ML14301A255
| ML14301A255 | |
| Person / Time | |
|---|---|
| Site: | Palisades, 07201007  |
| Issue date: | 10/24/2014 |
| From: | EnergySolutions |
| To: | Office of Nuclear Material Safety and Safeguards |
| References | |
| ES/NRC 14-018, TAC L24694 2007-20168, Rev. 00 | |
| Download: ML14301A255 (47) | |
Text
ES/NRC 14-018 October 24, 2014 Sargent and Lundy Calculation No. 2007-20168, Revision 00, Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 (1 paper copy)
CALCULATION FORMAT TEMPLATE GEG-0402-02, Revision 0 ISSUE
SUMMARY
Form SOP-0402-03 DESIGN CONTROL
SUMMARY
CUENT:
Entergy UNIT NO.:
N/A Page No.
I PROJECT NAME:
Palisades PROJECT NO.:
12122-035
[
NUCLEAR SAFETY-RELATED QA SERIAL CALC. NO.:
2007 - 20168 0
NOT NUCLEAR SAFETY-RELATED NO.
TITLE:
Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 EQUIPMENT NO.:
Spent Fuel Cask MSB No. 4, Model No. VSC-24 IDENTIFICATION OF PAGES ADDED/REVISED/SUPERSEDEDNOIDED & REVIEW METHOD INPUTS/ ASSUMPTIONS
[
VERIFIED UNVERIFIED REVIEW METHOD:
Independent Review
- REV, 0
STATUS:
DATE FOR REV.:
PREPARER A. Reiter C
DATE:
la/0/,3 D
REVIEWER I P. Hoang 4
h Z
DATE:
a/ 0 Z62..oc c APPROVER A. Dermenjian DATE:
IDENTIFICATION OF PAGES ADDED/REVISED/SUPERSEDED/VOIDED & REVIEW METHOD INPUTS/ASSUMPTIONS o
VERIFIED o
UNVERIFIED REVIEW METHOD:
REV.
STATUS:
DATE FOR REV.:
PREPARER DATE:
REVIEWER*
DATE:
APPROVER DATE:
IDENTIFICATION OF PAGES ADDED/REVISED/SUPERSEDEDNOIDED & REVIEW METHOD INPUTS/ASSUMPTIONS ol VERIFIED O
UNVERIFIED REVIEW METHOD:
REV.
STATUS:
DATE FOR REV.:
PREPARER DATE:
REVIEWER*
DATE:
APPROVER DATE:
I The reviewer's signature Indicates compliance with S&L procedure SOP-0402 and the verification of, as a minimum, the following items: correctness of mathematics for manual calculations, appropriateness of Input data, appropriateness of assumptions, and appropriateness of the calculation method.
NOTE: PRINT AND SIGN IN THE SIGNATURE AREAS EG0402-02.DOC Rev. Date: 06-18-2004 Page 1 of 33
Client Entergy Prepared by A. Reiter Date Project Palisades Reviewed by P. Hoang
{
(s
/ £ Date 12-CG..
Project No.
12122 - 035 Approved by A. Dermenjian Date TABLE OF CONTENTS
- 1.
PURPOSE..............................................................................................................................................
3
- 2.
DESIGN INPUTS....................................................................................................................................
4
- 3.
ASSUM PTIONS....................................................................................................................................
12
- 4.
ACCEPTANCE CRITERIA....................................................................................................................
12
- 5.
M ETHODOLOGY..................................................................................................................................
15
- 6.
CALCULATIONS...................................................................................................................................
18
- 7.
CONCLUSIONS...................................................................................................................................
31
- 8.
REFERENCES......................................................................................................................................
32
- 9.
ATTACHM ENTS...................................................................................................................................
33 EG0402-02.DOC Rev. Date: 06-18-2004 Page 2 of 33
Client Entergy Prepared by A. Reiter Q,
1 Date ;
Project Palisades Reviewed by P. Hoang Date Project No.
12122 - 035 Approved by A. Dermenjian Date
- 1.
PURPOSE 1.1 PURPOSE Evaluation of flaws in the longitudinal weld in Spent Fuel Cask MSB 004, Calculation EA-FC-864-50, was reviewed by the NRC staff. A Request for Additional Information (See Attachment E) was issued regarding to the parameter R value of 0.9 used in the fatigue crack growth rule, where the parameter R is the ratio of minimum stress and the maximum stress of the fatigue stress range.
By conservatively assuming a uniform welding residual stress of 54 ksi (base material yield stress), the parameter R for stress in the MSB longitudinal is in the range of 0.9 < R < 1. A value of R =1 would yield a higher fatigue crack growth rate than the crack growth rate in calculation EA-FC-864-50.
The purpose of this calculation is to reassess the calculation in EA-FC-864-50 to determine the flaw size at the end of 50-year life using the R value of 1.0.
EG0402-02.DOC Rev. Date: 06-18-2004 Page 3 of 33
.,Calcm.
For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007 - 20168 Iu
,Rev.
00 Date:
12/04/07 X J Safety-Related Non-Safety Related Page 4
of 33 Client Entergy Project Palisades Project No.
12122-035 Preparedby A. Reiter Date
/v/o Reviewed by P. Hoang Date Approved by A. Dermenjian Date
- 2.
DESIGN INPUTS 2.1 The postulated flaw is defined using a conservative interpretation of the MSB 004 indications. The characterization of the flaw for use in the flaw propagation analysis is defined in Section 2.2. The fatigue crack growth is calculated based on the fatigue load cases identified in the Safety Analysis Report, Reference 8.1. These load cases include the pressure test, vacuum drying, daily ambient temperature changes and the off-normal ambient temperature extremes. The effects of the daily changes in ambient temperature are defined using the thermal analysis results of Reference 8.1.
For each of these load cases, the membrane and bending stresses for the pressure and temperature loads are calculated in Sections 2.3 and 2.4 respectively.
2.2 Flaw Model for Analysis Reference 8.3 describes and characterizes the three indications found in the longitudinal weld of MSB 004. This reference concludes that the largest flaw is a subsurface flaw measuring 3/4" in length, along the MSB center line, and 3/16" in depth along the MSB radial direction. This flaw is located at the center of the shell thickness 52' from the top of the MSB. The other two indications are smaller in length and depth and meet the separation requirements of Reference 8.2, therefore, the evaluation of the largest flaw will envelope these indications. Since this evaluation assumes the largest MSB shell stress is acting at the postulated flaw and perpendicular to the flaw plane, the orientation of the other indications is in Reference 8.3 would permit a smaller subsurface flaw to be evaluated, this evaluation will assume a very conservative flaw model. The flaw is assumed to be an axial semi-elliptical surface flaw on the inside surface of the MSB. It is assumed to be 1" in length and 0.5 in epn.
2.3 Pressure Stress Cycles Each subsection below defines the membrane and bending stress due to pressure for the defined loading events. These stresses are determined from the results reported in References 8.1.
These results did not define the location or orientation of the maximum stress values, therefore this evaluation assumes the maximum reported stress is acting at the postulated flaw and is oriented perpendicular to the postulated flaw plane.
2.3.1 Pressure Test Events:
Maximum stresses in the MSB shell during the hydrostatic pressure test at 7 psi are (Section 3.4.4.1.7 of Reference 8.1):
Om=
1.2 Ksi Ub= 8.4-1.2Ksi 0 b = 7.2Ksi Two cycles of pressure test were assumed in Reference 8.1.
EG0402-02.DOC Rev. Date: 06-18-2004 Page 4 of 33
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Safety-Related I
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L[Client Entergy Project Palisades Prepared by A. Reiter C(7_S..
Reviewed by Project No.
Approved by P. Hoang A. Dermenjian Date Date Date 12122- 035 I I Approved by 2.3.2 Vacuum dry at 3mm Hg:
To remove the moisture in the MSB cavity, a vacuum pressure of 3mm Hg (0.058 psia or
-14.642 psig) is maintained in the MSB for 30 minutes as defined in Section 12.2.2.2 of Reference 8.1. The MSB shell stresses are proportional to the pressure stress for -1.5 psig reported in Table 3.4-5 of Reference 8.1.
