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{{#Wiki_filter:SUPPLEMENTAL INFORMATION ANALYTICAL EVALUATION OF INSERVICE INSPECTION EXAMINATION RESULTS Attachment B CMR-98-0243,"Fracture Mechanics Evaluation of N1A Nozzle Safe End." 9905i30i72 990429 PDR ADOCK 05000397 8 PDR WA5HINGTON FUSLIC POWER 49 SUPPLY SYSI'l&Qp/jo)q~g,L CMR Page Cont'd On Page BDC Page CALCULATION MODIFICATION RECORD A//F/Gale.Modification No.CMR-98-0243 Applies lo: Calcuhtion No.ME-02-98-04 Rev.0 This CMR has been filed against the current revision of the identified calculation, and must be closed out at a future date.All technical data needed to actually update the calculation has been included in this CMR package.1.Purpose of CMR This CMR provides the new fracture mechanics calculations and computer runs required to adjust the examination schedule for the N1 nozzle indication to 970 days versus 870 days evaluated in the initial calculation.
{{#Wiki_filter:SUPPLEMENTAL INFORMATION ANALYTICALEVALUATIONOF INSERVICE INSPECTION EXAMINATIONRESULTS Attachment B CMR-98-0243, "Fracture Mechanics Evaluation of N1A Nozzle Safe End."
The change to the examination time interval was required because of the change in the outage date.2.Input Data Summary (Use additional sheets if necessary)
9905i30i72 990429 PDR ADOCK 05000397 8               PDR
The data inputs were the same as those used in the original calculations for the IGSCC and Fatigue evaluations.
 
The change was made to the initial crack length used in the fatigue evaluation for the OBE and SSE computer run.The initial crack depth was taken from the IGSCC computer output for 970 days of operation.
BDC Page WA5HINGTON FUSLIC POWER         CALCULATIONMODIFICATIONRECORD                                            A//F/
The initial length was determined as in the original calculation by multiplying the depth by 20 as required by NUREG 0313 Rev 2.The applied cycles required for OBE and SSE were then applied to this crack size and the resulting final crack depth compared to the ASME Code tables as in the original calculation to determine acceptability.
49       SUPPLY       SYSI'l&                                             Qp/jo) q~g,L                       CMR Page     Cont'd On Page Gale. Modification No.                                             Applies lo:     Calcuhtion No.                               Rev.
It was determined that the 970 days of operation is acceptable base on the results of this CMR.3.Predicted Result or conclusion When this CMR is incorporated into the calculation, the resultslconclusions viill be: It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld has to occur.The evaluation demonstrates under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6.The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking.If the IGSCC phenomena is active the indication will increase in depth to 1.05" (including OBE and SSE)by the end of 970 days of operation, which is less than the ASME Code allowable.
CMR-98-0243                                                          ME-02-98-04                                                   0 This CMR has been filed against the current revision of the identified calculation, and must be closed out at a future date. All technical data needed to actually update the calculation has been included in this CMR package.
Qereare No o.<her C/ri/rs erron'rrst C ic-I>/-'8/"<rr ro'/.'Ae/nra A/,;+or(e r q (@(eo(ar;q (egal+h/'Prepared by I Date Verified by I Date Tom Erwin I 0/5/88 c lad gs This CMR has been incorporated into Revision of the identified calculation 968-19954 R2 (3/98)Signature Date WASHINGTON bUbLIC?OWER k3 SUPPLY SYSTEM VERIFICATION CHECKLIST FOR CALCULATIONS AND CMRs Page Conrd On Page Calculation/CMR CMR-.98-0243 verified using the following methods: Revision 0 was g Checklist Below Q Alternate Calculations Checklist Item Clear Statement of purpose of analysis Methodology clearly stated and sufficiently detailed and appropriate to proposed application Logical consistency of analysis~Completeness of documenting references
: 1. Purpose of CMR This CMR provides the new fracture mechanics calculations and computer runs required to adjust the examination schedule for the N1 nozzle indication to 970 days versus 870 days evaluated in the initial calculation. The change to the examination time interval was required because of the change in the outage date.
