SHALL BE SUITABLE FOR PT Figure 1-1: Weld Anomaly in Temper Bead Weld Repair Page 9

Gontrolled L)ocument A Document No. 32-9135800-001 ARE VA AREVA NP Inc.,

an AREVA and Siemens company.

DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 1.3 Postulated Flaws The triple point weld anomaly is assumed to be semi-circular in shape with an initial radius of 0.10", as indicated in Figure 1-1. It is further assumed that the anomaly extends 3600 around the nozzle. Three flaws are postulated to simulate various orientations and propagation directions for the anomaly. A circumferential flaw and an axial flaw on the outside surface of the nozzle would both propagate in a horizontal direction toward the inside surface.

A cylindrically oriented flaw along the interface between the weld and head would propagate downward between the two components. The horizontal and vertical flaw propagation directions are represented in Figure 1-2 by separate paths for the downhill and uphill sides of the nozzle, as discussed below. For both these directions, fatigue crack growth will be calculated considering the most susceptible material for flaw propagation.

Horizontal Direction (Path 1):

F!aw propagation is across the CRDM tube wall thickness from the OD of the tube to the IDof the tube.

This is the shortest path through the component wall, passing through the new Alloy 690 weld material, However, Alloy 600 tube material properties or equivalent are used for axial flaw evaluations to rensuire:

that another potential path'through the HAZ between the new repair weld and the Alloy 600 tube material is bounded.

For completeness, two types of flaws are postulated at the outside surface of the tube. A 3600 continuous circumferential flaw, lying in a horizontal plane, is considered to be a conservative representation of crack-like defects that may exist in the weld anomaly. This flaw would be subjected to axial stresses in the tube. An axially oriented semi-circular outside surface flaw is also considered since it would lie in a plane that is normal to the higher circumferential stresses. Both of these flaws would propagate toward the inside surface of the tube.

Vertical Direction (Path 2):

Flaw propagation is down the outside surface of the repair weld- between the weld and RV head. A continuous surface flaw is postulated to lie along this cylindrical interface between the two materials. This flaw, driven by radial stresses, may propagate along either the new Alloy 690 weld material or the low alloy steel head material.

Page. 10

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc..

an AREVA and 8Ienans ompay DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Path I Downhill Location L Path 2 Downhill Location Figure 1-2: Illustration of Crack Propagation Paths on the Finite Element Stress Model 2.0 ANALYTICAL METHODOLOGY This section presents several aspects of linear elastic fracture mechanics (LEFM) and limit load analysis (to address the ductile Alloy 600 and Alloy 690 materials) that form the basis of the present flaw evaluations. As discussed in Section 1.3, flaw evaluations are performed for flaw propagation Paths I and 2 in Figure 1-2.

2.1 SIF Solutions Path 1 represents a section across the new Alloy 52M weld metal which is equivalent to the thickness of the CRDM tube wall. Since the weld anomaly is located at the base of the OD of the CRDM tube and is assumed to be all the way around the circumference, a stress intensity factor (SIF) solution for a 3600 circumferential crack on the OD of a circular tube is deemed appropriate. Therefore, the SIF solution of Buchalet and Bamford (Ref.5) is used in the analysis. However, this solution is applicable to a 3600 part-through ID flaw. To develop an SIF solution for a 3600 part-through OD flaw, an F function is determined based on SIF solutions of Kumar (Ref.6 and Ref.7). Appropriate F functions for internal and external circumferential flaws are determined for a cylinder subjected to remote tension. The ratio of the F functions for the external and internal flaws is considered to be an appropriate multiplying factor for the Buchalet and Bamford SIF solution to extend its application to an external flaw. Similar ratios have been reported by Kumar (Ref.8). The material to be considered for this path is the Alloy 52M weld metal. Fatigue crack growth is calculated using crack growth rates for Alloy 52M from Reference 12. A limit load analysis for an external circumferential flaw in a cylinder subjected to remote tension (Ref.7) is also performed for applied loads on the CRDM tube.

Page 11

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair An axially oriented semi-circular OD surface flaw is also considered in the evaluation, as illustrated by the schematic below. F iFlaw Propagation Path Componqent W/all t

where, a = initial flaw depth =0.100 inch I =2c = flaw length = 0.200 inch t = wall thickness ={ } inch An axial flaw is considered since the stresses in the CRDM penetration region are primarily due to pressure and therefore the hoop stresses are more significant. The SIF solution by Raju & Newman (Ref.9) for an external surface crack in a cylindrical vessel is used in the evaluation, considering growth in both the radial and axial directions. The materials to be considered for axial flaws are the Alloy 600 for CRDM tube and Alloy 52M for IDTB repair. The fatigue flaw growth rates in an air environment for Alloy 600 and Ni-alloy welds are obtained from NUREG/CR-6721 (Ref. 11) and NUREG/CR-6921 (Ref.12), respectively.

The Irwin plasticity correction is also considered in the SIF solutions discussed above. This plastic zone correction is discussed in detail in Section 2.8.1 of (Ref.10). The effective crack length is defined as the sum of the actual crack size and the plastic zone correction:

a, =a+i, where ry for plane strain conditions (applicable for this analysis) is given by:

' )2 ry =.-(

Path 2 represents the interface between the new repair weld and the RV head material. The potential for flaw propagation along this interface is likely if radial stresses are significant between the weld. and head, This assessment utilizes an SIF solution for a continuous surface crack in a flat plate from Appendix A of the 1995 Edition of Section XI (Ref.3). Flat plate solutions are routinely used to evaluate flaws in cylindrical components, such as the repair weld since the added constraint provided by the cylindrical structure reduces the crack opening displacements. The solution is therefore inherently conservative for this application. Crack growth analysis is performed considering propagation through the Alloy 52M weld metal or the low alloy steel head material, whichever is limiting.

Page 12

(ontrolled Vocument A

AR EVA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 2.2 Fatigue Crack Growth SA-533 Grade B Class 1 Low Alloy Steel Plate Material (RV Head)

From Article A-4300 of the 1995 Edition with 1996 Addendum of Section Xl (Ref.3), flaw growth due to fatigue is characterized by da where C, and n are constants, that depend on the material and environmental conditions, AKI is the range of applied stress intensity factor in terms of ksi*/in, and da/dN is the incremental flaw growth in terms of inches/cycle.

For the embedded weld anomaly considered in the present analysis, it is appropriate to use crack growth rates for an air environment. Fatigue crack growth is also dependent on the ratio of the minimum to the maximum stress intensity factor; i.e.,

R = (K 1 )min I(Kj )max The fatigue crack growth constants for subsurface flaws in an air environment are:

n = 3.07 C. = 1.99 x 10"10 S where S = 25.72 ( 2.88 - R )-3.0 7 for 0 < R< 1 Alloy 600 for CRDM Tube Fatigue crack growth rates for Alloy 600 are used to predict flaw growth in the CRDM tube. From NUREG/CR-6721, Section 3.1 [11], flaw growth due to fatigue is characterized by d6,f = ,(K)n where C. and n are constants that depend on the material and environmental conditions, AKI is the range of applied stress intensity factor in terms of MPa/m, and da/dN is the incremental flaw growth in terms of m/cycle.