01M= -0.1'(14.642/1.5) ab= (-1.2 - (-0.1))*(14.642 / 1.5) rn= -0.9761 Ksi (yb= -10.7375 Ksi 2.3.3 Pressure Changes Due to Off-normal Ambient Temperature Extremes:
This event defines shell membrane and bending stress caused by the internal pressure changes when the ambient temperature reaches the extremes of 100 F and -40 F. These ambient temperatures are postulated to occur 10 times each year.
For the -40°F temperature extreme, the MSB pressure is -1.5 psi and the shell stresses reported in Table 3.4-5 of Reference 8.1 are listed below.
This external pressure is assumed to generate a negative stress. To be consistent, a positive internal pressure is assumed to generate a positive pressure stress.
0rn = -0.1 Ksi 0 b = -1.2 - (-0.1) Ksi
.b
=
-1.1 Ksi For 100°F day, the MSB pressure is 0.7 psi and the shell stresses are taken as 1/10 of the above test stress at 7 psi.
Urn 0.12 Ksi (7b *0.72 Ksi 2.3.4 Pressure Changes Due to Normal Daily Ambient Temperature Change:
The average ambient temperature fluctuation on a daily basis is assumed to be 360F.
This assumption is based on the maximum ambient temperature change of 20°C from figure 4.1.1 of Reference 8.1. The average daily temperature reported in Reference 8.1 is 750F; therefore, the daily temperature range of 570F to 930F will be used in the fatigue crack growth analysis.
From Table 3.4.2 of Reference 8.1:
EGO402-02.DOC Rev. Date: 06-18-2004 Page 5 of 33
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Client Entergy Project Palisades Project No.
12122 - 035 Prepared by A. Reiter Date I
Reviewed by P. Hoang Date Approved by A. Dermenjian Date Ambient T (OF)
(-40) 75 Tamb :=
100
, 125)
MSB Internal Pressure (psi) d J. 4 ]
I i:=0.. 3 i.-----.
dpi
-100 0
100 200 Tamb MSB Pressure, dp v.s.
Ambient Temperature, Ta It can be seen from these plots that the MSB maximum shell pressure is linearly proportional to the ambient temperature. Therefore, the following linear relationship is established to calculate the MSB pressure for the defined daily temperature fluctuations.
Pmsb(Tamb) := 0.4 -
[
-(-15)] J amb" Therefore, the daily ambient temperature change of 570F to 930F will cause the following pressure change:
For 570F ambient temperature the MSB pressure from Eq. (2) is:
Pmsb( 5 7 ) = -0.1836 psi This is a negative pressure (less than the atmospheric pressure); therefore, the MSB shell stresses are proportional to the stresses in Table 3.4-5 of Reference 8.1 for P=-1.5 psi.
Furthermore, these stress values are conservatively assumed to be negative hoop stresses located near the axial flaw.
l" 9m
-0.1 -(O0.1 8 4 / -. 5) Ksi "m-
-0.0123 Ksi Orb
-0.1349 Ksi EG0402-02.DOC Rev. Date: 06-18-2004 Page 6 of 33
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of 33 X I Safety-Related I
I Non-Safety Related Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter 4
Reviewed by P. Hoang Approved by A. Dermenjian For 930F ambient temperature the MSB pressure is:
Pmsb( 9 3) = 0.305 psi This is a positive pressure; therefore, the stresses are proportional to the pressure test stress reported in Reference 7.1.
am 1.2 * (0.305 / 7) Ksi a b (8.4 + 1.2) * (0.305 / 7) Ksi a~m 0.0523 Ksi b=
0.3137 Ksi 2.4 Thermal Stress Cycle Reference 8.1 reported the maximum shell stress was caused by the -40°F extreme ambient temperature condition. This stress is a shell bending stress caused by the MSB temperature gradient. For this evaluation, this bending stress is assumed to be at the postulated flaw and acting perpendicular to it. This section defines the membrane and bending stress resulting from the MSB temperature gradients for the defined fatigue loading events.
2.4.1 Temperature Chanaes Due to Off-Normal Ambient Temperature Extremes:
The extreme ambient temperature range per Reference 8.1, Section 4, is -40°F with no solar load and 100°F with maximum solar load and is assumed to occur 10 times a year.
Per section 3.4.4.1.1 of Reference 8.1, the maximum axial temperature gradients in the MSB for different ambient temperatures are listed below.
Ambient T (F)
Ta :=
75 100 Maximum Temperature Gradient S423 dT := 404 1400) i:=0.. 2 420 dT 400 0
100 MSB Temperature gradient, dT v.s. Ambient Temperature, Ta EG0402-02.DOC Rev. Date: 06-18-2004 Page 7 of 33
Cales. For Palisades Weld Flaw Analysis far Loaded Spent S3wgeraWi*:M Lxsriudy X I Safety-Related Non-Safety Related Fuel Cask MSB No. 4 Calc. No.
2007 - 20168 Rev. 00 Date:
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V Page 8
of 33 Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter Date I k /
Reviewed by P. Hoang Date Approved by A. Dermenjian Date It can be seen from the above plot that the MSB maximum temperature gradient is linearly proportional to the ambient temperature.
The MSB shell thermal stress is proportional to this temperature gradient. Therefore, the thermal stress corresponding to different ambient temperatures can be estimated from the thermal stress of 1 Ksi for the -
40°F case.
For -40°F ambient:
Ob -
1.0 Ksi For 100°F ambient:
Ub = (400 / 423)
- 1.0 Ksi tUb = 0.9456 Ksi 2.4.2 Temperature Chanaes Due to Daily Ambient Temperature Changes:
The daily ambient temperature change of 360 F will not significantly change the MSB temperature gradient and the associated shell stress. This conclusion is supported by the magnitude of the stress change for the -40OF to 100°F ambient temperature change calculated in the previous section.
2.5 Seismic and Handlinq Loads The handling load associated with moving the MSB was not required to be considered in the fatigue evaluation of Reference 8.1, however for conservatism, the effects of the handling load will be considered for the flaw propagation and stability analysis. In Reference 8.1, the seismic load is defined as an accident condition load and not required to be included in the fatigue evaluation, however for conservatism, it also will be considered in the flaw propagation analysis. The seismic load was determined to be enveloped by the handling load in Reference 8.1. Therefore, the MSB shell stress values for the handling load can be used to conservatively represent the seismic stress values. Considering the probability of a seismic event occurring to be equivalent to the design basis for the station, the enveloped seismic and handling loading events are conservatively assumed to occur 5 times during the design life of the cask with 10 maximum stress cycles associated with each occurrence. The handling stress values are defined in Table 3.4-5 of Reference 8.1 and listed below.
UMrn
= 0.9 Ksi 0b 2.4-0.9 Ksi Ub = 1.5 Ksi 2.6 Residual Stress in the Longitudinal Weld Welding residual stress is required to be considered in the ferritic fatigue crack growth and crack stability evaluations per ASME Section XI Code, Reference 8.2. The residual stress does not affect the primary driving force for the fatigue crack growth, i.e. the stress intensity range AK. It does affect the stress intensity ratio, R, (Kmin / Kmax) which is a secondary variable in EGO402-02.DOC Rev. Date: 06-18-2004 Page 8 of 33
[
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 X-ISafety-Related Non-Safety Related Calc. No.
Rev. 00 Page 2007 - 20168 Date:
12/04/07 9
of 33 Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter Ct.0-6--
Date Reviewed by P. Hoang Date Approved by A. Dermenjian Date determining the fatigue crack growth rate. This evaluation considers the effect of the longitudinal weld residual stress on the fatigue crack growth rate by using the ASME Section XI da/dN crack growth curve for R=1. The value of R=1 is chosen because the stress ranges defined in Sections 2.2 and 2.3 are relatively small and adding the large residual stress to Kmin and Kmax would yield an R ratio close to one.
