ML071490278

From kanterella
Jump to navigation Jump to search
Areva Np, Calculation Document No. 32-9046889-002, Callaway CRDM Hypothetical Flaw Evaluations
ML071490278
Person / Time
Site: Callaway Ameren icon.png
Issue date: 04/25/2007
From: Gunawardane H
AREVA NP
To:
Office of Nuclear Reactor Regulation
References
EA-03-009, ULNRC-05416 32-9046889-002
Download: ML071490278 (61)
v • d • e


Text

Attachment 3 to ULNRC-05416 AREVA Calculation Callaway CRDM Hypothetical Flaw Evaluations AREVA NP Document No. 32-9046889-002 NON-PROPRIETARY VERSION

20697-10 (3/30/06)

A CALCULATION

SUMMARY

SHEET (CSS)

AR EVA Document Identifier 32-9046889-002 Title CALLAWAY CRDM HYPOTHETICAL FLAW EVALUATIONS PREPARED BY:

REVIEWED BY:

METHOD: 0 DETAILED CHECK El INDEPENDENT CALCULATION NAME H. P. GUNAWARDANE NAME A. D. NANA SIGNATURE SIGNATURE TITLE ENGINEER IV DATE ( 12.5- (O0'-

TITLE ADVISORY ENGINEER DATE

____(

COST REF.

TM STATEMENT:

CENTER 41314 PAGE(S) 60 REVIEWER INDEPENDENCE NAME B. DJAZMATI PURPOSE AND

SUMMARY

OF RESULTS:

This document is a non-propietary version of AREVA NP Document Number 32-9045288-002. The proprietary information removed from 32-9045288-002 is indicated by a pair of square brackets "[

]". The geometry and operating conditions are AmerenUE Proprietary and the detailed through-wall stresses are Dominion Engineering, Inc. Proprietary.

The CRDM nozzles at Callaway will be undergoing Ultrasonic Testing (UT) inspections during the Spring of 2007. RVCH nozzle penetrations 74 through 78 have an area that is not inspectable. This fracture mechanics analysis is being performed in order to support the potential for not obtaining full 3600 UT coverage in certain localized regions of the CRDM below the attachment weld. The purpose of this analysis is to determine the maximum allowable beginning-of-life (BOL) through-wall flaw size, at each of the postulated flaw regions, which would not reach critical flaw size conservatively considering a two-year service period.

This analysis addresses the effects of the as-designed and the as-built weld configurations. For this purpose, three types of outermost nozzle configurations (490 penetration angle) were analyzed by Dominion Engineering, Inc. (DEI). They are referred to as cases 49A, 49B, and 49C. A hypothetical circumferential through-wall flaw and an axial through-wall flaw were evaluated in each of the three types of nozzles.. These postulated flaws were located at or just below the attachment weld.

The purpose of Revision 001 is to update the calculation for a period of seven years between inspections.

The purpose of Revision 002 is to incorporate minor editorial customer comments.

The results of the flaw evaluation are summarized in Section 5.0.

THE DOCUMENT CONTAINS ASSUMPTIONS THAT MUST BE VERIFIED PRIOR TO USE ON THE FOLLOWING COMPUTER CODES HAVE BEEN USED IN THIS DOCUMENT:

SAFETY-RELATED WORK CODENERSION/REV CODENERSION/REV YES ZNO AREVA NP Inc., an AREVA and Siemens company.

Page I of 60

AREVA 32-9046889-002 ARE VA 32-9046889-002 Record of Revisions Revision Date PageslSections Changed Brief Description 000 03/07 All Original Release 001 04/07 All Updated calculations for period of seven year between inspections 002 04/07 All Incorporated minor editorial customer comments (corrected flaw numbers in List of Tables) 2

A AR EVA 32-9046889-002 Table of Contents Section Title Page Record of Revisions..............................................................................................................

2 List of Tables.............................................................................

4 List of Figures.........................................................................................................................

5 1.0 Purpose...........................................................................................................

6 2.0 Analytical M ethodology...................................................................................

6 3.0 Key Assum ptions............................................................................................

7 4.0 Calculations.....................................................................................................

7 4.1 Geom etry and Flaw M odel..............................................................................

7 4.2 Nozzle Dim ensions..........................................................................................

7 4.3 Postulated Flaw Shapes..................................................................................

8 4.4 M aterial Properties........................................................................................

9 4.5 Primary Water Stress Corrosion Cracking (PWSCC)....................................

10 4.6 Stress Intensity Factor (SIF) Solutions.............................................................

11 4.6.1 Circumferential Through-W all Flaws................................................................

11 4.6.2 Edge Crack...........................................................................................................

12 4.7 Applied Stresses...............................................................................................

13 4.7.1 Applied Stresses for Nozzle 49A....................................................................

16 4.7.2 Applied Stresses for Nozzle 49B.....................................................................

22 4.7.3 Applied Stresses for Nozzle 49C.........................

28 4.8 Acceptance Criteria.............................................................................................

34 4.9 Flaw Evaluations...................................................................................................

35 4.9.1 Flaw Evaluation for Nozzle 49A............................................................................

35 4.9.2 Flaw Evaluation for Nozzle 49B.........

42 4.9.3 Flaw Evaluation for Nozzle 49C..........................................................................

49 4.10 Required Vertical Interface (Contact Area) Between Nozzle and Weld.......... 56 5.0 Results, Sum m ary/Conclusion..............................................................................

57 5.1 M inim um Inspection Height for Axial Flaws....................................................

57 5.2 Circumferential Below the W eld Through-W all Flaws...........................................

59 6.0 References..........................................................................................................

60 7.0 Computer Output..........................................

60 3

A AR EVA 32-9046889-002 LIST OF TABLES Table Title Paqe

1.

Steady State Axial Stresses in 490 CRDM Nozzle "A" on Downhill Side........................ 17

2.

Steady State Axial Stresses in 490 CRDM Nozzle "A" on Uphill Side..................

18

3.

Steady State Hoop Stresses in 490 CRDM Nozzle "A" on Downhill Side......................

19

4.

Steady State Hoop Stresses in 490 CRDM Nozzle "A" on Uphill Side..........................

20

5.

Axial Stresses Along the Circumference at the Bottom of the Weld in 490 Nozzle "A". 21

6.

Steady State Axial Stresses in 490 CRDM Nozzle "B" on Downhill Side.................... 23

7.

Steady State Axial Stresses in 490 CRDM Nozzle "B" on Uphill Side.........................

24

8.

Steady State Hoop Stresses in 490 CRDM Nozzle "B" on Downhill Side....................

25

9.

Steady State Hoop Stresses in 490 CRDM Nozzle "B" on Uphill Side........................

26

10.

Axial Stresses Along the Circumference at the Bottom of the Weld in 490 Nozzle "B".. 27

11.

Steady State Axial Stresses in 490 CRDM Nozzle "C" on Downhill Side...................

29

12.

Steady State Axial Stresses in 490 CRDM Nozzle "C" on Uphill Side.......................

30

13.

Steady State Hoop Stresses in 490 CRDM Nozzle "C" on Downhill Side...................

31

14.

Steady State Hoop Stresses in 490 CRDM Nozzle "C" on Uphill Side.......................

32

15.

Axial Stresses Along the Circumference at the Bottom of the Weld in 490 Nozzle "A".. 33

16.

Axial Stresses Along the Circumference at Bottom of Weld of Nozzle 49A (Uphill Side)....................................................

36

17.

Circumferential Growth of Flaw #1 a in Nozzle 49A (Bottom of Weld, Uphill Side) fo r 7 y e a rs.....................................................................................................................

3 7

18.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49A (D ow nhill S ide)......................................................................................................

38

19.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49A (Uphill Side).. 39

20.

Axial Growth of Flaw #2a in Nozzle 49A (Bottom of Nozzle, Downhill Side) for 7 years 40

21.

Axial Growth of Flaw #2a in Nozzle 49A (Bottom of Nozzle, Uphill Side) for 7 years.... 41

22.

Axial Stresses Along the Circumference at Bottom of Weld of Nozzle 49B (Uphill S id e )...................

4 3

23.

Circumferential Growth of Flaw #1 b in Nozzle 49B (Bottom of Weld, Uphill Side) for 7 years.......

44

24.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49B (Downhill S id e )....................................

.............................................. 4 5

25.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49B (Uphill Side).. 46

26.

Axial Growth of Flaw #2b in Nozzle 49B (Bottom of Nozzle, Downhill Side) for 7 years 47 27 Axial Growth of Flaw #2b in Nozzle 49B (Bottom of Nozzle, Uphill Side) for 7 years.... 48 4

A ARE VA 32-9046889-002 Table Title Page

28.