For the embedded weld anomaly considered in the present analysis, it is appropriate to use crack growth rates for an air environment. Fatigue crack growth is also dependent on the ratio of the minimum to the maximum stress intensity factor, i.e.,

R = (K )min I(K, )max The fatigue crack growth constants for flaws in an air environment are:

Page i3

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair n= 4.1 CO = CA600 X SR where CA600 = 4.835x0"14 +1.622x1 016 T-1.490x1 01 T 2+4.355 x1021T 3 T = Temperature, 'C 22 SR = (1-0.82R)- .

Alloy 52M/82 Weld Metal for IDTB Alternate Repair Fatigue crack growth rates for Ni-alloy welds including Alloy 82 and Alloy 52 are used to conservatively predict flaw growth in the new Alloy 52M repair weld. From NUREG/CR-6921, Section 5.2 [12], flaw growth due to fatigue is characterized by C-0 da =C(AK, )nl where C, and n are constants that depend on the material and environmental conditions, AKI is the range of applied stress intensity factor in terms of MPa*/m, and da/dN is the incremental flaw growth in terms of m/cycle.

For the embedded weld anomaly considered in the present analysis, it is appropriate to use crack growth rates for an air environment. Fatigue crack growth is also dependent on the ratio of the minimum to the maximum stress intensity factor; i.e.,

R =.(Kj)rnin I(KI )..x The fatigue crack growth"constants for flaws in an air environment are:

n= 4.1 Co = CNi-weld X SR where 17 8 2 20 3 2 CNi-weld = 8.659x1 O-4-5.272x1 0* T+2.129x1 0" T 1.965x1 0 T +6.038x1 0 3T4 T= Temperature, 0C SR = (1-0.82R)-'"2 2.3 Acceptance Criteria The low alloy steel reactor vessel head material will be evaluated against the IWB-3612 acceptance criteria of Section Xl (Ref.3). For the highly ductile materials Alloy 600 and Alloy 690 materials, the initial flaw depth to thickness ratio for the postulated weld anomaly is only about 20% and fatigue crack growth is minimal for these materials in an air environment. A convenient acceptance criterion on flaw size is the industry developed 75% through-wall limit on depth (Ref.13):

a

-*0.75 t

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Uontrolled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair For the shallow cracks considered in the present analysis, this criterion is easily met. In addition, stress intensity factors will be calculated and evaluated against conservative fracture toughness requirements using a factor of safety of 410 for normal and upset conditions.

Another acceptance criterion for ductile materials is demonstration of sufficient limit load margin. From IWB-3642 (Ref.3), the required safety margin, based on load, is a factor of 3 for normal and upset conditions and a factor of 1.5 for emergency and faulted conditions.

Since stresses for emergency/faulted conditions are bounded by the controlling normal/upset condition stresses (see Section 4.2). and the required fracture toughness margins are less stringent for emergency/faulted conditions, satisfying normal/upset conditions requirements implicitly satisfies thosefor emergency/faulted conditions as well.

3.0 ASSUMPTIONS This analysis contains no major assumptions that must be verified prior to use on safety-related work. Listed below are minor assumptions that are pertinent to the present fracture mechanics evaluation.

1) The anomaly is assumed to include a "crack-like" defect, located at the triple-point location and extending all the way around the circumference. For analytical purposes, a continuous circumferential flaw is located in the horizontal plane at the top of the weld. Another continuous flaw is located in the cylindrical plane between the weld and reactor vessel (RV) head.

2) In the radial plane, the anomaly is assumed to include a quarter-circular "crack-like" defect (see Figure 1-1). For analytical purposes, a semi-circular flaw is used to represent the radial cross-section of the anomaly.

3) An RTNDT value of 60OF is conservatively assumed for the SA-533 Grade B Class 1 low alloy reactor vessel head material. This is based on a highest measured value of 40°F for 13 heats of SA-533 Grade B plate material (Ref.14).

4) The current operating head temperature is { } OF. The reactor trip starting temperature (or steady state condition temperature) at transient time 10.000 hours0 days 0 hours 0 weeks 0 months used in the transient analysis is { } 'F (Ref. 16).

The difference between the current higher head temperature and the analyzed temperature is only { }

'F. The effect of this difference in steady state head temperature will be negligible on the transient stresses considered in this analysis.

4.0 DESIGN INPUTS The region of interest for the present flaw evaluations is at the triple point, where three different materials intersect. These materials are the CRDM nozzle material, the new weld material and the reactor vessel head material.

The DB Unit 1 CRDM nozzles are made from Alloy 600 material to ASME specification SB-167 for tubular products (Ref.2)., The new weld, as noted in Section 1.2, is made from Alloy 690 type (Alloy 52M) material. The portion of the reactor vessel head that contains the CRDM nozzles is fabricated from SA-533 Grade B Class 1 (Ref.2). The normal operating temperature is { } OF (Ref.15).

4.1 Code Minimum Yield Strength The code minimum yield strength, Sy, values for SB-167 Material N06600 (Alloy 600 Material) as per the 1989 edition of the ASME Code (Ref.20) is 35.0 ksi at room temperature and 27.7 ksi at operating temperature of { }

OF.

For the SA-533 Grade B Class 1 Low Alloy Steel Material (RV Head), the room temperature yield strength is 50.0 ksi and at operating temperature ({ } OF) the yield strength is 43.7 ksi (Ref.20).

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uontroieci Uocument A

AREVA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair For the Alloy 52M new weld material, the material properties are obtained from Code Case N-474-2 as per (Ref.2). The yield strength for Alloy 52M material at operating temperature of { } OF is 27.6 ksi.

The code minimum yield strength is used for limit load analysis. The yield strength values used for plastic zone correction of the stress intensity factor as discussed in section 5.0 are the same as the ones used for residual stress calculation.

4.2 Applied Stresses The applied stresses are the6yclic stresses that contribute to fatigue crack growth. Incremental crack growth is based on six design heatup/cooldown 'cycles per year of operation. Residual stresses are also developed in the repair weld from the ID temper bead welding process that forms the new pressure boundary.

4.2.1 Fatigue Stresses Fatigue stresses are obtained from the generic stress analysis for the B&W 177 FA plants contained in Reference16. The maximum stresses, which occur during cooldown (at 10.004 hours4.62963e-5 days 0.00111 hours 6.613757e-6 weeks 1.522e-6 months into the composite heatup/cooldown transient), are combined with a zero stress at shutdown to produce a maximum cyclic load since stresses remain positive during this transient due to the dominating effect of pressure. The reactor coolant pressure at the 10.004 hour4.62963e-5 days 0.00111 hours 6.613757e-6 weeks 1.522e-6 months time point is { } psig (Ref.16). A slightly higher pressure ({ } psia) occurs during a rod withdrawal accident, which is classified as an upset condition in the reactor coolant system functional specification (Ref.17). Stresses for the rod withdrawal transient will be obtained by multiplying the stresses at 10.004 hours4.62963e-5 days 0.00111 hours 6.613757e-6 weeks 1.522e-6 months into the composite heatup/cooldown transient by the ratio of the pressures for the two transients.