For the crack stability analysis, the through wall residual stress distribution in the MSB longitudinal double V weld is required.
Therefore, the following engineering judgments are made to justify that the magnitude of the residual stress distribution in a double V weld is significantly less than the magnitude of the residual stress in a typical single V weld in piping.
-The weld metal volume in a double V is less than in single V weld therefore, there is less weld shrinkage.
-Double V weld is symmetric with respect to the mid thickness plane, hence residual stress distribution is more uniform than that of a single V weld.
-Double V weld creates compressive residual stress in the weld root area where the flaw is characterized.
-As the R/t ratio increases, the shell stiffness decreases. The relationship tends to reduce the weld residual stress magnitude in large R/t cylinder.
It is concluded that the residual magnitude in the MSB double V weld is significantly less than the typical residual stress magnitude in a circumferential single V butt weld for piping. The maximum magnitude of the residual stress in a typical circumferential single V butt weld in piping is in tension at the pipe inside surface and approximately equal to the yield of the base material. ;The yield stress of the MSB shell material is 54 ksi (see Section 4.0) and is assumed to be the bounding stress magnitude for the double V weld. Note that the residual stress is highly non-linear in nature; however, for simplicity and conservatism the peak residual stress is added into the bending stress field in the MSB weld.
2.7 Summary of Loadina Stress Ranues for Flaw ProDaqation Initial pressure test stress range (1 Event per MSB life time)
Membrane (Ksi)
Bending (Ksi)
Minimum Maximum Minimum Maximum 0
1.2 0
7.2 EG0402-02.DOC Rev. Date: 06-18-2004 Page 9 of 33
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Entergy Palisades 12122- 035 Prepared by A. Reiter
(
Date J* ilI Reviewed by P. Hoang Date Approved by A. Dermenjian Date Vacuum dry / pressure test stress range (1 Event per MSB life time)
Membrane (Ksi)
Minimum
-0.976 Maximum 1.2 Bending (Ksi)
Minimum Maximum
-10.737 7.2 Daily stress range (365 cycles / year)
Membrane (Ksi)
Minimum Maximum
-0.012 0.052 Bending (Ksi)
Minimum Maximum
-0.135 0.314 Pressure Temp. Gradient Total N/A
-0.012 N/A 0.052 N/A
-0.135 N/A 0.314 Off-Normal Ambient Temperature Extremes (10 Cycles per year)
Membrane (Ksi)
Pressure Temp. Gradient Total Minimum
-0.1 N/A
-0.1 Maximum 0.12 N/A 0.12 Bending (Ksi)
Minimum Maximum
-1.1 0.72 0.946
-0.154 1.0 1.72 Seismic and Handlinq Stress Ranqe Membrane (Ksi)
Bending (Ksi)
Minimum
-0.9 Maximum 0.9 Minimum
-1.5 Maximum 1.5 Seismic / Handling EG0402-02.DOC Rev. Date: 06-18-2004 Page 10 of 33
Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter 6
_ Date
.A-i
'/G-7 Reviewed by P. Hoang Date Approved by A. Dermenjian Date 2.8 Normal and Accident Condition Loads for Flaw Stability Analysis The loads used for the flaw stability analysis are determined from the normal and off-normal (Service Level B only) condition load combinations defined in Table 2.2-4 of Reference 8.1. The maximum combined membrane and bending stress values for the controlling load combination are given in Table 3.4-5 of Reference 8.1 and are listed below.
MSB Shell Maximum Normal Condition Stress Values - Ksi Dead Weight Pressure Thermal Handling Total PL+ Pb P+Q 0.1 0.1 N/A 0.1 1.2 N/A 0.1 1.2 N/A 0.9 1.1 2.4 3.7 2.4 4.7 The pressure test condition loads which must be elevated as a normal condition load are taken from Section 3.4.4.1.7 of Reference 8.1. The maximum MSB shell stress values for the pressure test are listed below. These stress values are greater than the other load combinations and therefore, used in the normal condition flaw stability evaluation.
Pressure Test Stress Values - Ksi Pm 1.2 Residual Stress - Ksi 54.0 Pm + Pb 8.4 For the accident condition flaw stability evaluation, the controlling load combination identified in Table 2.2-4 as Horizontal Drop load. These maximum shell stress values, listed below, are used for the accident condition flaw stability analysis.
Accident Condition Horizontal Drop Stress - Ksi Dead Weight Pressure Thermal Handling Total Pm N/A N/A 0.1 N/A 1.2 N/A 25.9 26.0 71.8 73.0 Residual Stress - Ksi Ph 54.0 EG0402-02.DOC Rev. Date: 06-18-2004 Page 11 of 33
M~-~m*
L-1 cv, Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
Rev. 00 X I Safety-Related Non-Safety Related Page 2007-20168 Date:
12/04/07 12 of 33 Client Entergy Prepared by A. Reiter Date,,
Project Palisades Reviewed by P. Hoang Date Project No.
12122- 035 Approved by A. Dermenjian Date
- 3.
ASSUMPTIONS 3.1 The maximum MSB shell stress values reported in Reference 8.1 are assumed to be acting on the flaw and perpendicular to the flaw plane.
3.2 The average ambient temperature fluctuation on a daily basis is assumed to be 360F.
3.3 The longitudinal weld residual stress is assumed to be a maximum tensile stress equal to the yield stress, i.e. 54.0 Ksi.
- 4.
ACCEPTANCE CRITERIA The following acceptance criteria will be used to determine if the results satisfy the purpose of the calculation:
4.1 Material Properties 4.1.1 Base metal: (
Reference:
Traveler RE022, Heat #61066-32)
Specification ASME SA-516 Gr 70 Yield Stress 367 MPa = 53.23 Ksi Ultimate Stress 541 MPa = 78.47 Ksi Elongation 52%
Average Charpy Impact Energy CVN = 77KJ = 56.875 ft-lbs at -460C or -50°F 4.1.2 Weld Metal: (Attached CMTR for weld metal)
Specification ASME SFA 5.01 Sec. II Part C and ASME Sec III Yield Stress 89.9 Ksi Ultimate Stress 93.2 Ksi Elongation 23%
Charpy Impact CVN 64, 65, 54 ft-lbs at 0 deg°F EGO402-02.DOC Rev. Date: 06-18-2004 Page 12 of 33
Client Project Project No.
Entergy Palisades Prepared by Reviewed by Approved by A. Reiter P. Hoang Date l/- c/
.7 Date Date 12122-035 A. Dermenjian 4.1.3 Weld test coupon POR No. 205 - 92 Ultimate Stress 82.7 Ksi Weld Metal Impact Energy Value:
Cv = 24, 20, 18 ft-lbs at -50 deg°F Heat Affected Zone (HAZ) Impact Energy Value Cv = 56, 60, 52 ft-lbs at -50 deg°F 4.2 Material Fracture Touahness The linear elastic fracture mechanics (LEFM) model of a postulated part through the wall axial crack in the MSB shell longitudinal weld shall meet the IBW-3612 acceptance criteria based on applied stress intensity factor.
The fracture toughness of weld material is determined by two properties Kic and Kid. Kid is the lower bound of critical crack arrest stress intensity at temperature. KIc is the lower bound of critical crack initiation stress intensity at temperature. These two material toughness properties have a correlation to the material Charpy V-notch impact energy, CVN. Reference 8.4, provides a review of many empirical correlations between CVN and Kic and Kid.
Note that Kid, is the material plane strain dynamic fracture toughness which is essentially identical to the Code Kid toughness. Reference 8.4 provides the following simple correlations of Kic and Kid with the CVN value.
3 Klc := 2.CVN 2
Kid:= 5.CVN ksi.-/in, ft - lb ksi -v/in, ft - lb Since the lowest MSB shell temperature is 50F, section 11.1.1.3 of Reference 8.1 and the MSB will not be transported when the ambient temperature less than 0°F, the minimum CVN value for the weld metal at 0°F (54 ft-lbs) is used to calculate Kic and Kid.