Axial Stresses Along the Circumference at Bottom of Weld of Nozzle 49C (Uphill Side).........

50

29.

Circumferential Growth of Flaw #1 c in Nozzle 49C (Bottom of Weld, Uphill Side) for 7 ye a rs.............................................................................................................

..... 5 1

30.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49C (Downhill S id e )...................................................................

5 2

31.

Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49C (Uphill Side).. 53

32.

Axial Growth of Flaw #2c in Nozzle 49C (Bottom of Nozzle, Downhill Side) for 7 years 54

33.

Axial Growth of Flaw #2c in Nozzle 49C (Bottom of Nozzle, Uphill Side) for 7 years.... 55

34.

Summary of Minimum Inspection Heights for Axial Flaws below the Weld............... 57

35.

Summary of Circumferential Below the Weld Through-Wall Flaws..............

59 LIST OF FIGURES Title Page

1.

CRDM Penetration Node Numbering Scheme in DEl FEA Model (Ref. 1)....................

13

2.

Geometry of 48.70 Penetration, As Designed (FEA Model Weld Geometry in Red)

(R e f. 1 )........................................................................

................................................ 1 5

3.

Geometry of 48.70 Penetration, As Built Assumptions (FEA Model Weld Geometry in R e d ) (R e f. 1 )..............................................................................................................

1 5

4.

Schematic Showing the Required "Min. Inspection Band" from Downhill to Uphill S id e.............................................................................................................................

... 5 8 5

A AR EVA 32-9046889-002 1.0 PURPOSE The CRDM nozzles at Callaway (CA) will be undergoing Ultrasonic Testing (UT) inspections during the Spring of 2007 Reactor vessel closure head (RVCH) nozzle penetrations 74 through 78 have an area that is not inspectable. This fracture mechanics analysis is being performed in order to support the potential for not obtaining full 3600 UT coverage in certain localized regions of the CRDM Ibelow the attachment weld. The purpose of this analysis is to determine the maximum allowable beginning-of-life (BOL) through-wall flaw size, at each of the postulated flaw regions, which would not reach critical flaw size conservatively considering a period of seven years between inspections.

2.0 ANALYTICAL METHODOLOGY The localized regions within the CRDM nozzle that may not receive full 3600 coverage are in the portions of the nozzle at or just below the bottom elevation of the J-groove weld. This evaluation will consider the stresses from each of three Dominion Engineering, Inc. (DEI) finite element analysis models that were performed in support of this analysis (Reference 1).. Each of these models represents different heights from the bottom of the nozzle to the bottom of the weld corresponding to the downhill side of the nozzle.

The allowable BOL flaw size for a given service period will be determined, through an iterative analysis, by considering flaw growth in a PWR environment due to PWSCC, and comparing against the allowable end-of-life (EOL) flaw size, for hypothetical axial through-wall flaws or edge cracks postulated at the bottom of the CRDM nozzles as well as hypothetical circumferential through-wall flaws below the weld. The fatigue crack growth will not be accounted for in this analysis because previous experience with similar geometries and loading has shown that fatigue crack growth is approximately three orders of magnitude less than PWSCC.

The maximum allowable EOL flaw size is based on the current NRC accepted flaw evaluation criteria, in Alloy 600 reactor vessel head partial penetration nozzles. Stresses that contribute to PWSCC are the long term steady state stresses due to shrinkage of the partial penetration attachment weld (residual stresses) and steady state pressure and thermal loads.

The following postulated through-wall flaws in the Alloy 600 CRDM nozzles are evaluated in the present analysis.

1)

Circumferential flaw located at or just below the bottom elevation of the J-groove weld in the outermost CRDM nozzle (48.7 degree penetration angle) for each of the three DEI stress models, referred to as 49A, 49B, and 49C.

2)

Edge crack located at the bottom of the outermost CRDM nozzle (48.7 degree penetration angle) for each of the three DEI stress models, noted above.

The above hypothetical flaws are evaluated as flaw #1a through #1c, and flaw #2a through #2c, respectively, where the flaw ID numbers "a" through "c" are defined in Section 4,2.

6

A ARE EVA 32-9046889-002 3.0 KEY ASSUMPTIONS There are no major assumptions in this document that require verification., Minor assumptions are noted where applicable.

4.0 CALCULATIONS 4.1 Geometry and Flaw Model The nozzle is described by its basic diameters. Circumferential through-wall flaws are modeled as through cracks in an infinite body subjected to arbitrary loading. Axial through-wall cracks are modeled as a continuous surface crack in a semi-infinite body under an arbitrary stress profile.

4.2 Nozzle Dimensions The cylindrical CRDM nozzle is dimensioned as follows to be in agreement with the Dominion Engineering residual stress analysis (see Section 4.6). These dimensions are based on Reference 2.

Basic Parameters Outside diameter, Do =

Inside diameter, Di

=

))

Derived dimensions are:

Outside radius, R0 Inside radius, R.

Thickness, t Mean radius, R I

=1 Heiclht of the nozzles below the weld* in DEI Finite Element Models (FEMs):

Flaw ID a

b c

DEI FEM # (Ref. 1) 49A 49B 49C Height of Nozzle (Ref. 1)

[

I

  • Corresponding to the downhill side of the nozzle 7

A AREVA 32-9046889-002 4.3 Postulated Flaw Shapes The crack is modeled as a through-wall crack in an infinite body and subjected to an arbitrary stress profile. A circumferential through-wall flaw is shown below. The length of the crack, 2a, is 20R (or flaw length, a, is eR).

Thrcugh-\\/a[ RIaw R

Ri An edge crack (axially oriented through-wall flaw with respect to the nozzle axis) with flaw size, a, is modeled as a continuous surface crack in a semi-infinite body and subjected to arbitrary loading as depicted below. The location x = 0 corresponds to the bottom of the nozzle.

G(x) x 8

A AREVA 32-9046889-002 4.4 Material Properties The Callaway CRDM nozzles are made from Alloy 600 material to ASME specification SB-167 for tubular products (Reference 3).

A value nozzle yield strength value of 45.0 ksi at room temperature is assumed (Reference 1).

The yield strength at a normal operating temperature of [

] (Reference 1, 8) is obtained by multiplying the room temperature value by the ratio of the ASME Code minimum values at 70°F and [

], as shown below.

Condition Temperature Yield Strength, S, (ksi)

(OF)

ASME Code (Ref 4.)

Callaway Room Temperature 70 35.0 45.0 Normal Operating

[

]

[

I

[

I 9

A AR EVA 32-9046889-002 4.5 Primary Water Stress Corrosion Cracking (PWSCC)

Flaw growth due to primary water stress corrosion cracking (PWSCC) is calculated using the NRC flaw evaluation guideline (Reference 5, 6) for dispositioning flaws in reactor vessel head penetration base metal material (Alloy 600). This model provides a reference crack growth rate at 325°C (617 0F) and uses an activation energy of 31,000 calories/mole to account for differences in temperature.

Using a temperature correction factor (C,) that reduces to unity at 325°C, crack (SCC) growth equation is:

the stress corrosion Metric units:

da/dt = C,(2.67 xl 0-12)(K, - 9)116 m/sec where K, is the applied stress intensity factor in MPaqm, or English units:

da/dt=Co(1.17x 10-1

)(KI-8.19)1 16 in/sec da/dt = C0(3.69 x 10-3 )(KI -8.19)1'16 in/yr or, where K, is the applied stress intensity factor in ksi'/in.

The temperature correction coefficient, Co, is defined as (1 =e C0 e R.T Tref) where and Q = 130 kJ/mole = 31,000 calories/mole R = 8.314 x 10-3 kJ/mole-0 K = 1.987 calories/mole-°K T = Operating temperature in degrees Kelvin Tref = Reference temperature in degrees Kelvin The C0 term is tabulated below as a function of temperature, based on:

Tref = 325.0 "C

= 617.0 'F

= 598.2 °K, T

T T

Co (OF)

(°C)

(°K) 617.0 325.0 598.2 1.0000

[

]

[

]

[

I

[]

It is noted that the crack growth equation given above includes an explicit threshold for stress intensity factor (9 MPa*/m or 8.19 ksilin) below which crack propagation will not occur.

10

A AREVA 32-9046889-002 4.6 Stress Intensity Factor (SIF) Solutions Two types of flaw are considered in the present flaw evaluations, circumferential through-wall flaws and an edge crack located at the bottom of the nozzle. The stress intensity factor solutions used to analyze these flaws are discussed in this section.