Component stresses are obtained for the two crack propagation paths outlined on the finite element model in (Ref.16). Stresses for Paths 1 and 2 are obtained from (Ref.16). Stresses are reported in a cylindrical coordinate system relative to the CRDM nozzle and include the three component stresses (axial, hoop and radial) needed to calculate mode I stress, intensity factors for the various postulated flaws. These stresses, provided at four uniform increments along each path, were derived for ligament thicknesses of 0.488" for Path 1 and 1.143 inches for Path 2.

The stresses in Reference 16 apply directly to a weld thickness of 0.488". After grinding the inside surface of the weld, the thickness of the weld relative to the outside surface of the nozzle is { }

(Ref.1). The length of the actual weld is 1.35 inches (Ref.1). Since the actual weld thickness and length are greater than the analyzed thickness, no adjustment will be made to the Reference 16 stresses in the present flaw evaluations.

To ensure that the bounding stresses are captured for use in the present flaw evaluations, stresses are obtained at every 45 degrees from the downhill (00) to the uphill (1800) locations, as shown by the figure in Appendix D of Reference 16. It is concluded in that reference that the most limiting path is at the 1800 uphill location. The uphill stresses are presented in Tables 4-1 and 4-2 for Paths I and 2, respectively.

As noted in the conclusions of Appendix F of Reference 16, stresses due to emergency/faulted conditions are bounded by the controlling normal/upset condition stresses. Therefore, the emergency/faulted condition stresses are bounded by the normal/upset condition stresses, considered above, for the fatigue crack growth analysis.

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A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 4-1: Stresses for Flaw Evaluations along Path I (Ref.1 6)

Composite HeatuplCooldown Transient (Normal Operating Conditions)

Path: WA180 Length = 0.488 Triple Point Location: 0.000 0.000 0.000 0.122 0.122 0.122 0.244 0.244 0.244 0.366 0.366 0.366 0.488 0.488 0.488 Pressure Time --SX-- -SY-- -SZ-- -SX- --SY-- -SZ- -SX-- -SY- -SZ- -SX-- -SY-- -SZ- -SX-- --SY-- -SZ-(psig) I (hr.) - Radial Hoop Axial Radial Hoop Axial Radial Hoop Axial Radial Hoop Axial I Radial Hoop Axial C, 0.001 0 4.770 4.871 7.000 0 7.313 7.412 1A(AflR(

10000_A.

Q

{ } 10n~ r-34 1000 1- .

10.013 10.117 0 10.217 10.250 C) 10.718 12.939 CD Ratioed Stresses for Rod Withdrawl Accident (Upset Condition)

Note: Rod Withdrawal Accident Stress = { )

Heatup/Cooldown Stress Triple Point

. Location: 0.000 0.000 0.000 0.122 0.122 0.122 0.244 0.244 0.244 0.366 0.366 0.366 0.488 0.488 0.488/

Pressure -SX-- -SY-- -SZ-- --SX-- --SY-- -. SZ-- --SX-- -SY- --SZ- --SX-- --SY-- --SZ--. --SX-- --SY-- -SZ-(psig) Radial Hoop Axial Radial Hoop Axial Radial Hoop Axial Radial Hoop Axial Radial Hoop Axial

{C } {;

Legend: SX = radial stress SY = hoop stress SZ = axial stress Page 17

A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 4-2: Stresses for Flaw Evaluations along Path 2 (Ref.16)

Composite HeatuplCooldown Transient (Normal Operating Conditions)

Path: WV180 Length= 1.143 Triple Point Location: 0.0000 0.0000 0.0000 0.2858 0.2858 0.2858 0.5715 0.5715 0.5715 0.8573 0.8573 0.8573 1.1430 1.1430 1.1430 Pressure Time -SY-- --SX-- --SY-- --SZ-- -SX-- -SY- -SZ- --SX-- -SY-- -SZ-- --SX-- -SY- -SZ--

--SX-- --SZ--

In i I fjhr I-l~nn Hnnn AxiAl Hood AiAA Radial Hnoo Axial thr I Radial Hoo Axial Radial Hoo Axial Radial 0.001 4.770 4.871 7.000 7.313 7.412 1n ann 10000

{ } 1(n Nn.4 10004 1 10.013 10.117 10.217 10.250 10.718 12.939 Ratioed Stresses for Rod Withdrawl Accident (Upset Condition)

Note: Rod Withdrawal Accident Stress = { }* Heatup/Cooldown Stress Triple Point I Location: 0.000 0.000 0.000 0.122 0.122 0.122 0.244 0.244 0.244 0.366 0.366 0.366 0.488 0.488 0.488 Pressure --SX- -SY-- --SZ-- -SX-- -SY-- -SZ-- -SX- H-SY-- --SZ- --SX- -SY-- -SZ-- --SX-- -SY-- -SZA-Insia I Radial HooD Axial Radial HooD Axial Radial HooD Axial Radial Hoop Axial Radial Hoop Axial Legend: SX = radial stress SY = hoop stress SZ = axial stress Page 18

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA end Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 4.2.2 Residual Stresses A three-dimensional elastic-plastic finite element analysis (see Ref.18) was performed to simulate the sequence of steps involved in arriving at the configuration of the CRDM nozzle and reactor vessel head after completion of the IDtemper bead repair. A comparison of the geometry and materials of reactor vessel closure heads of ANO-1 and DB-1 is presented in Appendix A of this document to justify the use of the weld residual stresses from the analysis of Reference 18. To simplify the analysis of the complete repair process, only the center nozzle was modeled (Figure 4-1). Although this axisymmetric analysis was based on the geometry of the center nozzle penetration, adjustments were made to represent significant aspects of the controlling nozzle at the outermost hillside location ({ }O from the top of the vessel). In particular, the repair weld was positioned at the minimum distance above the J-groove and the J-groove weld was chamfered to simulate the largest chamfer (7/8"). The model also used the highest yield strength of any nozzle in the head ({ }). The { }o nozzle location was limiting for all three of these conditions.

The FE analysis simulated the laying of the original weld butter' and the subsequent post-weld stress relief, the heatup of the original J-groove weld and adjacent material during the welding process and the subsequent cooldown to ambient temperature, a pre-service hydro test, and operation at steady state conditions, After the steady state loads were removed and the structure was again at ambient conditions, the portion of the nozzle below the cut line (Ref.1) was deleted. Deposition of the repair weld was simulated using four weld passes, and the J-groove weld was chamfered as shown in Figure 4-2. The analysis of this final configuration provided residual stresses in the repair weld for use in the present flaw evaluations. These stresses are listed in Table 4-3

&Table 4-4.