CVN: 54-ft-Ib K10:= [2.E.CVN ' 5 Kid:= %r5. E.CVN E:=29.5-1O6.psi K,,= 153.0105 ksii.1in Kid = 89.2468 ksi.Vin-EG0402-02.DOC Rev. Date: 06-18-2004 Page 13 of 33
satw-~S~ L.aridy Caics. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
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Client Entergy Project Palisades Project No.
12122 - 035 4.3 Acceptance Criteria per IWB-3612 Prepared by Reviewed by Approved by A. Reiter Cv-,. 66A, P. Hoang A. Dermenjian Date * ;r/
Date Date
-1 The allowable stress intensification factor for the normal condition including the upset and test condition is:
Kla The allowable stress intensification factor for the emergency and faulted condition is:
Kic K, <
EG0402-02.DOC Rev. Date: 06-18-2004 Page 14 of 33
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
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Non-Safety Related Page 15 of 33
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Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter (.j.,
Date i -/olf0 Reviewed by P. Hoang Date Approved by A. Dermenjian Date
- 5.
METHODOLOGY 5.1 Methodology The fatigue crack growth analysis and the flaw stability analysis are performed using the rules of IWB-3610 and IWB-3620 (for ferritic components less than 4" thick) and Appendix A of Reference 8.2.
EPRI's Ductile Fracture Handbook, Reference 8.5, is used to calculate stress intensity factors for membranes and bending stress for the postulated flaw in the MSB shell weld.
To define the stress intensity factor, K4, for this evaluation, Zahoor's formulation for a semi-elliptical axial flaw subjected to membrane and bending stress in Reference 8.5 is used. The stress intensity formulae are limited to (R1<10). For larger R/t ratios, the above formulae are a conservative approximation. The plots in Reference 8.5 (Figures 8.1-19 and 8.1-30) show the convergence of the stress intensity coefficients as the RAt ratio approaches 10 and these coefficients decrease as the R/t ratio increases. Therefore, the above formulae are conservative for a part through wall flaw in a cylinder with higher Rt ratio.
5.1.1 Stress Intensity Factor K. formulas for uniform stress distribution:
Geometry:
t:= 1 Model Thickness (in)
Ri:= 10 Model Inner Radius (in) a := 0.5 Postulated initial flaw depth (in) b := 0.5 Half of postulated initial flaw length (in) a = 0.5 Flaw depth / thickness ratio t
a = 1 Flaw aspect ratio b
Membrane Stress am:= 1 Ksi (Initial Value)
Parameter a for membrane stress field In Reference 8.5 (page 8.1.23) as a function of a and b:
a am(a, b) :=
.am(a, b) = 0.5 The applicable stress intensity factor, K,n, at the maximum flaw depth for a/b >0.2 and a <2 is calculated below:
1.7767.a - 2.5975.a 2 + 2.752.cc3 - 1.3237-ca 4 +.2363-(a5 Go(a) :
C R1
.05
.102.
-.02
)
Klma(a, b, a) := o-(i-t) 5.Go(aXm(a, b))
Ksi vri EG0402-02.DOC Rev. Date: 06-18-2004 Page 15 of 33
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Safety-Related J Non-Safety Related Page 16 of 33 Client Entergy Prepared by A. Reiter
/
Date
/,.,
Project Palisades Reviewed by P. Hoang Date Project No.
12122 - 035 Approved by A. Dermenjian Date The applicable stress intensity factor, Klmb, at the maximum flaw length location is below:
Gso(a, b) :=[1.06 +.28.Ja )2].fa('41.Go((am(a, b))
,t) Jb 5
Klmb(a, b, () := c,.(irt)*.Gs(a, b)
Ksi *Fi 5.1.2 Stress Intensity Factor K, for Linear Stress Distribution:
From Reference 8.5, page 8.1-37 Go:= Ob. t A linear stress distribution (Ksi) with z Is a distrance from ID and y is the maximum bending stress.
The above linear stress distribution is equivalent to the a stress distribution of a bending stress
- o, plus a membrane stress of ab/2. Therefore, it is conservative to use the above linear stress distribution for bending stress.
From Reference 8.5 (page 8.1-37), parameterci for a linear stress distribution as a function of flaw sizes a and b is:
a ab(a, b) :
The applicable stress intensity factor, K1ba, at the maximum flaw depth location is calculated below:
0.1045.czb(a, b) +.4189.ccb(a, b)2 G1 (a, b) :=
~
2 Ri
.05
.102.
-.02)
Klba(a, b, ci) :=
5(*-t)5.G 1 (a, b)
Ksi-Vrin The applicable stress intensity factor, KbbI at the maximum flaw length location is below:
EG0402-02.DOC Rev. Date: 06-18-2004 Page 16 of 33
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 XaIgrSaf Lty-RyelatedNSn-eafetyRelate
.I aet-eae I
I Non-Safety Related Calc. No.
Rev. 00 Page 2007 -20168 Date:
12/04/07 I
17 of 33 Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter Date V
I0 Reviewed by P. Hoang Date Approved by A. Dermenjian Date Gs, (a, b) :=[0.25 +.
.(a)
J' 6 GI(a,b)
Klbb(a, b, ) := a- (n.t)5G.Gsl (a, b)
Ksi -N/in 5.1.3 Combined Stress Intensity Factor KI for Membrane Plus Bending Stress The above stress intensity factors are combined to formulate the stress intensity factor for a combined membrane plus bending stress field.
Ka(a, b, am, ab):= Klma(a, b, am) + Klba(a, b, ab)
Kb(a, b, am, ab):= Klmb(a, b, am) + Klbb(a, b, ab)
At the maximum crack depth At the maximum crack length 5.2 Fatigue Crack Growth Analysis:
The fatigue crack growth analysis is performed per the requirements of Reference 2.1.2 using the flaw model and fatigue loading stress ranges defined in Section 2.0.
5.2.1 Crack Growth Law.
ASME Section Xl, Appendix A, Fall 1993 Addenda, ferrictic material fatigue crack growth in air environment:
da n
dN where C:=1.99.10
°0.[25.75 (2.88-R) 3.07]
n:= 3.07 AKI =: Kimax - Klmin Klmin R:= Klmax per Section 2.6, the effect of residual stress on fatigue crack growth is considered by conservatively using R=1.
5.3 Computer Programs Used 5.3.1 MathCAD Version 11.2 Enterprise Edition, S&L Program No.: 03.7.548-11.2 EG0402-02.DOC Rev. Date: 06-18-2004 Page 17 of 33
Calcs. For Palisades Weld Raw Analysis for Loaded Spent Fuel Cask MSB No. 4 P
X Safety-Related Non-Safety Related Client Entergy Prepared by A. Reiter Q _.
Project Palisades Reviewed by P. Hoang Project No.
12122 - 035 Approved by A. Dermenjian
- 6.
CALCULATIONS 6.1 Fatigue Crack Growth Calculation 6.1.1 Initial Hydro-test Number of circle is 1. Number of calculation block is 1 Calculation block index i:= 1 Initial flaw dimension: (in) a0:= 0.5 b0 := 0.5 Stress range (Ksi):
ammax := 1.2 abmax := 7.2 Smmin := 0 0 bmin:= 0 Calc. No.