4.6.1 Circumferential Through-Wall Flaws The circumferential through-wall flaw SIF solution, derived in Reference 7, is utilized in this analysis. The solution is for a through-wall crack in an infinite body subjected to a stress profile symmetric with respect to the middle of the crack as shown below.

where, a = flaw length

/ = 2a = crack length Stress intensity factors are determined at the crack tip, using cubic through-wall stress profiles. The SIF solution is described below.

polynomials to characterize K,= V~a[(AO +A,)+ A, 2a+A2 a2 +A3t(4a'~J 11

A.

AR EVA 32-9046889-002 The above SIF solution characterizes the distribution of stress through the wall as a third-order polynomial up to the depth of the flaw, cy=Ao+AIx+A 2x 2 +A 3x 3,

where, x =

distance from the middle of the crack A0, A1, A2, and A3 = coefficients of the polynomial expression representing the stress profile in the uncracked section The normal operating steady state condition pressure value of 2.332 ksi is considered as the crack face pressure, AP which is subsequently added to the constant A0 stress term.

4.6.2 Edge Crack The SIF solution for an edge crack under an arbitrary stress profile, also derived in Reference 7, is utilized in this analysis. In that Reference, the solution is referred to as a continuous surface crack in a semi-infinite body. The edge crack is schematically illustrated in Section 4.3. In this analysis the edge crack is postulated at the bottom of the nozzle.

The stress intensity factor for such a flaw is given by 2a a2 A3 4a3 ii K, =1.12ýira (A 0+A,)+ AA,

+A 2 a-- +A 3 a 3J This solution is essentially identical to the circumferential through-wall solution given in Section 4.6.1 with the exception of a multiplication factor of 1.12 on the SIF solution. This factor accounts for free surface effects. As stated in Reference 7, this factor strictly applies only to the uniform component of the stress profile, A0. However, in this solution, it is being conservatively applied to all the components of the stress profile. The through-wall stress distribution is as defined in Section 4.6.1 where x is the distance from the bottom of the nozzle.

12

A AREVA 32-9046889-002 4.7 Applied Stresses The maximum sustained steady state stresses needed to predict crack growth by stress corrosion cracking in a primary water environment are obtained from an elastic-plastic three-dimensional finite element analysis (Reference 1) performed by Dominion Engineering, Inc.

(DEI). Figure 1 presents a sketch of the finite element model of nozzle which includes a single nozzle, the partial penetration attachment weld, the weld buttering, and a portion of the reactor vessel head, with cladding. The finite element node numbering scheme, which is utilized to report stresses, is described in Figure 1.

+ a"~I.......

M a

Dowuhill pLottanodes me Ciý- Sefivm LyhM -alme uo&r xe 120 OW-. Smn.

V ShefllNode Samikm Cs at Aa ID (minged wkube 00) ivkýdare-Sio

'275a

  • dye ofhefl LNdi=

Node am~bem in nozz4e imatre biy IOD up ea le&

of the nozzle.

Figure 1. CIRDM Penetration Node Numbering Scheme in DEl FEA Model (Ref. 1) 13

A A R E VA 32-9046889-002 It should be noted that the fatigue crack growth will not be accounted for in this analysis because previous experience with similar geometries and loading has shown that fatigue crack growth is three orders of magnitude less than PWSCC.

DEI provided FE stresses for nozzle 49A. Nozzle "49A" (48.70 penetration angle) represents the "as-designed" height of approximately [

] below the bottom of the weld on the downhill side as illustrated in Figure 2.

In addition, DEI provided FE stresses for nozzles 49B and 49C which represent the "as-built" cases shown in Figure 3. Each of these nozzles represents different heights of the nozzle from the bottom of the attachment weld to the bottom of the nozzle as described in Section 4.2. The applied stresses for nozzles 49A, 49B, and 49C, are given in Sections 4.7.1, 4.7.2, and 4.7.3, respectively.

The DEI analysis simulated the heatup of the weld, butter, and adjacent material during the welding process and the subsequent cooldown to ambient temperature, a pre-service hydro test, and operation at steady state pressure and temperature conditions. The final stress is strongly dependent on the yield strength of the nozzle. A nozzle yield strength value of 45.0 ksi was used by DEL.

The normal operating pressure is [

] (Reference 1, 8). Although the effects of this pressure load are included in the steady state stresses reported in Tables 1 through 15, an additional load will be considered in the flaw evaluations by applying this pressure to the crack face.

Time dependent stress corrosion crack growth is calculated in half yearly increments.

14

A

AREVA, 32-9046889-002 Figure 2. Geometry of 48.70 Penetration, As Designed (FEA Model Weld Geometry in Red) (Ref 1)

"'1 Case B Case C Figure 3. Geometry of 48.70 Penetration, As Built Assumptions (FEA Model Weld Geometry in Red) (Ref 1) 15

A AREVA 32-9046889-002 4.7.1 Applied Stresses for Nozzle 49A Steady state axial and hoop stresses, on the downhill and the uphill sides of nozzle 49A are summarized in Tables 1 through 4 for the 48.70 penetration angle nozzle analyzed by DEI, as listed below. Stresses are provided for each node on the downhill and uphill sides of the nozzle, referenced to the inside surface nodal locations.

DEI Analysis Case Stress Summary Tables Nozzle Anqle*

48.70 48.70 Yield Type Downhill Strengqth Side Uphill Side 2

4 Outermost nozzle Outermost nozzle 45.0 ksi Axial 45.0 ksi Hoop 1

3

  • Relative to the center of the head.

The axial stresses from the DEI analysis, reported every 15 degrees in the circumferential direction from 0-degrees (downhill side) to 180-degrees (uphill side), are also summarized. The stresses are summarized for the bottom of the weld locations in Table 5.

The steady state stresses are reviewed to determine which region from the downhill to the uphill location is the most highly stressed location. From Table 5, the maximum axial stress for the bottom of the weld location occurs at the uphill side. From review of Tables 3 and 4, it is clear that the maximum hoop stress below the weld occurs at the uphill side.

16

A AREVA 32-9046889-002 Table 1. Steady State Axial Stresses in 490 CRDM Nozzle "A" on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wail Through-Wall Position Value Bottom Node Elevation Thickness In side 1/T ide of Nozzle 1

BON

-1488 101

-332 201 2196 301 4672 401 6406 501 7221 601 BOW 2004 701

-5710 801

-13265 901

-14292 1001

-10535 1101

-4546 1201 2111 1301 7624 1401 TOW 12909 1501 20895 1601 18528 1701 16319 1801 15206 1901 13429 2001 11468 2101 9107 2201 6811 2301 5086 2401 3889 2501 3120 2601 2515 2701 1359 2801 481 2901 1947 3001 1817 3101 2332 3201 TOH 2372 3301 1TON 2243 17

A AR EVA 32-9046889-002 Table 2. Steady State Axial Stresses in 490 CRDM Nozzle A" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEl [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside

, Average from Surface Wall Through-Wall Position jValue Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 120001 BON

-379 120101 2193 120201 7795 120301 15281 120401 23730 120501 31845 120601 BOW 32498 120701 29938 120801 24029 120901 21575 121001 17833 121101 16163 121201 15199 121301 12801 121401 TOW 10503 121501 2421 121601 4094 121701 3789 121801 3269 121901 2220 122001 1691 122101 1430 122201 1321 122301 1349 122401 1496 122501 1727 122601 1981 122701 2200 122801 2333 122901 2365 123001 2315 123101 2224 123201 TOH 2141 123301 TON 1 2106 18

A AREVA 32-9046889-002 Table 3. Steady State Hoop Stresses in 490 CRDM Nozzle "A' on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON =.Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 215T 3/5T 4/5T Outside of Nozzle 1

BON

-379 101 2193 201 7795 301 15281 401 23730 501 31845 601 BOW 32498 701 29938 801 24029 901 21575 1001 17833 1101 16163 1201 15199 1301 T2801 1401 TOW 10503 1501 2421 1601 4094 1701 3789 1801 3269 1901 2220 2001 1691 2101 1430 2201 1321 2301 1349 2401 1496 2501 1727 2601 1981 2701 2200 2801 2333 2901 2365 3001 2315 3101 2224 3201 TOH 2141 3301TON 2106 19

A AREVA 32-9046889-002 Table 4. Steady State Hoop Stresses in 490 CRDM Nozzle "A" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1)

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average fBtom Surface Wall Through-WaA Position Value Botom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 120001 BON

-5639 120101

-5987 120201

-1319 120301 6503 120401 14771 120501 31030 120601 BOW 42431 120701 53899 120801 54046 120901 55388 121001 54716 121101 53388 121201 50314 121301 46224 121401 TOW 39206 121501 29292 121601 19387 121701 8120 121801 4786 121901 1836 122001 1382 122101 1945 122201 2736 122301 3574 122401 4399 122501 5037 122601 5385 122701 5434 122801 5296 122901 5133 123001 5044 123101 5030 123201 TOH 5055 123301 A

TON 1 5064 t

20

Table 5. Axial Stresses Along the Circumference at the Bottom of the Weld in 49 deg. Nozzle "A" Source:

DEI [1]

Downhill Uphill Location-->

0 deg.