The repair weld analysis in Ref.18 used a multi-linear isotropic hardening model to characterize the nozzle material and elastic-perfectly plastic material models for the welds, butter, cladding and head. The yield strengths for the non-strain hardening models were selected to represent the flow stress of the various materials. The following yield strength values were used in the repair weld FE analysis:

Component Material Yield Strength at 600 OF Nozzle Alloy 600 { } ksi Repair weld Alloy 52M { } ksi J-groove weld Alloy 182 { }ksi Butter Alloy 182 { } ksi Head Low alloy steel { } ksi Cladding Stainless steel { } ksi

Note, the operating temperature of the plant is { } OF. However the effect of this small difference in the temperature should be minimal.

In this evaluation for Davis-Besse, chamfering is not applicable. However, the effect of chamfering of J-groove weld on IDTB weld will be minimal since J-Groove weld chamfering range is away from the triple point. In addition, comparing with transient stresses that determine the AK,, the sustained residual stresses are usually not a major contributor to fatigue crack growth since they do not contribute to AK,, but only to the ratio of the minimum to the maximum stress intensity factor. Therefore, the residual stresses used in Reference 18 are considered a reasonable approximation for this flaw evaluation.

Page 19

Controlled Document A Document No. 32-9135800-001 AREVA AREVA NP inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Nozile Cut Line 2601/

Nozzle Repair _

Weld Region 2001, Pass 4/

Pass I/

Nozzle Elements Removed During Repair Weld Prep Node Numbers Increase by 100 tip the length of [he tube and shell

/ 9 Node Numbers Increase by I along the tube and shel I radius Nodes 609 through 1409 are coincident with 610 through 1410 Figure 4-1: FEA Model for Center CRDM Nozzle with Weld Repair Page 20

Controlled Document A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Nozzle Repair Weld Region 450 Region Removed for Weld Clnamfer Figure 4-2: FEA Model for Center CRDM Nozzle after Weld Repair and Chamfer*

Chamfering not applicable for this analysis Page 21

Controlled Document A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 4-3: Residual Stresses in Repair Weld after Chamfering* J-Weld Residual Stresses in Repair Weld after Chamfering J-Weld Penetration angle = 0 degrees Nozzle yield strength = { }

Time: 16001 Path Along Interface Between Repair Weld and Remaining Nozzle (Corresponds to Path 1)

Radial Hoop Axial Coordinates Location Node Stress Stress Stress X Z (psi) (psi) (psi) (in.) (in.)

Triple Point 2609 2608 2607 2606 2605 2604 2603 2602 Inside Surface 2601

Chamfering not applicable for this analysis Page 22

Controlled Document A Document No. 32-9135800-001 AR EVA.

AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle'Weld Anomaly Flaw Evaluation of IDTB Repair Table 4-4: Residual Stresses in Repair weld after Chamfering* J-weld (Cont'd)

Residual Stresses in Repair Weld after Chamfering J-Weld Penetration angle = 0 degrees Nozzle yield strength = { }

Time: 16001 Path Along Interface Between Repair Weld and Reactor Vessel Head (Corresponds to Path 2)

Stresses in Weld Radial Hoop Axial Coordinates Relative Location Node Stress Stress Stress X Z Position (Dsi) (osi) (in.) (in.) (in.)

Triple Point 2609 (psi) 2509 2409 2309 2209 2109 Lower End 2009 Stresses in Head Radial Hoop Axial Coordinates Relative Location Node Stress Stress Stress X Z Position (psi) (psi) (psi) (in.) (in.) (in.)

Triple Point 2610 2510 2410 2310 2210 2110 Lower End 2010

Chamfering not applicable for this analysis Page 23

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 4.3 Fracture Toughness 4.3.1 Low Alloy Steel RV Head Material Fracture toughness curves for SA-533 Grade B Class 1 material are illustrated in Figure A-4200-1 of Reference (Ref.3). At an operating temperature of about { O

°F, the Kia and K1c fracture toughness values for this material (using an assumed RTNOT of 60'F) are above 200 ksi4in. An upper bound value of 200 ksi'/in will be conservatively used for the present flaw evaluations.

4.3.2 Alloy 600 and Alloy 690 Materials In Table 7 of Reference19, Mills provides fracture toughness data for Unirradiated Alloy 600 material at 24 0 C (75 OF) and 427 °C (800 OF) in the form of crack initiation values for the J-integral, J.. Using linear interpolation and the LEFM plane strain relationship between Jc and fracture toughness, Kjc,

_ JE 2 Kjc =1-v the fracture toughness at an operating temperature of { }OF is derived as follows:

Note. v 0.3

! kN/m = 1 kN/m + 4.448 N/Ilb x 0.0254 mr/in = 0.00571 kip/in Mills Code (Ref.19) (Ref.20)

Temp. Jc Jc E Kjc (F) (kN/m) (kip/in) (ksi) (ksi*/in) 75 382 2.18 31000 273

{8 {5 {3 {2 {3 800 575 3.28 27600 316 Since brittle fracture is not a credible failure mechanism for ductile materials like Alloy 600 or Alloy 690, these fracture toughness measures, provided for information only, are not considered in the present flaw evaluations.

However, it should be noted that the fracture toughness measures of these ductile materials is significantly greater than the fracture toughness measure of the low alloy RV head material reported in Section 4.3.1. The failure mechanism for the ductile Alloy 600 and 690 materials is limit load.

Page 24

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 5.0 CALCULATIONS The evaluation of the postulated external circumferential flaw for propagation along Path 1 is contained in Tables 5-1 and 5-2. The fatigue crack growth analysis is provided in Table 5-1 and a limit load analysis is presented in Table 5-2.

The evaluation of an external axial flaw for fatigue crack growth along Path 1 is contained in Table 5-3.

A continuous surface flaw along the cylindrical interface between the repair weld and the reactor vessel head is analyzed for fatigue-crack growth along Path 2 in Table 5-4.

Theflaw evaluations utilize the upset set condition stresses shown in Tables 4-1 and 4-2, which are obtained from heatup/cooldown transient stresses by multiplying the stresses by 1.05 {( )}, the ratio of maximum upset condition stresses to heatup/cooldown transient stresses. The stresses used for fatigue crack growth are resulting from the sum of the residual stresses and the transient stresses. This is a conservative approximation of the actual state of stress since the elastic transient stresses are added directly to the elastic-plastic residual stresses, with no attenuation for additional plastic strain. It is therefore appropriate to use the yield strengths from the repair weld residual stress analysis when applying the Irwin plastic zone correction for crack length.

As required by Article IWB-3612, Reference 3, a safety factor of 410 is used to evaluate applied stress intensity factors for normal and upset conditions, considering the lower K1a fracture toughness for crack arrest. Article IWB-3612 also specifies that a safety factor of 4/2 must be used for emergency and faulted conditions, along with the higher K1c fracture toughness for crack initiation. Since the required safety margin for the emergency condition rod withdrawal accident is less than that for normal and upset conditions by a factor of -110 / '/2 = 2.24 and emergency condition stresses are less than the maximum normal and upset condition stresses (Appendix F, Reference 16),

the flaw evaluations performed for normal and upset conditions serve as a bounding analysis for the emergency condition rod withdrawal accident.