2007-20168 Rev. 00 Date:
12/04/07 Page 18 of 33 Date Date
)
Date R Ratio Fatigue Crack Growth Coefficient R:=I C:= 1.99.10- 1 0 -[25.75.(2.88 - R) 3.07]
n := 3.07 Flaw size after the first hydro test:
a2 := C(Ka(ai-1, bi-1, 0mmax, Gbmax) - Ka(ai-1, bi-1, Ommin, abmin))n + ai-1 b,,:= C.(Kb(ai_1, bi 1-, ammax, Obmax) - Kb(ai-1, biil, Ommin, Obmin))n + bij, ai = 0.5000000234 bi = 0.5000000046 Strress Intensity Factors used in the above crack growth calculation:
(for checking purpose)
Ka(a-1, bh-1, 03mmax, 0bmax) = 3.0829597014 Kb(ai_1,bi, Ommax, obmax) = 1.8210363457 Ka(ai-1, bi-1, Gmmin, Obmin) = 0 Kb(ai-1, bi-1i, cmmin, Gbmin) = 0 AKa := (Ka(ai-1, bi-1, 0 mmax, Obmax) - Ka(ai-1, bi-1, 05mmin, obmin))
AKa = 3.0829597014 AKb := (Kb(ai-,1, b1 1 ammax, 'bmax)
- Kb(ai-1, bi-1., mmin, 'bmin))
AKb = 1.8210363457 EG0402-02.DOC Rev. Date: 06-18-2004 Page 18 of 33
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
S,9.gEDI.*
L.undVy, Rev. 00 X
Safety-Related Non-Safety Related Page Client Entergy Prepared by A. Reiter Project Palisades Reviewed by P. Hoang Project No.
12122 - 035 Approved by A. Dermenjian 6.1.2 Vacuum Drying - Hydro-test Stress Range:
Number of circle is 1. Number of calculation block is 1 Calculation block index i := 2 Initial flaw dimension: (in) a0:= 0.5 b0 := 0.5 Stress range (Ksi):
Gmmax := 1.2 abmax 7.2 Ommin := -0.976 Cbmin :=-10.737 R Ratio R:= 1 Fatigue Crack Growth 2007-20168 Date:
12104/07 19 of 33 Date V*'0 q/07 Date Date Coefficient C:= 1.99.10 10.[25.75.(2.88 - R)- 3.07]
n := 3.07 Flaw size after the vaccum - leak test:
ai := C.(Ka(ai-t, bi-1, ummax, %bmax) - Ka(ai-1, bi-1, Ommin, brbmin))n + ai-1 bi:= C'(Kb(ai-1, bi-1, mmax, %bmax) - Kb(ai-1, b1i-1, rmmin, C'bmin))n + bi_,
ai = 0.5000003069 bi = 0.5000000459 Strress Intensity Factors used in the above crack growth calculation:
(for checking purpose)
Ka(ai-1i, b-1, ammax, gbmax) = 3.0829598475 Kb(ai-1, bi-t, Ommax, obmax) = 1.8210364451 Ka(ai-,, bi-1, ammin, Obmin) = -3.8655 Kb(ai-,., bi-1,, ommin, (9bmin) = -1.8885 AKa := (Ka(ai_
, bi-1, cammax, abmax) - Ka(-i-,, 1-I Ommin,o (bmin))
A*Ka = 6.9485 AKb := (Kb(ai-1, bi-1, gmmaxg, bmax) - Kb(ai-1, bi-1, ommin, Obmin))
AKb = 3.7096 EG0402-02.DOC Rev. Date: 06-18-2004 Page 19 of 33
6.1.3 Daily Temperature and Pressure Stress Range for 50-year Numbers of circle per block is 365. Number of calculation block is 50 Calculation block index i:= 3.. 52 Initial flaw dimension: (in) a2 = 0.5000003069 b2 = 0.50 Stress range (Ksi):
Ommax := 0.052 abmax:= 0.
Ommin :=-0.012
%bmin :=-0 R Ratio R := 1 Fatigue Crack Growth
)00000459 314
.135 Coefficient C:= 1.99.1-10.25.75.(2.88 R)- 3.07]
n := 3.07 Fatigue calculation for 50 blocks of 365 cycles C := 365.C Yeari := i - 2 First, calculated flaw depth at a constant aspect ratio b/a:
bae: -
a2 ai := C-(Ka(ai-i, ba-a,-1, 0 mmax, abmax) - Ka(ai-1i, ba-ai-1.,
Ommin, (Fbmin))n + ai--
Then, calculate crack length bi := C.(Kb(ai-1, bi-1, ammax, Obmax) - Kb(ai-1, bi-1, 0mmin, Obmin))n + hi and crack depth ai := C.(Ka(ai-1, bi-1,,Ymmax, Obmax) - Ka(ai-1, bi-1, 0 mmin, Obmin))n + ai-1 EG0402-02.DOC Rev. Date: 06-18-2004 Page 20 of 33
~agrn1~
LAAN~dy Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
Rev. 00 X
Safety-Related Non-Safety Related Page Prepared by A. Reiter Reviewed by P. Hoang Approved by A. Dermenjian 2007 - 2016E Date:
21 12/04/07 of 33 Client Project Project No.
Entergy Palisades 12122 -035 Date I Oi 0* 7 Date Date Flaw size change in 50 years due to daily temperature change Year Year1 1
2 3
4 5
6 7
8 9
10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Flaw depth (in) aj =
0.5000003084 0.5000003098 0.5000003113 0.5000003127 0.5000003142 0.5000003156 0.5000003171 0.5000003185 0.5000003200 0.5000003214 0.5000003229 0.5000003243 0.5000003258 0.5000003273 0.5000003287 0.5000003302 0.5000003316 0.5000003331 0.5000003345 0.5000003360 0.5000003374 0.5000003389 0.5000003403 0.5000003418 0.5000003432 0.5000003447 0.5000003461 0.5000003476 0.5000003491 0.5000003505 Flaw length (in) 2.bj =
1.0000000924 1.0000000929 1.0000000933 1.0000000938 1.0000000943 1.0000000948 1.0000000953 1.0000000958 1.0000000963 1.0000000968 1.0000000973 1.0000000978 1.0000000983 1.0000000988 1.0000000993 1.0000000998 1.0000001003 1.0000001008 1.0000001013 1.0000001018 1.0000001023 1.0000001028 1.0000001033 1.0000001037 1.0000001042 1.0000001047 1.0000001052 1.0000001057 1.0000001062 1.0000001067 j :=3.. 32 EG0402-02.DOC Rev. Date: 06-18-2004 Page 21 of 33
Caics. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007-20168 r
Rev. 00 Date:
12104/07 X I Safety-Related NornSafety Related Page 22 of 33 Year Flaw depth (in)
Flaw length (in) j:= 33.. 52 Yearj 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 a1 =
0.5000003520 0.5000003534 0.5000003549 0.5000003563 0.5000003578 0.5000003592 0.5000003607 0.5000003621 0'5000003636 0.5000003650 0.5000003665 0.5000003679 0.5000003694 0.5000003709 0.5000003723 0.5000003738 0.5000003752 0.5000003767 0.5000003781 0.5000003796 2.bi =
1.0000001072 1.0000001077 1,0000001082 1.0000001087 1.0000001092 1.0000001097 1.0000001102 1.0000001107 1.0000001112 1.0000001117 1.0000001122 1.0000001127 1.0000001132 1.0000001137 1.0000001141 1.0000001146 1.0000001151 1.0000001156 1.0000001161 1.0000001166
(
EG0402-02.DOC Rev. Date: 06-18-2004 Page 22 of 33
!B.0.
4L ' Ldyav Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
Rev. 00
(
X1 x I Safety-Related Non-Safety Related Page Client Entergy Prepared by A. Reiter Project Palisades Reviewed by P. Hoang Project No.