15 deg.

30 deg.

45deg.

60 deg.

75 deg.

90 deg.

105 deg. 120 deg. 135 deg. 150 deg. 165 deg.

180 deg.

Nodes -->

601 10601 20601 30601 40601 50601 60601 70601 80601 90601 100601 110601 120601 Thru Node 606 10606 20606 30606 40606 50606 60606 70606 80606 90606 100606 110606 120606 Thru-Wall Stresses (at time = 110004.) in psi.

Inside 1/5T 2/5T 3/5T 4/5T Outside Average =

2004

-480

-2241

-1270 1413 4195 7544 12140 17650 22616 27375 31362 32498 (b

0 ODOD C) 0, 0Q

A AREVA 32-9046889-002 4.7.2 Applied Stresses for Nozzle 49B Steady state axial and hoop stresses, on the downhill and the uphill sides of nozzle 49B are summarized in Tables 6 through 9 for the 48.70 penetration angle nozzle analyzed by DEI, as listed below. Stresses are provided for each node on the downhill and uphill sides of the nozzle, referenced to the inside surface nodal locations.

DEI Analysis Case Stress Summary Tables Nozzle Angle*

48.70 48.70 Yield Strenqth 45.0 ksi 45.0 ksi Type Axial Hoop Downhill Side 6

8 Uphill Side 7

9 Outermost nozzle Outermost nozzle

  • Relative to the center of the head.

The axial stresses from the DEI analysis, reported every 15 degrees in the circumferential direction from 0-degrees (downhill side) to 180-degrees (uphill side), are also summarized. The stresses are summarized for the bottom of the weld locations in Table 10.

The steady state stresses are reviewed to determine which region from the downhill to the uphill location is the most highly stressed location. From Table 10, the maximum axial stress for the bottom of the weld location occurs at 150 from the uphill side. From review of Tables 8 and 9, it is clear that the maximum hoop stress below the weld occurs at the uphill side.,

22

A AR EVA 32-9046889-002 Table 6. Steady State Axial Stresses in 490 CRDM Nozzle "B" on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 1

BON

-1512 101

-146 201 2648 301 6064 401 9193 501 11745 601 BOW 11375 701 9153 801

-5905 901

-19806 1001

-25063 1101

-18575 1201

-9942 1301

-219 1401 TOW 7191 1501 16798 1601 14401 1701 12482 1801 11698 1901 10276 2001 8659 2101 6572 2201 4794 2301 3473 2401 2721 2501 2295 2601 2003 2701 1268 2801 634 2901 2021 3001 1919 3101 2342 3201 TOH 2346 3301 TON 1 2228 23

A AREVA 32-9046889-002 Table 7. Steady State Axial Stresses in 490 CRDM Nozzle "B" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:.

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 120001 BON 396 120101 4201 120201 11658 120301 20136 120401 27782 120501 34250 120601 BOW 33871 120701 32299 120801 26702 120901 24202 121001 20459 121101 18520 121201 17303 121301 14090 121401 TOW 11219 121501 2807 121601 4524 121701 4068 121801 3645 121901 2584 122001 1943 122101 1617 122201 1446 122301 1441 122401 1566 122501 1778 122601 2011 122701 2209 122801 2324 122901 2345 123001 2293 123101 2209 123201 TOH 2135 123301 TON 2103 24

A A R EVA 32-9046889-002 Table 8. Steady State Hoop Stresses in 490 CRDM Nozzle "B" on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEl [1]

BOW = Bottom of Weld Penetration Angle:

48 7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 1

BON

-18683 101

-11138 201

-4834 301

-323 401 1555 501 6837 601 BOW 16711 701 33915 801 37139 901 31364 1001 22604 1101 23323 1201 28739 1301 32570 1401 TOW 35549 1501 41133 1601 37344 1701 30186 1801 26274 1901 23512 2001 20224 2101 16120 2201 12130 2301 9035 2401 6650 2501 4908 2601 3289 2701 2967 2801

-197 2901 3970 3001 5522 3101 5495 3201 TOH 5009 3301 TON 1 4986 25

AR AREVA 32-9046889-002 Table 9. Steady State Hoop Stresses in 490 CRDM Nozzle "B" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48..7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 215T 3/5T 4/5T Outside of Nozzle 120001 BON

-9500 120101

-4235 120201 785 120301 8560 120401 15976 120501 32476 120601 BOW 43430 120701 55274 120801 55388 120901 56176 121001 55469 121101 53734 121201 50899 121301 46108 121401 TOW 38258 121501 28888 121601 19160 121701 8078 121801 4587 121901 1227 122001 675 122101 1407 122201 2368 122301 3352 122401 4277 122501 4977 122601 5351 122701 5408 122801 5275 122901 5119 123001 5038 123101 5029 123201 TOH 5056 123301 TON 5068 26

Table 10. Axial Stresses Along the Circumference at the Bottom of the Weld in 49 deg. Nozzle "B" Source:

DEI [1]

Downhill Uphill Location-->

0 deg.

15 deg.

30 deg.

45 deg.

60 deg.

75 deg.

90 deg.

105 deg. 120 deg. 135 deg. 150 deg. 165 deg.

180 deg.

Nodes-->

601 10601 20601 30601 40601 50601 60601 70601 80601 90601 100601 110601 120601 Thru Node 606 10606 20606 30606 40606 50606 60606 70606 80606 90606 100606 110606 120606 Thru-Wall Stresses (at time = 110004.) in psi.

Inside 1/5T 2/5T 3/5T 4/5T Outside Average=

11375 5067

-2678

-3814

-480 3828 8357 13775 20136 25976 30673 34027 33871

-'4 m

(0 0)

ODo OD K) 02 023 ICD

A AREVA 32-9046889-002 4.7.3 Applied Stresses for Nozzle 49C Steady state axial and hoop stresses, on the downhill and the uphill sides of nozzle 49C are summarized in Tables 11 through 14 for the 48.70 penetration angle nozzle analyzed by DEI, as listed below. Stresses are provided for each node on the downhill and uphill sides of the nozzle, referenced to the inside surface nodal locations.

DEI Analysis Case Stress Summary Tables Nozzle An~qle*

48.70 48.70 Yield Type Downhill Strength Side 45.0 ksi Axial 11 45.0 ksi Hoop 13 Uphill Side 12 14 Outermost nozzle Outermost nozzle

  • Relative to the center of the head.

The axial stresses from the DEI analysis, reported every 15 degrees in the circumferential direction from 0-degrees (downhill side) to 180-degrees (uphill side), are also summarized. The stresses are summarized for the bottom of the weld locations in Table 15.

The steady state stresses are reviewed to determine which region from the downhill to the uphill location is the most highly stressed location. From Table 15, the maximum axial stress for the bottom of the weld location occurs at the uphill side. From review of Tables 13 and 14, it is clear that the maximum hoop stress below the weld occurs at the uphill side.

28

A AREVA 32-9046889-002 Table 11. Steady State Axial Stresses in 490 CRDM Nozzle "C" on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48 7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 1

BON A1740 101

-599 201 1850 301 4939 401 8052 501 0894 601 BOW 12287 701 15900 801 5008 901

-13558 1001

-30307 1101

-27806 1201

-19797 1301

-7262 1401 TOW 1967 1501 13180 1601 10869 1701 9294 1801 8860 1901 7756 2001 6310 2101 4559 2201 3104 2301 2086 2401 1624 2501 1492 2601 1480 2701 1095 2801 701 2901 2061 3001 2003 3101 2369 3201 TOH 2339 3301 TON 2224 29

A ARE VA 32-9046889-002 Table 12. Steady State Axial Stresses in 490 CRDM Nozzle "C" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48,7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45 0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 120001 BON 261 120101 4535 120201 12240 120301 20906 120401 28310 120501 34381 120601 BOW 33628 120701 32818 120801 27443 120901 25005 121001 21164 121101 19146 121201 17722 121301 14269 121401 TOW 11318 121501 2980 121601 4659 121701 4274 121801 3865 121901 2822 122001 2134 122101 1755 122201 1557 122301 1537 122401 1651 122501 1846 122601 2061 122701 2240 122801 2337 122901 2345 123001 2288 123101 2204 123201 TOH 2131 123301 A