Table 5-1: Evaluation of Continuous External Circumferential Flaw for Fatigue Crack Growth along Path I INPUT DATA Geometry: Outside diameter, Do = in.

Inside diameter, Di = in.

Thickness, t= in.

Ri/t =

Flaw Size: Flaw depth, a = in.

a/t =

O Environment: Temperature, T*= F tC Page 25

Controlled Document A

ARE VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-1: Evaluation of Continuous External Circumferential Flaw for Fatigue Crack Growth along Path 1 (Cont'd)

Variation of F Function between Continuous External and Continuous Internal Circumferential Flaws Using Solutions by V. Kumar et al.

Source: EPRI NP-1 931 Topical Report, Section 4.3 for aninternal circumferential crack under remote tension 7(Ref. 6).

The applied KI equation is given by the.expression:

K, = a 4/(n a) F(a/b, R/Ro) where S= P/I ((2 - RI2) and F is a function of a/b and b/Ri, where a/b = 0.177 b/Ri = 0.383 By extrapolation from Table 4-5 of EPRI-1 931, the internal F-factor is estimated to be:

Fintemal = 1.12' Source: GE Report SRD-82-048, Prepared for EPRI Contract RP-1237-1, Fifth & Sixth Semi-Annual Report, Section 3.5 for an external circumferential under remote tension (Ref. 7).

For the external circumferential crack, the expressions for KI and a are as defined above for the internal circumferential crack, where a/b = 0.177 R/Ro = 0.723 From Figure 3-11 of SRD-82-048, the external F-factor is estimated to be:

Fexternal = 1.25 Multiplying Factor:

To estimate the stress intensity factor for an exteirnal circumferential crack from the solution for an internal circumferential crack under'remote tension, the appropriate multiplying factor is:

Fex temal /Fintemal = 1.25 /1 .12 1.12' Thisvalue seems reasonable since from Figure 3-9 of EPRI NP-3607 [8], the multiplying factor for circumferential flaws with an a/t ratio of 0.2 is estimated to be:

Fextemal / Fintemal = 1.10 Page 26

Controlled Document A Document No. 32-9135800-001 AR E VA AREVA NP Inc.,

an AREVA and Siemens company DB-i CRDM Nozzle Weld'Anomaly Flaw Evaluation of IDTB Repair Table 5-1: Evaluation of Continuous External Circumferential Flaw for Fatigue Crack Growth along Path I (Cont'd)

STRESS INTENSITY FACTOR FOR CIRCUMFERENTIAL FLAW Basis: Buchalet and Bamford solution for continuous circumferential flaws on the inside surface of cylinders (Ref 5)

KI= 'q(7ra) [A 0 F1 + (2ar)A1 F 2 + (a2/2)"A2 F3 (4a 3)/(37) A3 F4 ]

where, F1 = 1.1259 + 0.2344(a/t) + 2.2018(a/t) 2 - 0.2083(a/t) 3 3

F2 = 1.0732 + 0.2677(a/t) + 0.6661(a/t) 2 + o..6354(a/t) 3 F3' = 1 .0528 + o.1065.(a/t) + 0.4429(a/t) 2 + 0.6042(a/t) 3 F4 = 1.0387 - 0.0939(a/t) + 0.6018(a/t) 2 + 0.3750(a/t) and the through-wall stress distribution is described by the:third order polynomial, S(x),= A0.+Ajx + A2X2 + A3X3*

Applicablility: Ri/t = 10 alt*,0.8 Axial Stresses:

Wall Residual Normal/Upset Cond. Total Stresses Position Stress Stresses: _at Operation x in Weld Cooldown Shutdown Cooldown Shutdown (in.) (ksi) (ksi) (ksi) (ksi) (ksi)

Stress Coefficients:

Normal/Upset Stress Loading Conditions Coeff. NU1 NU2 (ksi) (ksi)

A0 A1 A2 A3 Page 27

A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-1: Evaluation of Continuous External Circumferential Flaw for Fatigue Crack Growth along Path I (Cont'd)

CRACK GROWTH FOR CIRCUMFERENTIAL FLAW (IN-AIR) - Alloy 52 Aa = AN Co(AKI)n AT AN = 6 fatigue cycles /year Sy= }I ksi AT = 1 year NU1 NU2 NU1 Cycle a KI(a)max Kl(a)min AKI AKI R SR Co=CNi-weld*SR Aa Aa ry ae KI(ae)max (in.) (ksi~Iin) (ksi'~in) (ksi'in) (MPa4m) (M) (in.) (ksi/in) 0 6

12 18 24 30 36 42 48 54 60 66 72 78 84 90 96 102 108 114 120 126 132 138 144 150 I

.Page 28

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-2: Limit Load Analysis for a Continuous External Circumferential Flaw LIMIT LOAD Basis: GE Report SRD-82-048, Combined Fifth and Sixth Semi-Annual Report by V. Kumar et al, Section 3.5 (Ref 7)]

For remote tension loading, Po = 2//3 a, n (Rc 2-Ri 2) where Rc = Ro - a and Ro = in.

a -in.

Then Rc Ri Spsi in.

in. (using the minimum yield strength of Alloy 52M) lbs P0= {

From Reference 21, the applied loads on a typical B&W design CRDM tube are:

a) Normal/Upset conditions, b) Emergency/Faulted conditions, lbs The limit load margins are greater than those required by Article IWB-3642 of Section XI (Ref. 3), as shown below.

a) Normal/Upset conditions, Po/P = 10.44 > 3.0 b) Emergency/Faulted conditions, Po/P = 7.38 > 1.5 Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path I INPUT DATA Geometry: Outside diameter, Do = in.

Inside diameter, Di = in.

t Thickness, in.

Ri/t Flaw depth, Flaw Size: a in.

Flaw length, 2c in.

a/t Environment: Temperature, T OF JC Page 29

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path I (Cont'd)

STRESS INTENSITY FACTOR FOR AXIAL FLAW Basis: Raju & Newman, "Stress Intensity Factors for' Internal & External Surface Cracks in Cylindrical Vessels (Ref. 9) 5 15 A2 a 25

+ G3 A3 a3 5 ]

KI = 4*(JQ) [GOAo a°' +G1 A1 a . +G 2 where, fromTable 4 of Reference, 11, for an external surface crack with t/R = 0.25, a/t = 0.2, a/c = 1.0, the influence coefficients are as follows:

Location: Deepest Point Surface (2ý/n = 1) (20/n = 0)

Go 1.030 1.163 G, 0.720 0.204 G2= 0.591 0.077 G3= 0.513 0.040 and Q= 2.464 = 1 + 1.464 (a/c)1"65 and the through-wall stress distribution is described by the third'order polynomial, S(x) = A0 + AIx + A 2x2+ A 3 x3.