12122 - 035 Approved by A. Dermenjian 6.1.4 Off-normal Ambient Temperature Extremes, 10 cycles per year for 50-year:
Numbers of circle per block is 10. Number of calculation block is 50 Calculation block index i:= 53.. 102 Initial flaw dimension: (in) a5 2 = 0.5000003796 b52 = 0.500000 Stress range (Ksi):
Gmmax := 0.12 Obmax := 1.72 ammin :=-0.o1 bmin :=-0.154 R Ratio R := 1 2007 -20168 Date:
12/04/07 23 of 33 Date jD-I'i
-7 Date Date 0583 Fatigue Crack Growth Coefficient C:= 1.99*.10-
.[25.75.(2.88-R)- 3.07]
n:= 3.07 Fatigue calculation for 50 blocks of 365 cycles C:= 10.C Yeari:= i - 52 First, calculated flaw depth at a constant aspect ratio b/a:
ba:=
a52 N:= C.(Ka(ai-1, ba.ai1l, cmmax, Gbmax) - Ka(ali-,
baSai-l, cmmin, Gbmin))n + ai-"
Then, calculate crack length bi := C.(Kb(ai-1, bi-1, 0mmax, Obmax) - Kb(ai-1, bi-1, mmin, Obmin)) n + bi-,
and crack depth ai := C.(Ka(ai-1, bi-1, 0mmax, bmax) - Ka(ai-1, bi-1, Ommin, Obmin)) n + ai-1 EG0402-02.DOC Rev. Date: 06-18-2004 Page 23 of 33
Flaw size change in 50 years due to off-normal ambient temperature change Year Year=
1 2
3 4
5 6
7 8
9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Flaw depth (in) aj 00 0.5000003823 0.5000003849 0.5000003876 0.5000003903 0.5000003930 0.5000003957 0.5000003984 0.5000004010 0.5000004037 0.5000004064 0.5000004091 0.5000004118 0.5000004145 0.5000004172 0.5000004198 0.5000004225 0.5000004252 0.5000004279 0.5000004306 0.5000004333 0.5000004359 0.5000004386 0.5000004413 0.5000004440 0.5000004467 0.5000004094 0.5000004520 0.5000004547 0.50000045741 0.50000046011 Flaw length (in) 2.bj =
1.0000001174 1.0000001181 1.0000001189 1.0000001197 1.0000001204 1.0000001212 1.0000001219 1.0000001227 1.0000001234 1.0000001242 1.000000125 1.0000001257 1.0000001265 1.0000001272 1.000000128 1.0000001287 1.0000001295 1.0000001303 1.000000131 1.0000001318 1.0000001325 1.0000001333 1.000000134 1.0000001348 1.0000001356 1.0000001363 1.0000001371 1.0000001378 1.0000001386 1.0000001393 j:= 53.. 84
/
EG0402-02.DOC Rev. Date: 06-18-2004 Page 24 of 33
aE-frg043N:
LA~rHAV..
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007 - 20168 Rev. 00 Date:
12/04/07 X I Safety-Related
{Non-Safety Related Page 25 of 33 Client Project Project No.
Entergy Palisades 12122- 035 I
Prepared by Reviewed by Approved by A. Reiter P. Hoang A. Dermenjia
/
Date
/Oq /
Date an Date Year Yearj 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 501 Flaw depth (in) aj=
0.5000004628 0.5000004655 0,5000004681 0.5000004708 0.5000004735 0.5000004762 0.5000004789 0.5000004816 0.5000004842 0.5000004869 0.5000004896 0.5000004923 0.5000004950 0.5000004977 0.5000005004 0.5000005030 0.5000005057 0.5000005084 0.5000005111 0.5000005138 Flaw length (in) 2.bj =
1.0000001401 1.0000001409 1.0000001416 1.0000001424 1.0000001431 1.0000001439 1.0000001446 1.0000001454 1.0000001462 1.0000001469 1.0000001477 1.0000001484 1.0000001492 1.0000001499 1.0000001507 1.0000001515 1.0000001522 1.000000153 1.0000001537 1.0000001545 j := 83.. 102 EG0402-02.DOC Rev. Date: 06-18-2004 Page 25 of 33
r'ger'm; ILL*ny **
Client Entergy Project Palisades Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007-20168 Rev. 00 Date:
12/04/07 X I Safety-Related Non-Safety Related Page 26 of 33 Prepared by A. Reiter Date \\
/1 Reviewed by P. Hoang Date Project No.
12122-035 Approved by A. Dermenjian Date 6.1.5 Seismic and Normal Handling Stress Range, 1 cycles per year for 50-year:
Numbers of circle per block is 1. Number of calculation block is 50 Calculation block index i := 103.. 152 Initial flaw dimension: (in) a102 = 0.5000005138 b10 2 = 0.5000000772 Stress range (Ksi):
Gmmax := 0.9 Obmax:= 1.5 ammin :=-0.9 cbmin:= -1.5 R Ratio R:= 1 Fatigue Crack Growth Coefficient C:= 1.9910 1
.[25.75.(2.88 - R)- 3.07]
n:= 3.07 Fatigue calculation for 50 blocks of 1 cycle C:= 1.C Yeari := i - 102 b52 First, calculated flaw depth at a constant aspect ratio b/a:
ba:=
a52 ai:= C.(Ka(ai-1, ba.ai-.l, ammax' %bmax) - Ka(ai-1(, ba.aiil, ammin, %bmin))n + ai-1 Then, calculate crack length bi:= C-(Kb(ai-1, bi-i, ammax, Gbmax) - Kb(ai-1, bi-1, ammin, abmin))n + bi-1 and crack depth ai := C. (Ka(ai-1, bi-1i, cammax, Obmax) - Ka(ai-1, bi-1, cymmin, obmin ))n + ai-1 EG0402-02.DOC Rev. Date: 06-18-2004 Page 26 of 33
Client Project Project No.
'S LaIJrwdy~
A Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
Rev. 00 X I Safety-Related Non-Safety Related Page 2007-20168 Date:
27 12/04/07 of 33 Entergy Palisades 12122-035 i
Prepared by Reviewed by Approved by A. Reiter G,*
P. Hoang A. Dermenjian Date I /10/07 Date Date Flaw size change in 50 years due to seismic and normal handling loads:
Year Flaw depth (in)
Flaw length (in) j := 103.. 134 Year=
1 2
3 4
5 6
7 8
9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 271 281 J291 301 aj =
0.5000005254 0.5000005370 0.5000005486 0.5000005602 0.5000005718 0.5000005835 0.5000005951 0.5000006067 0.5000006183 0.5000006299 0.5000006415 0.5000006532 0.5000006648 0.5000006764 0.5000006880 0.5000006996 0.5000007112 0.5000007228 0.5000007345 0.5000007461 0.5000007577 0.5000007693 0.5000007809 0.5000007925 0.5000008041 0.5000008158 0.5000008274 0.5000008390 0.5000008506 0.5000008622 2.bi =
1.0000001685 1.0000001825 1.0000001965 1.0000002104 1.0000002244 1.0000002384 1.0000002524 1.0000002664 1.0000002804 1.0000002944 1.0000003084 1.0000003224 1.0000003363 1.0000003503 1.0000003643 1.0000003783 1.0000003923 1.0000004063 1.0000004203 1.0000004343 1.0000004482 1.0000004622 1.0000004762 1.0000004902 1.0000005042 1.0000005182 1.0000005322 1.0000005462 1.0000005602 1.0000005741 EG0402-02.DOC Rev. Date: 06-18-2004 Page 27 of 33
Client Entergy Project Palisades Project No.
12122 - 035 Prepared by A. Reiter Date
/O
- )
Reviewed by P. Hoang Date Approved by A. Dermenjian Date Year Flaw depth (in)
Flaw length (in) j:= 133.. 152 Year1 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 aj=
0.5000008738 0.5000008854 0.5000008971 0.5000009087 0.5000009203 0.5000009319 0.5000009435 0.5000009551 0.5000009668 0.5000009784 0.5000009900 0.5000010016 0.5000010132 0.5000010248 0.5000010364 0.5000010481 0.5000010597 0.5000010713 0.5000010829 0.5000010945 2.bj =
1.0000005881 1.0000006021 1.0000006161 1.0000006301 1.0000006441 1.0000006581 1.0000006721 1.0000006861 1.0000007 1.000000714 1.000000728 1.000000742 1.000000756 1.00000077 1.000000784 1.000000798 1.0000008119 1.0000008259 1.0000008399 1.0000008539
( )
EG0402-02.DOC Rev. Date: 06-18-2004 Page 28 of 33
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Catc. No.
2007 - 20168 r,=,
, L-uRsy" Rev. 00 Date:
12/04/07 X I Safety-Related J
Non-Safety Related Page 29 of 33 Client Entergy Prepared by A. Reiter CQ, h.. o Date 4/O=1/O7 Project Palisades Reviewed by P. Hoang Date Project No.