TON 1 2102 30

A AREVA 32-9046889-002 Table 13. Steady State Hoop Stresses in 490 CRDM Nozzle "C" on Downhill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45.0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average OTom Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 1

BON

-23755 101

-15334 201

-11501 301

-10516 401

-8262 501

-4494 601 BOW 997 701 21826 801 32437 901 30945 1001 18655 1101 19369 1201 24974 1301 30838 1401 TOW 34334 1501 40862 1601 36937 1701 29898 1801 25842 1901 23106 2001 19830 2101 15850 2201 12054 2301 9131 2401 6866 2501 5225 2601 3628 2701 3306 2801 596 2901 4277 3001 5507 3101 5441 3201 TOH 5007 3301 TON 1 4989 31

A AR EVA 32-9046889-002 Table 14. Steady State Hoop Stresses in 490 CRDM Nozzle "C" on Uphill Side Plant:

Callaway BON = Bottom of Nozzle Source:

DEI [1]

BOW = Bottom of Weld Penetration Angle:

48.7 Degrees TOW = Top of Weld Shrink Fit:

None TOH = Top of Head Nozzle Yield:

45 0 ksi TON = Top of Nozzle Residual Plus Operating Stresses (Time 110004)

Distance Inside Average from Surface Wall Through-Wall Position Value Bottom Node Elevation Thickness Inside 1/5T 2/5T 3/5T 4/5T Outside of Nozzle 120001 BON

-11328 120101

-2053 120201 1437 120301 9223 120401 16953 120501 33705 120601 BOW 44149 120701 56064 120801 56103 120901 56633 121001 56001 121101 54277 121201 51502 121301 46462 121401 TOW 38527 121501 29339 121601 19488 121701 8351 121801 4747 121901 1293 122001 511 122101 1291 122201 2298 122301 3313 122401 4252 122501 4956 122601 5330 122701 5388 122801 5258 122901 5109 123001 5034 123101 5028 123201 TOH 5056 123301 TON 1 5071 32

Table 15. Axial Stresses Along the Circumference at the Bottom of the Weld in 49 deg. Nozzle "C" Source:

DEl III Downhill Uphill Location-->

0 deg.

15 deg.

30 deg.

45 deg.

60 deg.

75deg.

90 deg.

105 deg. 120 deg. 135deg. 150 deg. 165 deg.

180 deg.

Nodes -->

601 10601 20601 30601 40601 50601 60601 70601 80601 90601 100601 110601 120601 Thru Node 606 10606 20606 30606 40606 50606 60606 70606 80606 90606 100606 110606 120606 Thru-Wall Stresses (at time = 110004.) in psi.

Inside 1/5T 2/5T 3/5T 4/5T Outside Average=

12287 5060

-2124

-4414

-225 4840 9887.

15114 21188 27080 31557 34590 37252 C.,

C,)

OD 0

K3

-.11

-1 _,-_

A A R EVA 32-9046889-002 4.8 Acceptance Criteria The acceptance criteria for the postulated circumferential and axial through-wall flaws are provided in Table 1 (Reference 5). The acceptance criterion for postulated circumferential flaws below the weld is 75 percent of the circumference.

For hypothetical axial through-wall flaws located below the weld, there is no limit (i.e. the allowable flaw size is the full height of the nozzle below the weld).

34

A AR EVA 32-9046889-002 4.9 Flaw Evaluations Hypothetical flaw evaluations are performed for Callaway, to determine the maximum allowable beginning-of-life (BOL) through-wall flaw size, at various postulated flaw regions and for various heights of nozzles below the weld (represented by the three DEI finite element models discussed in Section 4.2), which would not reach critical flaw size considering a period of seven years between inspections.

Two types of through-wall flaws were considered in the outermost CRDM nozzle, as follows:

a)

Circumferential flaw located at the bottom of the J-groove weld (referred to as flaw #1a through #1c where "a" through "c" represent the three heights of the nozzles),

b)

Axial flaw or edge crack located at the bottom of the nozzle (referred to as flaw

  1. 2a through #2c where "a" through "c" represent the three heights of the nozzles).

Crack growths were predicted using the primary water stress corrosion crack growth model of Section 4.5, the applicable stress intensity factor solutions described in Sections 4.6.1 and 4.6.2, and the applied stresses provided in Section 4.7. Since through-wall flaws are considered in this evaluation, the average nozzle stresses are the applicable stresses.

4.9.1 Flaw Evaluation for Nozzle 49A For nozzle #49A (corresponding to DEI model 48.7A), the stress coefficients (A-coefficients) for the polynomial expressions in the SIF solutions for flaws #1a, #2a downhill side, and #2a uphill side are provided in Tables 16, 18, and 19, respectively. The flaw evaluations for the period of seven years between inspections are provided in Tables 17, 20, and 21, respectively for the above flaws.

35

A AREVA 32-9046889-002 Table 16. Axial Stresses Along the Circumference at the Bottom of the Weld in Nozzle 49A (Uphill Side)

STRESS INTENSITY FACTOR FOR CIRCUMFERENTIAL FLAW Basis:

Buchalet and Bamford solution for a through-wall crack in an infinite body [6]

KI = */(1*a)

(A0 + Ap) + (2alT)A 1 + (a2/2) A 2 + (4a3)/(37t) A3]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Alx + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Axial Stresses for, Crack Growth:

Wall Steady State Note: x is measured from the Position Stresses center of the flawed surface.

x SS (in.)

(ksi) 0.00000 32.498 0.44179 31.362 0.88357 27.375 1.32536 22.616 1.76715 17.650 2.20893 12.140 2.65072 7.544 3.09251 4.195 3.53429 1.413 3.97608

-1.270 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

A0 32.942535 A1

-3.227399 A2

-4.417400 A3 0.778762 36

A AR EVA 32-9046889-002 Table 17. Circumferential Growth of Flaw #1a in Nozzle 49A (Bottom of Weld, Uphill Side) for 7 years Circumferential Flaw Growth for a Through-wall Crack in an Infinite Body Stress intensity factor' KI = 4(7*a) * [ (Ao + Ap) + (2a/ir)A 1 + (a2/2) A2 + (4a 3)/(37c) A3 ]

where a = flaw length S(x) = Ao + Alx + A2x2 + A3x3.

Ap= I

] ksi (pressure on crack face)

Flaw growth:

Aa= [C. (1.17xlO10)

(K,- 8.19)1 16 in./sec. ] At Co =

I Additional parameters:

At Initial time =

R=

Flaw length (a) =

Crack length (2a) =

as a % of circumference =

15768000 sec.,

0.00 years

] in. (mean radius)

] in. (mean circumference) in.

in.

67.7 Flaw Growth Calculations:

Percent Time a

K, Aa of Circ.

(years)

(in.)

(ksi)

(ksiqin)

(in.)

(%)

000 14.725 49.45 0.02922 67.7 050 14.576 49.15 0..02897 68.3 1,00 14.431 48.85 0.02873 68.8 1.50 14.289 48.56 0.02849 69.4 2,00 14.151 48.28 0.02826 69.9 2.50 14.016 4800 0.02803 70.4 3..00 13.885 47.73 0.02781 71.0 3.50 13.757 47.47 0.02760 71.5 4.00 13.632 47.21 0.02739 72.0 4.50 13.511 46.96 0.02718 72.5 5.00 13.393 46.71 0.02698 73.0 5.50 13.279 46.47 0.02679 73.5 6,00 13,167 46.24 0,,02660 74.0 6,50 13 059 46.01 0.02642 74.5 7.00 12,954 45.80 0.02624 75.0 37

Ak1A AREVA 32-9046889-002 Table 18. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49A (Downhill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1.12s/(lr*a) * [ (k + Ap) + (2a/h)AI + (a'/2) A2 + (4a')/(37t) A3 where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Aix + A2x2 + A3x3 and Ap = pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Position x

(in.)

0.00000 0..62400 1.12400 1-52500 184600 2.10300 2.30900 Steady State Stresses SS (ksi)

-11.953

-7.506

-2.518 6.425 14.683 22.700 39.193 Steady State Stresses SS (ksi)

-12.164 12.644

-10,465 6.192 Note.: x is measured from the bottom of the nozzle.

Stress Coefficients:

Stress Coeff A0 A1 A2 A3 38

AREVA 32-9046889-002 Table 19. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49A (Uphill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1.12"(7r*a) * (A0 + Ap) + (2a/h)A 1 + (a2/2) A2 + (4a3)/(3n) A3 where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Alx + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Position x

(in.)