Hoop Stresses:

Wall Residual Normal/Upset Cond. Total Stresses Position Stress Stresses at Operation x in Weld Cooldown Shutdown Cooldown Shutdown (in.) (ksi) (ksi) (ksi) (ksi) (ksi)

Stress Coefficients:

Normal/Upset Stress Loading Conditions Coeff. NUI NU2 (ksi) (ksi)

A0 A1 A2 A3 __

Page 30

A Document No. 32-9135800-001 ARE VA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path 1 (Cont'd)

RADIAL CRACK GROWTH FOR AXIAL FLAW (IN-AIR) - Alloy 600 Basis: Aa = AN C,(AKI)n AT AN =

AT =

6 1

fatigue cycles / year year Sy= } ksi Operating NUl NU2 NUl Time Cycle a KI(a)max KI(a)min AKI AKI R SR Co=CA600*SR Aa Aa ry a. KI(a,)max (yr.)

0.00 0 (in.) (ksi4in) (ksi4/in) (ksi'in) (MPa/m) (iM) (in.) (ks!Vin) 0 0

1.00 6 2.00 12 3.00 18 0 4.00 24 5.00 30 CD.

6.00 36 7.00 42 0.

8.00 48 9.00 54 0 10.00 60 C:

11.00 66 12.00 72 13.00 78 CD 14.00 84 15.00 90 16.00 96 17.00 102 18.00 108 19.00 114 20.00 120 21.00 126 22.00 132 23.00 138 24.00 144 25.00 150 Page 31

A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path 1 (Cont'd)

AXIAL CRACK GROWTH FOR AXIAL FLAW (IN-AIR) - Alloy 600 Basis: Aa = AN Co(AKI)" AT AN =

AT =

6 1

fatigue cycles I year year Sy = } ksi Operating NU1 NU2 NU1 Time Cycle a KI(a)max KI(a)min AKI AKI R SR CO=CA600*SR Aa Aa ry a, KI(a)rmax (yr.) (in.) (ksi'in) (ksi'in) (ksi'in) (MPa'Im) (M) (in.) (ksi4in) 0.00 0 1.00 6 2.00 12 3.00 18 4.00 24 5.00 30 6.00 36 7.00 42 8.00 48 9.00 54 10.00 60 11.00 66 12.00 72 13.00 78 14.00 84 15.00 90 16.00 96 17.00 102 18.00 108 19.00 114 20.00 120 21.00 126 22.00 132 23.00 138 24.00 144 25.00 150 Page 32

A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path I (Cont'd)

RADIAL CRACK GROWTH FOR AXIAL FLAW (IN-AIR) - Alloy 52M Basis: Aa = AN CQ(AKI)n AT AN = 6 fatigue cycles I year Sy={ } ksi.

AT = 1 year Operating NU1 NU2 NU1 Time Cycle a KI(a)max KI(a)min AKI AKI R SR Co=CN~weu*SR Aa Aa ry a, KI(ae)max (yr.) (in.) (ksi'in) (ksivin) (ksi'in) (MPa'm) (m) (in.) (ksi'in) 0.00 0 1.00 6 2.00 12 3.00 18 4.00 24 5.00 30 6.00 36 7.00 42 8.00 48 9.00 54 10.00 60 11.00 66 12.00 72 13.00 78 14.00 84 15.00 90 16.00 96 17.00 102 18.00 108 19.00 114 20.00 120 21.00 126 22.00 132 23.00 138 24.00 144 25.00 150 Page 33

A . Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-3: Evaluation of External Axial Flaw for Fatigue Crack Growth along Path I (Cont'd)

AXIAL CRACK GROWTH FOR AXIAL FLAW (IN-AIR) - Alloy 52M Basis: Aa = AN Co(AKI)n AT AN = 6 fatigue cycles / year Sy=.{ý ksi AT = 1 year Operating NU1 NU2 NU1 Time Cycle a KI(a)max KI(a)min AKI AKI R SR C0=CNiwed*SR Aa Aa ry ae KI(ae)max (y.) (in.) (ksilin) (ksi/in) (ksi'Iin) (MPam) (m) (in.) (ksiqdin) 0.00 0 1.00 6 2.00 12 3.00 18 4.00 24 5.00 30 6.00 36 7.00 42 8.00 48 9.00 54 10.00 60 11.00 66 12.00 72 13.00 78 14.00 84 15.00 90 16.00 96 17.00 102 18.00 108 19.00 114 20.00 120 21.00 126 22.00 132 23.00 138 24.00 144 25.00 150 Page 34

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 INPUT DATA Geometry: Plate thickness, t= in.

Flaw Size: Flaw depth, a= in.

a/t =

Environment: temperature, T= OF

C Page 35

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 (Cont'd)

STRESS INTENSITY FACTOR FOR CYLINDRICAL FLAW IN WELD Basis: Analysis of Flaws, 1.995 ASME'Code, Section Xl, Appendix A (Ref. 3)

KI = [A0 Go + A1 G1 +,A2 G 2 + A3 G 3 4(mia/Q) where Q = 1 + 4.593 (a/I) 165 - qy and qy = [ (A0 Go + A1 G1 + A2 G2 + A3 G3 ) /Yys ]2 /6 For all = 0.0 (continuous flaw) aft <= 0.1 Go = 1.195 G, = 0.773 G2 = 0.600 G3 = 0.501 Stresses are described by a third order polynomial fit over the flaw depth, 2 3 S(x) = A0 + AI(X/a) + A2(x/a) + A3(x/a)

Radial Stresses in Weld:

Wall Residual Normal/Upset Cond. Total Stresses Position Stress Stresses at Operation x in Weld Cooldown Shutdown Cooldown Shutdown (in.) (ksi) (ksi) (ksi) (ksi) (ksi)

Stress Coefficients: a 0.100 in.)

Normal/Upset Stress Loading Conditions Coeff. NU1 NU2 (ksi) (ksi)

A0 A1 A2 A3 Page 36

A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 (Cont'd)

CRACK GROWTH FOR CYLINDRICAL FLAW (IN-AIR) - Alloy 52M Basis: Aa AN C,(AKI)n AT AN = 6 cycles/year Sy= }ksi AT = 1 year Operating NU1 NU2 Time Cycle a Q KI(a)max KI(a)min AKI AKI R SR C0=CNWeld*SR Aa Aa qy Q(a.) KI(ae)max (yr.) (in.) (ksi~in) (ksi'Jin) (ksi'Jin) (MPa'/m) (m) (in.) (ksi~Iin) 0 0 1 6 2 12 3 18 4 24 5 30 6 36 7 42 8 48 9 54 10 60 11 66 12 72 13 78 14 84 15 90 16 96 17 102 18 108 19 114 20 120 21 126 22 132 23 138 24 144 25 150 Page 37

Controlled Document A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 (Cont'd)

STRESS INTENSITY FACTOR FOR CYLINDRICAL FLAW IN HEAD Basis: Analysis of Flaws, 1995 ASME Code, Section Xl, Appendix A (Ref. 3)

KI = [ A0 Go + A1 G1 + A 2 G 2 + A3 G 3 ] 4(7a/Q) where Q = 1 + 4.593 (a/l) 1' 65 - qy 2

and qy = [ (A0 Go + A, G1 + A2 G 2 + A3 G 3) / ys 16 For a/I = 0.0 (continuous flaw) a/t <= 0.1 Go 1.1945 G,= 0.7732 G2-0.5996 G3=