12122 - 035 Approved by A. Dermenjian Date 6.2 Flaw Stability Calculation After 50 years of service with the loading conditions defined in Section 2, the final crack size is:
al52 = 0.5000010945 in b15 2 = 0.500000427 in In this section, the flaw stability evaluation is based on the calculated final flaw size with R=1. The maximum loading under the normal condition and the accident condition will be considered. The ASME Section XI stress intensity factors acceptance criteria stated in Section 4.0 will be used in the evaluation.
The minimum weld CVN impact energy at 00F degree (see Section 4.0) is CVN := 54 ft-lbs E := 29.5 E+6 psi, elastic modulus Material facture toughness per Section 4.2 KIC:= J2
.E.CVN5 KIc= 153.011 ksi N 'in Kid:= %F5.ECVN KId = 89.247 ksi -4in EG0402-02.DOC Rev. Date: 06-18-2004 Page 29 of 33
r Ltjr~dy~
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007 - 20168 Rev.
00 Date:
12/04/07 X
Safety-Related Non-Safety Related Page 30 of 33 Client Entergy Project Palisades Prepared by A. Reiter Date io t/f Reviewed by P. Hoang Date n
Project No.
1212-2-035 Approved by A. Dermenjlian Date 6.2.1 Normal Loading Condition The maximum combined stress for the normal condition is defined in Section 2.8. The bounding welding residual stress of 54 ksi is conservative added to the bending stress of the normal condition.
m( := 1.2 ksi Ob:= 8.4 - 1.2 + 5 4 ksi Ka(a152, b152, am, Ob) = 18.107 Kb(al 5 2, b1 5 2, am, Ob) = 6.328 Safety Factor for the normal condition:
ksi Vlfii ksi -N1"n Kid
= 4.929 18.107 Therefore, the safety factor of the postulated flaw after 50 year of service is larger than the required safety factor of fh = 3.162 per ASME Section XI.
6.2.2 Faulted Loading Condition The maximum combined stress for the accidental load stress from the Horizontal Drop load case is defined in Section 2.8. The bounding welding residual stress of 54 ksi is conservative added to the bending stress of the normal condition.
am := 26 ksi Ob:= 73-26-+ 54 Ka(a152, b152,am, ab) = 51.495 Kb(a152, b152, am Ob) 34.865 Safety Factor for the faulted condition:
ksi ksi.V in ksi..ini KIC
=2.972 51.485 Therefore, the safety factor of the postulated flaw after 50 year of service is larger than the required safety factor of /2 = 1.414 per ASME Section XI.
EG0402-02.DOC Rev. Date: 06-18-2004 Page 30 of 33
- ""*i*
- m*
- .m*o
-,c o
aiae Wl lwA i
orLae pn Cas MS No 4 UIU.
NoU.
4VUU
- e-U 100 3r,-gei.
'-.ndiciy, Rev. 00 Date:
12004/07 X
Safety-Related f Non-Safety Related Page 31 of 33 Client Entergy Project Palisades Project No.
12122- 035 Prepared by A. ReiterC2 4 j k
Date Reviewed by P. Hoang Date Approved by A. Dermenjian Date
- 7.
RESULTS 7.1 This evaluation was based on a conservative flaw model assumed to be half the MSB wall thickness in depth and 1 u in length. The loads used for the fatigue crack growth included all normal, test and normal handling loads, as well as the seismic load. The normal condition flaw stability evaluation used the maximum combined loads from the normal operating, test and upset conditions. The emergency and faulted condition flaw stability evaluation used the maximum combined accident loads which were from the transportation drop load event. The shell stress values used in both evaluations were based on the maximum stress values reported for the MSB in the SAR, Reference 8.1, although the maximum shell stress did not occur at the location of the flaw. The direction of the shell stress values for each load were assumed to act in the shell hoop direction, i.e. perpendicular to the flaw plane, although some of these stress values are actually acting in the longitudinal direction,i.e parallel to the flaw plane. Although the residual stress for a double grove weld was shown to be less in magnitude than a single grove circumferential weld, the residual stress Is consistent with a typical residual stress magnitude for single grove circumferential welds.
Using the conservatively defined loads and flaw model, the fatigue crack growth for the 50 year life of the MSB was shown to be insignificant, i.e. less than 0.00001" in depth and length. The normal condition flaw stability yielded a margin of 4.93 compared to the ASME code safety factor of 3.16. The faulted condition flaw stability yielded a margin factor of 2.97 compared to the ASME Code safety factor of 1.414.
These results demonstrate that the stress levels in the MSB shell are very low and are insufficient to significant crack growth. Also, the postulated flaw remains stable when subjected to accident conditions. Consequently, it has been demonstrated that the postulated flaw will not grow through wall when subjected to fatigue loads or a one time accident condition load.
EGO402-02.DOC Rev. Date: 06-18-2004 Page 31 of 33
Calms. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007-20168
.rf
&LuId I
Rev. 00 Date:
12/04/07 X I Safety-Related Non-Safety Related Page 32 of 33 Client Entergy Prepared by A. Reiter (24/,-
Date Project Palisades Reviewed by P. Hoang Date Project No.
12122 - 035 Approved by A. Dermenjlan Date
- 8.
REFERENCES 8.1 Safety Analysis Report for the Ventilated Storage Cask, PSN-91 -001, Revision 1, October, 1991.
8.2 ASME B&PV Code,Section XI, 1992 Edition.
8.3 Postulated Causes for MSB #4 Flaws, J.C. Nordby to M.A. Ferens, August 22, 1994, JCN94*031.
8.4 Interpretive Report on Small-Scale Test Correlations with Kb Data, WRC Bulletin 265.
8.5 Zahoor Akram, "Ductile Fracture Handbook," Vol. 3, Electric Power Research Institute, Research Project 1757-69. Section 8.1.3 and 8.1.4.
8.6 Technical Report on Material Selection and Processing Guidelines for BWR Coolant Pressure Boundary Piping, NUREG-0313, Revision 2.
EG0402-02.DOC Rev. Date: 06-18-2004 Page 32 of 33
Calca. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSS No. 4 Calc. No.
2007 - 20168 r..iruny, Rev. 00 Date:
12/04/07 X I -Safety-Related I
Non-Safety Related Page 33 of 33 Client Entergy Prepared by A. Reiter U
/t Date
/c
[l/./ 7 Project Palisades Reviewed by P. Hoang Date Project No.
12122 - 035 Approved by A. Dermenjian Date
- 9.
ATTACHMENTS A.
Alloy Rod Corporation Certificate of Analysis B.
Testing Engineers, Inc, QM-483 Suggested Format for Procedure Qualification Record C.
Testing Engineers, Inc, Charpy V-Notch Impact Test Laboratory Number: M1061 D.
Testing Engineers, Inc, Work Request Number M1031 E.
NRC Letter Total Number of Pages 3
3 2
2 EG0402-02.DOC Rev. Date: 06-18-2004 Page 33 of 33
ATTACHMENT A Alloy Rod Corporation Certificate of Analysis Total Number of Pages Including this Cover Page = 3 EG0402-02.DOC Rev. Date: 06-18-2004 Page Al of A3
-1 e Celcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 S~r
.- LA-.
dy, X
Safety-Related Non-Safety Related Calc. No.
2007 - 20168 Rev. 00 Date:
12/04/07 Page A2 of A3
(,
Client Entergy Project Palisades Project No.
12122-035 Prepared by A. Reiter C 0 --
Date 1. /04107 Reviewed by P. Hoang Date Approved by A. Dermenjian Date I
~ BG -to Appmeaft ALLOY RODS CORPORATION CERTIFMCATE OF ANALYSIS P.O. BOX 517/11500 KAREN LANE HANO*VER. PA 17331 717 11'% V-1 I CEMTIFIED k4TERIALS WT UIDOlT cNTR COVERS RICEHOND ENTERPRISES PO#1648; VEWSTAR WUCZlAR SHIPING TICCET K910953 VELDSTAR CO.
Customer Order No.: 9094 2750 fITilEL', RD.