0.00000 2.00200 3.60600 4M8100 5.92100 6.74600 7.40600 Steady State Stresses SS (ksi)

-5..639

-5,987

-1.319 6.503 14.771 31,030 42.431 Note: x is measured from the bottom of the nozzle..

Stress Coefficients::

Stress

Coeff, A0 A1 A2 A3 Steady State Stresses SS (ksi)

-5.767 0.343

-0.415 0.169 39

A ARE VA 32-9046889-002 Table 20. Axial Growth of Flaw #2a in Nozzle 49A (Bottom of Nozzle, Downhill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edge Crack)

Stress intensity factor:

KI = 1.124I(i*a) * [ (Ao + Ap) + (2a/h)AI + (a2/2) A2 + (4a 3)/(37t) A3 ]

where a = flaw length S(x)= AO + Ax + A2x2 + A3x3.,

Ap = [

] ksi (pressure on crack face)

Aa= [C (1 17x10"'0) (K,- 8.19)'

in./sec. ] At Co= [

Flaw growth!!

Additional parameters.:

At = 15768000 sec.

Initial time =

0.00 years Flaw length (a) = [

] in.

height = [

] in. (height of nozzle below weld) as a % of the height =

91.3 minimum inspection height =

0.200 in. (downhill side)

Flaw Growth Calculations:

Percent Time a

K, Aa of Height (years)

(in.)

(ksi)

(ksiiin)

(in.)

(%)

0.00 17.162 49.48 0.02924 91 3 0.50 17.545 50,93 0.03044 926 1.00 17.944 52.46 0.03170 939 1.50 18360 54.06 0.03304 953 2.,00 18.793 5575 0.03446 967 2.50 19.245 57.53 0.03596 982 3.00 19.716 59.,41 0.03755 998 3.50 20.207 61.38 0.03923 101.4 4.00 20.718 63.46 0.04101 103.1 4.50 21.250 65.65 0,04290 104.9 5.00 21.805 67.95 0.04491 106.7 5,50 22.381 70.38 0,04703 108.7 6.00 22.981 72.94 0.04929 110.7 6.50 23.603 75.64 0.05167 112.9 7.00 24.248 78.47 0.05420 115.1 40

A AR EVA 32-9046889-002 Table 21. Axial Growth of Flaw #2a in Nozzle 49A (Bottom of Nozzle, Uphill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edgqe Crack)

Stress intensity factor:

KI = 1. 124 (T*a) * [ (Ao + Ap) + (2a/i)A 1 + (a2/2) A2 + (4a')I(3iT) A3 ]

where a = flaw length S(x) = Ao + Alx + A2x2 + A3x3.

AP = [

] ksi (pressure on crack face)

Aa =[Co (1. 17.10-"°) (K, - B. 19)' "6 in./sec. I At C. =

I Flaw growth:

Additional parameters:

At = 15768000 sec.

Initial time =

0.00 years Flaw length (a) = [

in.

height = []

in. (height of nozzle below weld) as a % of the height =

  1. DIV/0!

minimum inspection height =

-6.775 in, (uphill side)

Flaw Growth Calculations:

Percent Time a

K, Aa of Height (years)

(in.)

(ksi)

(ksiJin)

(in.)

(%)

0.00 10.847 56.05 0,.03471 91.5 0.50 11.102 57.51 0,03594 91.9 1.00 11.369 59.05

  • 0.03724 92.4 1.50 11.649 60.67 0.03862 92.9 2.00 11 943 62.38 0.04008 93,5 2.50 12,253 64.18 0.04163 94.0 3100 12578 66..08 0,04328 94.6 3.50 12.922 68.,09 0..04503 95.1 4,,00 13.284 70.23 0..04690 95.8 4.50 13.667 72.49 0.04889 96.4 5.00 14,073 74.90 0.05102 97.0 5.50 14.503 77.46 0.05330 97 7 6.00 14.960 80.19 0.05574 98.5 6..50 15.446 83.12 0.05838 99,2 7.00 15.965 86.25 0.06122 100.0 41

A ARE EVA 32-9046889-002 4.9.2 Flaw Evaluation for Nozzle 49B For nozzle #49B (corresponding to DEI model 48.7B), the stress coefficients (A-coefficients) for the polynomial expressions in the SIF solutions for flaws #1b, #2b downhill side, and #2b uphill side are provided in Tables 22, 24, and 25, respectively. The flaw evaluations for the period of seven years between inspections are provided in Tables 23, 26, and 27, respectively for the above flaws.

42

A AREVA 32-9046889-002 Table 22. Axial Stresses Along the Circumference at the Bottom of the Weld in Nozzle 498 (Uphill Side)

STRESS INTENSITY FACTOR FOR CIRCUMFERENTIAL FLAW Basis:

Buchalet and Bamford solution for a through-wall crack in an infinite body [6]

KI = *N(t*a)

[(Ao + Ap) + (2a/7)A1 + (a2/2) A2 + (4a3)/(3,,) A3]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + A1x + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Axial Stresses for Crack Growth:

Wall Position x

(in.)

0.00000 0.44179 0.88357 1.32536 1.76715 2.20893 2.65072 3.09251 3.53429 3.97608 Steady State Stresses SS (ksi) 33,871 34.027 30.673 25.976 20.136 13.775 8.,357 3.828

-0.480

-3.814 Note: x is measured from the center of the flawed surface.

Stress Coefficients:

Stress Coeff.

A0 A1 A2 Steady State Stresses SS (ksi) 34.316467 0.735853

-6.711455 A3 1.041654 43

A AREVA 32-9046889-002 Table 23. Circumferential Growth of Flaw #1b in Nozzle 49B (Bottom of Weld, Uphill Side) for 7 years Circumferential Flaw Growth for a Through-wall Crack in an Infinite Body Stress intensity factor:

KI = 4(7*a) * [ (Ao + Ap) + (2ah/)A 1 + (a2/2) A2 + (4a 3)/(31r) A3 ]

where a = flaw length S(x) = Ao + Alx + A2x2 + A3x 3, AP=[

] ksi (pressure on crack face)

Flaw growth:

Aa= [Co (1.17x10-)

(KI - 8..19) 1 6 in./sec. ] At Additional parameters:

At =

Initial time =

R=

Flaw length (a) =

Crack length (2a) =

as a % of circumference =

15768000 sec.

0M00 years

] in. (mean radius)

] in (mean circumference)

]in in 67.2 Flaw Growth Calculations Percent Time a

K, Aa of Circ.

(years)

(in.)

(ksi)

(ksi'/in)

(in.)

(%)

0,00 15.700 5254 0.03178 67.2 0.50 15.492 52.08 0.03139 67..8 1,00 15.289 51.62 0.03101 68.4 1.50 15.091 51.17 0.03063 69.0 2.00 14.899 50.72 0.03027 69.6 250 14.711 50.29 0.02991 70.2 3,00 14.529 49.87 0.02956 70.7 3.50 14.351 49,45 0.02922 71.3 400 14,179 4905 0.02889 71.8 450 14.011 4865 0.02856 72,,4 5.00 13.848 4826 0.02825 72..9 5.50 13.690 47,89 0.02794 73.5 6.00 13.536 47.52 0.02764 74.0 6.50 13.387 47.16 0.02735 74.5 7.00 13.242 46.81 0.02706 75.0 44

A AREVA 32-9046889-002 Table 24. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49B (Downhill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1.1 2I7t(*a) * [ (A0 + Ap) + (2a/h)A 1 + (a2/2) A2 + (4a3)/(37t) A3]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Ajx + A2x2 + A3 x,3.

and Ap = pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Steady State Note: x is measured from Position Stresses the bottom of the nozzle.

x SS (in.)

(ksi) 0.00000

-18683 0.38400

-11138 0.69100

-4.834 0.93800

-0.323 1.13500 1.555 1.29300 6.837 1.42000 16.711 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

A0

-19.048 A1 36.929 A2

-41.623 A3 22.962 45

A AREVA 32-9046889-002 Table 25. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49B (Uphill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1 12ý(7r*a) * [(A0 + Ap) + (2a/h)A 1 + (a2/2) A2 + (4a3)/(37E) A3]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Ajx + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Steady State Note: x is measured from Position Stresses the bottom of the nozzle.

x SS (in.)

(ksi) 0.00000

-9.500 2.00200

-4.235 3,60600 0.785 4.89100 8.560 5.92100 15.976 6.74600 32.476 7.40600 43.430 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

A0

-9.585 A1 4.662 A2

-1.353 A3 0.229 46

A AREVA 32-9046889-002 Table 26. Axial Growth of Flaw #2b in Nozzle 49B (Bottom of Nozzle, Downhill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edge Crack)

Stress intensity factor:

KI = 1 12 /(e*a) * [ (Ao + A,) + (2a/h)A 1 + (a 2/2) A2 + (4a')/(37T) A3 ]

where a = flaw length S(x) = Ao + A1 x + A2X2 + A3X3, Ap = I

] ksi (pressure on crack face)

Flaw growth.