0.5012 Stresses are described by a third order polynomial fit over the flaw depth, 2 3 S(x) = A0 + A1(x/a) + A2(x/a) + A3(x/a)

Radial Stresses in We ld:

Wall Residual Normal/Upset Cond. Total Stresses Position Stress Stresses at Operation x in Weld Cooldown Shutdown Cooldown Shutdown (in.) (ksi) (ksi) (ksi) (ksi) (ksi)

Stress Coefficients: (a= 0.100 in. )

Normal/Upset Stress Loading Conditions Coeff. NU1 NU2 (ksi) (ksi)

A1 A2 A3 Page 38

A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Table 5-4: Evaluation of a Continuous Cylindrical Surface Crack for Fatigue Crack Growth along Path 2 (Cont'd)

CRACK GROWTH FOR CYLINDRICAL FLAW (IN-AIR) - FERRITIC MATERIAL Basis: Aa = AN Co(AKI)n AT AN = 6 cycles/year AT = 1 Sy= { } ksi year Operating NU1 NU2 Time Cycle a KI(a)max KI(a)min AKI R S Co Aa qy Q(ae) KI(ae)max (yr.) (in.) (in.) (ksiqin)

(ksiqin) (ksNin) (ksiqin) 0 0 1 6 2 12 3 18 4 24 5 30 6 36 7 42 8 48 9 54 10 60 11 66 12 72 13 78 14 84 15 90 16 96 17 102 18 108 19 114 20 120 21 126 22 132 23 138 24 144 25 150 Iae Page 39

Controlled Document A Document No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA andSiemens company.

DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair 6.0 RESULTS The flaw evaluation results for 25 years, of fatigue crack growth are as follows.

6.1 Propagation of a.Continuous External Circumferential Flaw along Path I a) Fatigue crack growth analysis:

Initial flaw size, ai = 0'100 in.

Final flaw size, at<{ } in.

Stress intensity factor at final flaw size, KI (aef) < 0 ksi4in Fracture toughness Ki*a= 200 ksi'in Fracture toughness margin, K1a / Ki > /10 b) Limit load analysis:

Limit load, PO 0 { } lbs Applied loads: normal/upset, { } lbs emergency/faulted, Po/P

{ } lbs Limit load margins: normal/upset, Po/ P= 10.44 > 3.0 emergency/faulted, P0 P= 7.38 > 1.5 6.2 Fatigue Crack Growth of a Semi-Circular External Axial Flaw along Path I Initial flaw size, ai = 0.100 in.

Radial Growth Final flaw size, at<{ } in.

Stress intensity factor atfinal flaw size, KI (a~f) = 29.45 ksi'in Fracture toughness Kia = 200 ksi*/in Fracture toughness margin, K.a/Ki = 6.79 > q1o Axial Growth Final flaw size, atf<{ }in.

Stress intensity factor at final flaw size, KI (aef) = 34.46 ksi'/in Fracture toughness Kia = 200 ksiIin Fracture toughness margin, Kja / KI= 5.80 > 410 6.3 Fatigue Crack Growth of a Continuous Cylindrical Flaw along Path 2 Initial flaw size, a1= 0.100 in.

Final flaw size, af< { } in.

Stress intensity factor at final flaw size, KI (af) = 51.61 ksi'/in Fracture toughness KIa = 200 ksi'/in Fracture toughness margin, KIa/K 1 = 3.88 > 410 Page 40

Controlled Document AR AVA Document No. 32-9135800-001 AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair The results of the analysis demonstrate that the 0.10 inch weld anomaly is acceptable for a 25 year evaluation life of the CRDM ID temper bead weld repair. However, note that the design life the RVCH as per the design specification (Ref.2) is 4 years. Significant fracture toughness margins have been demonstrated for both the flaw propagation paths considered in the analysis. The minimum fracture toughness margins for flaw propagation Paths 1 and 2 have been shown to be 5.80 and 3.88, respectively, as compared to the required margins of 410 for normal/upset conditions and 42 for emergency/faulted conditions per Section Xl, IWB-3612 (Ref. 3). Fatigue crack growth is minimal. The maximum final flaw size is { } inch (considering both flaw propagation paths). A limit load analysis was also performed considering the ductile Alloy 600 and Alloy 690 materials along flaw propagation Path 1. The analysis showed limit load margins of 10.44 for normal/upset conditions and 7.38 for emergency/faulted conditions, as compared to the required margins of 3.0 and 1.5, respectively, per Section Xl, IWB-3642 (Ref.3).

Page 41

Controlled Document A

AR VA Document No. 32-9135800-001 AREVA NO Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair

7.0 REFERENCES

1. AREVA NP Inc Drawing 02-9134305E-004, "Davis Besse CRDM Nozzle ID Temper Bead Weld Repair"

2. AREVA NP Inc Document 08-9134304-000, "Davis Besse RVCH CRDM Penetration Modification"

3. ASME Boiler and Pressure Vessel Code, Section Xl, Rules for Inservice Inspection of Nuclear Power Plant Components, 1995 Edition with 1996 Addendum

4. ASME Section II, Part C, "Specification for Welding Rods, Electrodes, and Filler Metals," 1999 Addenda

5. C.B. Buchalet and W.H. Bamford, "Stress Intensity Factor Solutions for Continuous Surface Flaws in Reactor Pressure Vessels," Mechanics of Crack Growth, ASTM STP 590, American Society for Testing and Materials, 1976, pp. 385-402

6. EPRI Topical Report, EPRI NP-1931, "An Engineering Approach for Elastic-Plastic Fracture Analysis,:'

Research Project 1237-1, prepared by V. Kumar et al of General Electric Company, July 1981

7. General Electric Report, SRD-82-048, "Estimation Technique for the Prediction of Elastic-Plastic Fracture of Structural Components of Nuclear Systems," by V. Kumar et al, Contract RP1237-1, Combined Fifth and Sixth Semi-Annual Report, March 1982

8. EPRI Topical Report, EPRI NP-3607, "Advances in Elastic-Plastic Fracture Analysis," Research Project 1237-1, prepared by V. Kumar et al of General Electric Company, August 1984

9. I.S. Raju and J.C. Newman Jr., "Stress Intensity Factors for Internal and External Surface Cracks in Cylindrical Vessels," Transactions of the ASME, Journal of Pressure Vessel Technology, pp. 293-298, Vol. 104, November 1982

10. T.L. Anderson,- Fracture Mechanics: Fundamentals and Applications, CRC Press, 1991

11. NUREG/CR-6721 "Effects of Alloy Chemistry, Cold Work, and Water Chemistry on Corrosion Fatigue and Stress Corrosion Cracking of Nickel Alloys and Welds," U.S. Nuclear Regulatory Commission (Argonne National Laboratory), April 2001

12. NUREG/CR-6921 "Crack Growth Rates in a PWR Environment of Nickel Alloys from the Davis-Besse and V.C. Summer Power Plants," U.S. Nuclear Regulatory Commission (Argonne National Laboratory), April 2006