Order go.: 142928-2 AURORA. IL 60504 This Material Conforms to Specification:
ASNE SFA 5.20 SEC.
II PART C & ASHE SEC.
II, SUISEC. NZ FOR CLASS 2 MATERIAL 1989 Ea.. 1989 AMO.. ASIE SFA 5.01. CLASS T-2.
SCHEDULE K.
Trade Name 20 CEI PART 21 APPLIES or Trademark: Dual ShieLd 7100 Ultra Diameter Size: 1/16' x 600 CL Types E7:T-1 Weigbt: 7.680 lbs.
Test. NO.: 2-168564-00 Lot Number: 28365 X-Rays Satisfactory Carbon:
Manganese:
Chromium:
Nickel:
Columblum-:
Tantalum:
Holybdealma:
Tungsten:
Copper:
Tianlum:
Phosphoruss Sulphur:
Vanadium:
Cobalt:
.03 1.14
.04
.01
. 74
.01
.02
.012
. 02 Type Steel A-285 Full Split Triple Quad Volts Amps 1
5 29 300 DC*
Test Results:
0 Yield Tensile Elongation (2"). 2 Red. of Area As Velded 83.900 93.200 73.0 57.3 Charpy V-Notch Impacts Tested 0 00F.
Ft. Lbs.
64-65-54 Let. IPa.
56-48-51 Z Shear 30-30-30 Shielding gas: CO, Preheats 653F.
Int4rpass:
3250F.
Fillets:
OK Verticalloverbead Tensile Specimen.505'-
Impact Specimen.394" a.394' THIS MATERIAL IS CEIFIED TO K1 FREE OF ANY MERCURY CFETAMINATIOU.
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13as94 LuArbsdy Calm. For Palisades Weld Flaw Analysis for Loaded Spenl Fuel Cask MSB No. 4 Calc. No.
2007 - 20168 Rev. 00 Date:
12104/07 X ISafety-Related Non-Safety Related Page 81 of B3 Prepared by A. Reiter Date q-Oi Reviewed by P. Hoang Date Approved by A. Dermenlian Date Client Entergy Project Palisades Project No.
12122-035 ATTACHMENT B Testing Engineers, Inc. QM-483 Suggested Format For Procedure Qualification Record Total Number of Pages Including this Cover Page = 3 EG0402-02.DOC Rev. Date: 06-18-2004 Page B1 of B3
Calcm. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 wk L..jrdy X I Safety-Related I
I Non-Safety Related Calc. No.
Rev. 00 Page 2007-20168 Date:
B2 12/04/07 of B3 I.
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Client Entergy Project Palisades Project No.
12122-035 Calcs. For Palisades Weld Raw Analysis for Loaded Spent Fuel Cask MSB No. 4 X I Safety-Reated j Non-Safety Related Calc. No.
Rev. 00 Page Prepared by Reviewed by Approved by 2007-20168 Date:
12/04/07 C1 of C2 Date Date Date A. Reiter P. Hoang A. Dermenjian ATTACHMENT C Testing Engineers, Inc. Charpy V-Notch Impact Test, Laboratory Number M1061 Total Number of Pages Including this Cover Page = 2
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ATTACHMENT D Testing Engineers, Inc, Work Request Number M1031 Total Number of Pages Including this Cover Page = 2
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EG0402-02.DOC Rev. Date: 06-18-2004 Page D2 of D2
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 Calc. No.
2007 - 20168
- G4 r L,.dy" Rev. 00 Date:
12104/07 X
Safety-Related Non-Safety Related Page El of E3 Client Entergy Prepared by A. Reiter Date l>[o,1/'
Project Palisades Reviewed by P. Hoang Date Project No.
12122- 035 Approved by A. Dermenjian Date ATTACHMENT E NRC Letter Total Number of Pages Including this Cover Page = 3 EG0402-02.DOC Rev. Date: 06-18-2004 Page El of E3
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No. 4 X
Safety-Related Non-Safety Related Catc. No.
2007-20168 Rev. 00 Date:
12104/07 Page E2 of E3 Client Entergy Project Palisades Project No.
12122 - 035 Prepared by A. Reiter Date Reviewed by P. Hoang Date Approved by A. Dermenjian Date April 9, 2007 MEMORANDUM TO:
Jamnes L. Cameron, Branch Chief Division of Nuclear Material and Safety, Region III FROM:
SUBJECT:
Gordon Bjorkman, Branch Chief lRAw Spent Fuel Storage and Transportation Division, NMSS REQUEST FOR ADDITIONAL INFORMATION, REGION III TAR REQUESTING ASSESSMENT OF PALISADES WELD FLAW ANALYSIS FOR LOADED SPENT FUEL CASK MSB NO. 4 TAC No. A10126 The Division of Spent Fuel Storage and Transportation (SFST) staff finds that additional information is required in order to complete the ongoing TAR for assessing the adequacy of the Palisades weld flaw analysis for loaded spent fuel cask MSB No. 4.
During our review of the fatigue crack growth calculation, it was noted that one input variable was fixed at a possibly non-consurvatlva value. As a consequence of this assumption, the associated fatigue crack growth rates could also be non-conservative. The result could thus under-predict the eventual flaw size, possibly by a very significant margin. Consequently, attached is a request for additional information in regards to this calculation.
Please contact Jerry Chuang, Senior Structural Engineer, of my staff at 301-415-8586. if you require clarification of this issue.
Enclosure:
Request for Additional Information
(
DISTRIBUTION:
NMSS rOf SFST rOf MGryglak JChuang MDebose GHOmseth BWhlte ML07o080519 OFC:
JChuang MDebose GHornseth GBjorkman DATE:
04/05/2007 04105/2007 04/05/2007 04/09/2007 OFFICIAL AGENCY RECORD EG0402-02.DOC Rev. Date: 06-18-2004 Page E2 of E3
Calcs. For Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSS No. 4 X'
Safety-Related Non-Safety Related Calc. No.
2007 - 2016L Rev. 00 Date:
12/U-.
Page E3 of E3 Client Entergy Project Palisades Prepared by A. Reiter A'J 4
Date *
/(
~
Reviewed by P. Hoang Date Approved by A. Dermenjian Date Project No.
12122-035 REQUEST FOR ADDITIONAL INFORMATION Palisades Weld Flaw Analysis for Loaded Spent Fuel Cask MSB No 4 Model No. VSC-24
Reference:
Licensee supplied calculation EA-FC-864-50, Appendix 2 to MSB No. 4 "Strucku" Integrity Assessment," page 18.
Issue:
The fatigue crack growth analysis set a fixed value of R at 0.9 in a fatigue crack growth law provided by ASME Section XI, Article A-4000 for all stress cycles. Provide fatigue crack growth data for a surface crack In ASTM SA-516, Grade 70 femtic steel for the range of 0.9 < R < 1.0 and re-analyze the case using the data to demonstrate that the final crack length determined by the referenced calculation is conservative.
Background:
The Division of Spent fuel and Storage and Transportation (SFST) staff reviewed the fatigue crack growth calculatibn for an initial semi-circuler surface crack present In the MSB No. 4, considering 50 yearq'of cyclic service conditions. The calculations assumed all loading cycles had a constant R vgoue of 0.9. However, due to the level of residual stresses imposed in the assumptions, it appears to the staff tht most of the loading cycles are in the range of 0.9cR < 1.0.
It is well known that higher values of R yield a larger crack growth rate per cycle for a fixed stress amplitude. Thus, fatigue crack growm data for a semi-cirular surface crack in ASTM SA-516, Grade 70 ferritic steel for this R-range (0.9 < R c 1.0), In air, at room temperature are needed. Using such data, a new analysis should be performed to show that the final calculated crack sizes at the end of a 50 year service life remain stable.
Absent such data and re-analysis, the SFST staff are unable to determine if the flaw propagation after 50 years of cyclic loads would remain stable, thus assuring the integrity of the cask.
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EG0402-02.DOC Rev. Date: 06-18-2004 Page E3 of E3