Aa =C, (1.1 7xl 010 ) (K, - 8.19)-16 in./sec.. ] At co)=

I Additional parameters:

At =

Initial time =

Flaw length (a) = [

height = [

as a % of the height =

minimum inspection height =

15768000 sec..

0.00 years

]in.

in. (height of nozzle below weld) 100.0 0.000 in, (downhill side)

Flaw Growth Calculations Percent Time a

a K,

Aa of Height (years)

(in.)

(ksi)

(ksi/in)

(in.)

(%)

0.00 2.608 6.17 0.00000 100.0 0..50 2.608 6.17 0.00000 100.0 1.00 2608 6.17 0,00000 100.0 11.50 2,608 6.17 0.00000 100.0 2.00 2.608 6.17 0,00000 100.0 2.50 2.608 6.17 0,00000 100.0 3.00 2.608 6.17 0.00000 100.0 3.50 2.608 6,17 0.00000 100.0 4.00 2.608 6.17 0.00000 100.0 4.50 2.608 6.17 0..00000 100.0 5.00 2.608 6.17 0.00000 100.0 5.50 2.608 6.17 0.00000 100,0 6.00 2608 6.17 0.00000 100.0 6.,50 2608 6.17 0.00000 100.0 7.00 2.608 6.17 0.00000 100.0 47

A ARE EVA 32-9046889-002 Table 27. Axial Growth of Flaw #2b in Nozzle 49B (Bottom of Nozzle, Uphill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edge Crack)

Stress intensity factor:

KI = 1.1 2s/(n*a) * [ (Ao + Ap) + (2alir)A 1 + (a 2/2) A2 + (4a )/(3rr) A3 ]

where a = flaw length S(x) = Ao + Ajx + A2x2 + A3x'.

Ap= I

] ksi (pressure on crack face)

Flaw growth:

Aa = [ C, (1.17x10-")) (K, - 8.19)11' in./sec. ] At C =[

I Additional parameters!

At= 15768000 Initial time =

0.00 Flaw length (a) =

height =

as a % of the height =

90.7 minimum inspection height =

0.690 sec.

years

]in.

in. (height of nozzle below weld) in. (uphill side)

Flaw Growth Calculations Percent Time a

K, Aa of Height (years)

(in.)

(ksi)

(ksi-4in)

(in.)

M%

0.00 11.659 59.98 0.03803 90.7 0..50 11.929 61.54 0.03937 91.2 1..00 12.212 63.19 0.04078 91.7 1,50 12.510 64.92 0.04228 92.3 200 12.824 66.76 0.04387 92..8 250 13.155 68.70 0.04556 93.4 300 13.503 70.75 0.04735 94.1 350 13.872 72,93 0..04927 94.7 4..00 14.261 75.24 0.05132 954 4.50 14.675 77.70 0.05351 96.1 5.00 15.113 80.32 0.05586 96.8 5.50 15.580 83.12 0.05838 97..5 6.00 16.077 86.12 0.06110 98.3 6,.50 16.608 89.34 0.06404 99.1 7.00 17.176 92.80 0.06721 100.0 48

A ARE VA 32-9046889-002 4.9.3 Flaw Evaluation for Nozzle 49C For nozzle #43C (corresponding to DEI model 48.7C), the stress coefficients (A-coefficients) for the polynomial expressions in the SIF solutions for flaws #1c, #2c downhill side, and #2c uphill side are provided in Tables 28, 30, and 31, respectively. The flaw evaluations for the period of seven years between inspections are provided in Tables 29, 32, and 33, respectively for the above flaws.

49

A AREVA 32-9046889-002 Table 28. Axial Stresses Along the Circumference at the Bottom of the Weld in Nozzle 49C (Uphill Side)

STRESS INTENSITY FACTOR FOR CIRCUMFERENTIAL FLAW Basis:

Buchalet and Bamford solution for a through-wall crack in an infinite body [6]

KI = /(1*a) [(A0 + Ap) + (2a/r)A1 + (a2/2) A2 + (4a )/(3n) A3 1 where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Ajx + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Axial Stresses for Crack Growth:

Wall Steady State Note: x is measured from the Position Stresses center of the flawed surface.

x SS (in.)

(ksi) 0.00000 37.252 0'44179 34..590 0.88357 31..557 1.32536 27.080 1.76715 21.188 2.20893 15.114 2.65072 9.887 3.09251 4.840 3.53429

-0225 3.97608

-4.414 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

A0 37.197805 A1

-3.404710 A2

-4.259170 A3 0.627088 50

A AREVA 32-9046889-002 Table 29. Circumferential Growth of Flaw #1c in Nozzle 49C (Bottom of Weld, Uphill Side) for 7 years Circumferential Flaw Growth for a Through-wall Crack in an Infinite Body Stress intensity factor:

KI = 4/(m*a) * [ (Ao + Ap) + (2a/h )A1 + (a2/2) A2 + (4a 3)/(37r) A3 I where a = flaw length 2 +3 S(x) =A + Ajx+ A2x + A3X.

AP= [

] ksi (pressure on crack face)

Flaw growth:

Aa = [ C, (1.17x10-10) (K - 8,.19)116 in./sec.. ] At C =[

I Additional parameters:

At = 15768000 sec.

Initial time =

0.00 years R =[

]in. (mean radius) c = [

]in. (mean circumference)

Flaw length (a) = [

]in.

Crack length (2a) = [

] in..

as a % of circumference =

66..4 Flaw Growth Calculations Percent Time a

K, Aa of Circ.

(years)

(in.)

(ksi)

(ksi'in)

(in.)

(%)

0.00 17.107 56.90 0.03543 66.4 0.50 16..850 56.33 0.03495 67.1 100 16.599 55.76 0.03447 67..8 1.50 16.353 55.20 0.03399 68.4 2.00 16.112 54.64 0.03353 69.1 2.50 15.877 54.09 0.03306 69.7 3.00 15.646 53.54 0.03261 70.3 3,50 15.420 53.00 0.03215 70.9 4.00 15.199 52.46 0.03171 71.5 4.50 14.983 51.93 0.03127 72.1 5.00 14.772 51.41 0,03084 72.7 5.50 14..566 50.89 0..03041 73.3 6.00 14.364 50.39 0,02999 73.9 6.50 14,167 49.88 0..02958 74.4 7.00 1

13.975 49.39 0.02917 75.0 51

A A R EVA 32-9046889-002 Table 30. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49C (Downhill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1.1 2(,/(*a) * [ (A0 + Ap) + (2a/h)A 1 + (a2/2) A2 + (4a3 )/(37i) A3 ]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Ajx + A2x2 + A3x3.

and Ap = pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Steady State Note: x is measured from Position Stresses the bottom of the nozzle..

x SS (in.)

(ksi) 0.00000

-231755 0.21700

-15.334 0.39100

-11.501 0.53100

-10.516 0.64300

-8.262 0.73200

-4.494 0.80400 0.997 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

A0

-23.908 A1 69.787 A2

-153,353 A3 129.906 52

A AREVA 32-9046889-002 Table 31. Hoop Stresses from Bottom of Nozzle to Bottom of Weld in Nozzle 49C (Uphill Side)

STRESS INTENSITY FACTOR FOR EDGE CRACK Basis:

Buchalet and Bamford solution for continuous surface crack in semi-infinite body [6]

KI = 1.124/(-*a) * [ (A0 + Ap) + (2a/t)A1 + (a2/2) A2 + (4a3)/(37c) A3]

where the through-wall stress distribution is described by the third order polynomial, S(x) = A0 + Ajx + A2x2 + A3x 3..

and Ap

= pressure on the crack face Through-Wall Hoop Stresses for Crack Growth:

Wall Steady State Note: x is measured from Position Stresses the bottom of the nozzle.

x SS (in.)

(ksi) 0..00000

-11.328 2.00200

-2.053 3160600 1.437 489100 9223 5,92100 16.953 6.74600 33.705 7.40600 44.149 Stress Coefficients:

Steady State Stress Stresses Coeff.

SS (ksi)

Ao

-11.250 A1 7.511 A2

-2.108 A3 0.286 53

A AR EVA 32-9046889-002 Table 32. Axial Growth of Flaw #2c in Nozzle 49C (Bottom of Nozzle, Downhill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edgqe Crack)

Stress intensity factor:

KI = 1.12*/(i*a) * [ (Ao + Ap) + (2aht)A1 + (a 2/2) A2 + (4a 3)/(37[) A3 ]

where a = flaw length S(x) = A0 + A1 x + A2x 2 + A3x3.