13. AREVA NP Document No.38-1288355-00, "Flaw Acceptance Criteria"

14. BAW-10046A, Rev. 2, "Methods of Compliance with Fracture Toughness and Operational Requirements of 10 CFR 50, Appendix G," B&W Owners Group Materials Committee Topical Report, June 1986

15. AREVA.NP Document No. 51-9137401-000, "Evaluation of Fluid Temperature in DB RV Closure Head"

16. AREVA NP Document No. 32-5012424-12, "CRDM Temper Bead Bore Weld Analysis," April 2004

17. AREVA NP Document No. 18-1149327-003, "Functional Specification for Reactor Coolant System for Davis-Besse"

18. AREVA NP Document No. 32-5021539-02, "ANO-1 CRDM Nozzle IDTB Weld Anomaly Flaw Evaluations"

19. W.J. Mills, "Fracture Toughness of Two Ni-Fe-Cr Alloys," Hanford Engineering Development Laboratory Document HEDL-SA-3309, April 1985

20. ASME Boiler and Pressure Vessel Code,Section III, Rules for Construction of Nuclear Power Plant Components, Division 1 - Appendices, 1989 Edition No Addenda

21. AREVA NP Document No. 32-5012403-00, "OC-3 CRDM Nozzle Circumferential Flaw Evaluations", April 2001 Page 42

Controlled Document A Document-No. 32-9135800-001 AREVA AREVA NP Inc.,

an AREVA and Siemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair APPENDIX A: COMPARISION OF DB-1 AND ANO-1 REACTOR VESSEL CLOSURE HEADS The table below provides comparison of the critical dimensions that are applicable to the DB-1 and ANO-1 reactor vessel replacement closure heads.

Table A-I: Comparison of Critical Dimensions of DB-1 and ANO-1 4 1 4 4 +

4 4 +

i A

-I Table A-2: Comparison of IDTB Materials of DB-1 and ANO-1 As the tables above indicate, the DBl/Midland Head and ANO-1 are identical in geometry and material composition. It is therefore concluded that the Stress calculations for IDTB weld repair for ANO-1 performed in Doc. # { } (Reference All) is applicable for the DB-1/Midland replacement RVCH and that resulting residual stresses for the ANO-1 ID temper bead welds are applicable to DB-1 as well.

Page 43

Controlled Document A Document No. 32-9135800-001 AR EVA AREVA NP Inc.,

an AREVA andSiemens company DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Repair Appendix

References:

r Page 44

ENCLOSURE D AFFIDAVIT FOR DB-1 CRDM NOZZLE WELD ANOMALY FLAW EVALUATION OF IDTB ALTERNATE REPAIR WITH ALLOY 52M/82 AREVA CALCULATION 32-9136807-001 Three Pages Follow

AFFIDAVIT COMMONWEALTH OF VIRGINIA )

) ss.

CITY OF LYNCHBURG )

1. My name is Gayle F. Elliott. I am Manager, Product Licensing, for AREVA NP Inc. and as such I am authorized to execute this Affidavit.

2. I am familiar with the criteria applied by AREVA NP to determine whether certain AREVA NP information is proprietary. I am familiar with the policies established by AREVA NP to ensure the proper application of these criteria.

3. I am familiar with the AREVA NP information contained in Calculation Summary Sheet (CSS) 32-9136807-001 entitled "DB-1 CRDM Nozzle Weld Anomaly Flaw Evaluation of IDTB Alternate Repair with Alloy 52M/82," dated May 2010 and referred to herein as "Document." Information contained in this Document has been classified by AREVA NP as proprietary in accordance with the policies established by AREVA NP for the control and protection of proprietary and confidential information.

4. This Document contains information of a proprietary and confidential nature and is of the type customarily held in confidence by AREVA NP and not made available to the public. Based on my experience, I am aware that other companies regard information of the kind contained in this Document as proprietary and confidential.

5. This Document has been made available to the U.S. Nuclear Regulatory Commission in confidence with the request that the information contained in this Document be withheld from public disclosure. The request for withholding of proprietary information is made in accordance with 10 CFR 2.390. The information for which withholding from disclosure is

requested qualifies under 10 CFR 2.390(a)(4) "Trade secrets and commercial or financial information."

6. The following criteria are customarily applied by AREVA NP to determine whether information should be classified as proprietary:

(a) The information reveals details of AREVA NP's research and development plans and programs or their results.

(b) Use of the information by a competitor would permit the competitor to significantly reduce its expenditures, in time or resources, to design, produce, or market a similar product or service.

(c) The information includes test data or analytical techniques concerning a process, methodology, or component, the application of which results in a competitive advantage for AREVA NP.

(d) The information reveals certain distinguishing aspects of a process, methodology, or component, the exclusive use of which provides a competitive advantage for AREVA NP in product optimization or marketability.

(e) The information is vital to a competitive advantage held by AREVA NP, would be helpful to competitors to AREVA NP, and would likely cause substantial harm to the competitive position of AREVA NP.

The information in the Document is considered proprietary for the reasons set forth in paragraphs 6(b) and 6(c) above.

7. In accordance with AREVA NP's policies governing the protection and control of information, proprietary information contained in this Document have been made available, on a limited basis, to others outside AREVA NP only as required and under suitable agreement providing for nondisclosure and limited use of the information.

8. AREVA NP policy requires that proprietary information be kept in a secured file or area and distributed on a need-to-know basis.

9. The foregoing statements are true and correct to the best of my knowledge, information, and belief.

SUBSCRIBED before me this day of f\ktA/2010.

Sherry L. McFaden NOTARY PUBLIC, COMMONWEALTH OF VIRGINIA MY COMMISSION EXPIRES: 10/31/10 Reg. # 7079129

- SHERRY L. MCFADEN Notary Public Commonwealth ot Virginia 7079129 I

My Commission Expires Oct 31. 2010

ENCLOSURE E AFFIDAVIT FOR DB-1 CRDM NOZZLE J-GROOVE WELD FLAW EVALUATION FOR IDTB REPAIR AREVA CALCULATION 32-9134664-003 Three Pages Follow

AFFIDAVIT COMMONWEALTH OF VIRGINIA )

) ss.

CITY OF LYNCHBURG )

1. My name is Gayle F. Elliott. I am Manager, Product Licensing, for AREVA NP Inc. and as such I am authorized to execute this Affidavit.

2. I am familiar with the criteria applied by AREVA NP to determine whether certain AREVA NP information is proprietary. I am familiar with the policies established by AREVA NP to ensure the proper application of these criteria.

3. I am familiar with the AREVA NP information contained in Calculation Summary Sheet (CSS) 32-9134664-003 entitled "DB-1 CRDM Nozzle J-Groove Weld Flaw Evaluation for IDTB Repair," dated May 2010 and referred to herein as "Document." Information contained in this Document has been classified by AREVA NP as proprietary in accordance with the policies established by AREVA NP for the control and protection of proprietary and confidential information.