AP = I

] ksi (pressure on crack face)

Flaw growth:

Aa = [ CO(1. 17xl010') (K, -8.19)'-' 6in./sec.,]I t CO = [

I Additional parameters:,

At = 15768000 sec.

Initial time =

0.00 years Flaw length (a) = [

] in.

height = [

] in. (height of nozzle below weld) as a % of the height =

100.0 minimum inspection height =

0.000 in. (downhill side)

Flaw Growth Calculations Percent Time a

a K,

Aa of Height (years)

(in.

-(ksi)

(ks 0in0 (in.)

(%)

0.00

-6.767

-12.04 0.00000 100.0 0ý50

-6.767

-12.04 0.00000 100.0 1.00

-6.767

-12.04 0.00000 100.0 1.50

-6.767

-12.04 0.00000 100.0 2.00

-6.767

-12.04 0.00000 100.0 2.50

-6.767

-12.04 0.00000 100.0 3.00

-6.767

-12.04 0.00000 100,0 3.50

-6.767

-12..04 0.00000 100.0 4.00

-6.767

-12..04 0.00000 100 0 4,50

-6.767

-12.04 0.00000 100.0 5.50

-6.767

-12.04 0.00000 100.0 5.50

-6.767

-12.,04 0.00000 100.0 6.00

-6.767

-12.04 0.00000 100.0 6.50

-6.767

-12.04 0.00000 100.0 7.00

-6.767

-12.04 0.00000 100.0 54

A AR EVA 32-9046889-002 Table 33. Axial Growth of Flaw #2c in Nozzle 49C (Bottom of Nozzle, Uphill Side) for 7 years Axial Flaw Growth for a Continuous Surface Crack in a Semi-Infinite Body (Edge Crack)

Stress intensity factor:

KI = 1.1 217c(*a) * [ (Ao + Ap) + (2a/T)A 1 + (a2/2) A2 + (4a3)/(3it) A3 ]

where a = flaw length S(x) = Ao + Ajx + A2x2 + A3x3.

AP = [

] ksi (pressure on crack face)

Aa=[ C (1.17x10l') (K, - 8.19)1 " in./sec, ] At C" =

I Flaw growth:

Additional parameters&:

At =

Initial time =

Flaw length (a) =

height =

as a % of the height =

minimum inspection height =

15768000 sec.

0.00 years

]in.,

in (height of nozzle below weld) in, (uphill side) 90.1 0.731 Flaw Growth Calculations Percent Time a

K, Aa of Height (years)

(in.)

(ksi)

(ksi1in)

(in.)

(%)

0.00 12,188 62.51 0.04020 90.1 0.50 12.470 64.15 0.04161 90.7 1,00 12,767 65.88 0.04310 91,2 1M50 13.079 67.70 0.04469 91,8 2.,00 13.409 69.64 0.04638 92.4 2.50 13.757 71.69 0.04818 93.0 3.00 14.125 73.86 0.05010 93.7 3.50 14.515 76.18 0.05215 94.4 4.00 14.929 78.64 0.05435 95.1 4.50 15.370 81.28 0.05672 95,8 5.00 15,.839 84.09 0.05926 96..6 5.50 16.340 87.11 0.06200 97.4 6.00 16.876 90.35 0.06497 98..2 6.50 17.451 93.85 0.06818 99.1 7.00 18.069 97.62 0.07168 100.0 55

A A R E VA 32-9046889-002 4.10 Required Vertical Interface (Contact Area) Between Nozzle and Weld As a result of a potential for lack of weld fusion, the full contact height of the weld may not be present. This Appendix addresses the required contact height of the weld at the CRDM nozzle-to-weld interface region. The ASME Code criterion of limiting the shear stress to 0.6 Sm as defined by paragraph NB-3227.2 of the ASME Code (Reference 4) is utilized. The external applied load is primarily due to design pressure. The calculations are given below:

p =

[

]

(Reference 8)

Ro=

Sm 23300 psi Shear load:

Fs =

p7ERo 2

= 31414 lbs Stress criterion:

Fs/A = 0.6Sm

= 13980 psi Contact area, A = (27cRo)H in.2 Required weld height, H = Fs / (2nRo) / (0.6Sm)

= 0.1788 in.

(use 0.25 in.)

During upset and emergency conditions peak pressure value as high as [

] is also acceptable. Therefore, the required height of the weld (all the way around the circumference) at the CRDM nozzle-to-weld interface is 0.25 inches.

56

A AREVA 32-9046889-002 5.0 RESULTS,

SUMMARY

ICONCLUSION Flaw evaluations have been performed for the hypothetical flaws in the outermost CRDM nozzle of Callaway reactor vessel closure head (RVCH) nozzle penetrations 74 through 78. This evaluation is limited to the portions of the CRDM nozzles from the bottom of the nozzle to the bottom of the attachment weld. Flaw growth was calculated considering primary water stress corrosion cracking. The maximum allowable BOL flaws were determined considering the flaw acceptance criteria given in Section 4.8. The evaluations were performed for a period of seven years between inspections.

5.1 Minimum Inspection Height for Axial Flaws The required minimum inspection heights for the downhill and uphill sides for the "as-designed" CRDM nozzle 49A, and the "as-built" fillet welded nozzles 49B and 49C, are summarized in Table 34 with an illustration in Figure 4.

Table 34. Summary of Minimum Inspection Heights for Axial Flaws Below the Weld Length of Minimum Inspection Nozzle Nozzle Height Fillet Weld Below Design1 Weld Downhill Uphill (inch)

(inch)

(inch) 49A r

0.200 0.631 49B 0.000 0.690 49C 0.000 0.731 Considering As-Designed and As-Built fillet weld sizes (see Figure 2 and Figure 3) 57

A AREVA 32-9046889-002 Figure 4. Schematic Showing the Required "Minimum Inspection Band "from Downhill to Uphill Side 58

A AR EVA 32-9046889-002 5.2 Circumferential Below the Weld Through-Wall Flaws The maximum allowable circumferential below the weld through-wall flaws for the "as-designed" CRDM nozzle 49A, and the "as-built" fillet welded nozzles 49B and 49C, are summarized in Table 35 below.

Table 35. Summary of Circumferential Below Weld Through-Wall Flaws Nozzle Fillet Weld Length of Nozzle Design1 Below Weld (inch)

Maximum Allowable Flaw Size 49A 67.7% of circumference 49B 67.2% of circumference 49C 66.4% of circumference Considering as-Designed and as-Built fillet weld sizes (see Figure 2 and Figure 3) 59

A AREVA 32-9046889-002 ARE VA 32-9046889-002

6.0 REFERENCES

1. AREVA NP Document 32-9045848-000, "Transmittal of DEI Caic. C-4181-00-01, Rev. 1, "Callaway Upper Head CRDM Nozzle Welding Residual Stress Analysis," March 2007.
2. AREVA NP Document 51-9043028-000, "RPV Head Penetration Inspection Plan and Coverage Assessment for'AmerenUE Callaway Plant," February 2007.
3.
  • Combustion Engineering Drawing No. 11173-112-002, Rev 03, "Control Rod Mechanism Housing Details
4. ASME Boiler and Pressure Vessel Code,Section III, 1971 Edition including Addenda through Winter of 1972.
5. NRC Letter from Richard Barrett, Director Division of Engineering, Office of NRR to Alex Marion of Nuclear Energy Institute, "Flaw Evaluation Guidelines," April 11, 2003, Accession Number ML030980322.
6. Attachment 2 to Reference 5, "Enclosure 2 Appendix A: Evaluation of Flaws in PWR Reactor Vessel Upper Head Penetration Nozzles," April 11, 2003, Accession Number ML030980333.
7. Buchalet, C. B. and Bamford, W.H., "Stress Intensity Factor Solutions for Continuous Surface Flaws in Reactor Pressure Vessels," Mechanics of Crack Growth, ASTM STP 590, American Society of Testing and Materials, 1976, pp. 385-402.
8. AREVA NP Document 38-9046724-000, "Transmittal of Input Doc. NET 07-0056 from AmerenUE for RVCH Flaw Evaluation," March 2007.
  • Reference 3 is not retrievable from the AREVA NP document control system but is referenced here in accordance with AREVA NP Procedure 0402-01, Appendix 2.

W. A. Thomas Project Manager 7.0 COMPUTER OUTPUT There is no computer output associated with this document.

60

Retrieved from "https://kanterella.com/w/index.php?title=ML071490278&oldid=5346160"