~Completeness of documenting and updating output interface documents Completeness of input Accuracy of input data Consistency of input data with approved criteria Completeness in stating assumptions Validity of assumptions Calculation sufficiently detailed~Arithmetical accuracy~Physical units specified and correctly used Reasonableness of output conclusion Supervisor independency check (if acting as Verifier)-Did not specify analysis approach-Did not rule out specific analysis options-Did not establish analysis inputs Initial~If a computer program was used:-Is the program appropriate for the proposed application?
: 2. Input Data Summary (Use additional sheets if necessary)
-Have the program error notices been reviewed to determine if they pose any limitations for this application'
The data inputs were the same as those used in the original calculations for the IGSCC and Fatigue evaluations. The change was made to the initial crack length used in the fatigue evaluation for the OBE and SSE computer run. The initial crack depth was taken from the IGSCC computer output for 970 days of operation. The initial length was determined as in the original calculation by multiplying the depth by 20 as required by NUREG 0313 Rev 2. The applied cycles required for OBE and SSE were then applied to this crack size and the resulting final crack depth compared to the ASME Code tables as in the original calculation to determine acceptability. It was determined that the 970 days of operation is acceptable base on the results of this CMR.
-ls the program name, revision number and date of run inscribed on the output?-Is the program identified on the Calculation Method form'If so, is it listed in chapter 10 of the Engineering Standards Manual?Other Elements Considered
: 3. Predicted Result or conclusion When this CMR is incorporated into the calculation, the resultslconclusions viill be:
~If a separate verifier was used for validating these functions or a portion of these functions, sign and initial below.Based on the foregoing, the calculation is adequate for the purpose intended.Verifier Signature(s)/Date
It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld has to occur. The evaluation demonstrates under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6. The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking. If the IGSCC phenomena is active the indication will increase in depth to 1.05" (including OBE and SSE) by the end of 970 days of operation, which is less than the ASME Code allowable.
/d6 ys Verifier Initials 988-25280 R I (3/98)
Qereare             No       o.<her     C/ri/rs       erron'rrst C ic- I>/- '8/ "<rr ro'/.
WASHINGTON tulLIC POWER I>SUPPLY SYSIVM CALCULATION OUTPUT
                                'Ae/ nra               A/,;+or(e                                           egal+ h/ '
r q       (@(eo(ar;q (
Prepared by I Date                                                               Verified by I Date Tom Erwin I 0/5/88 c                                               lad   gs This CMR has been incorporated into Revision           of the identified calculation                                                                     Signature                        Date 968-19954 R2 (3/98)
 
Conrd On Page WASHINGTON bUbLIC ?OWER           VERIFICATIONCHECKLIST FOR                              Page k3 SUPPLY SYSTEM                                 CALCULATIONSAND CMRs Calculation/CMR CMR-.98-0243                                   Revision 0 was verified using the following methods:
g       Checklist Below                             Q     Alternate Calculations Checklist Item                                                                                     Initial Clear Statement of purpose of analysis Methodology clearly stated and sufficiently detailed and appropriate to proposed application Logical consistency of analysis
            ~     Completeness of documenting references
            ~     Completeness of documenting and updating output interface documents Completeness of input Accuracy of input data Consistency of input data with approved criteria Completeness in stating assumptions Validity of assumptions Calculation sufficiently detailed
            ~     Arithmetical accuracy
            ~     Physical units specified and correctly used Reasonableness of output conclusion Supervisor independency check (if acting as Verifier)
                        - Did not specify analysis approach
                        - Did not rule out specific analysis options
                        - Did not establish analysis inputs
            ~     If a computer program was used:
                        - Is the program appropriate for the proposed application?
                        - Have the program error notices been reviewed to determine ifthey pose any limitations for this application'
                        - ls the program name, revision number and date of run inscribed on the output?
                        - Is the program identified on the Calculation Method form' If so, is it listed in chapter 10 of the Engineering Standards Manual?
Other Elements Considered
          ~     If a separate verifier was used for validating these functions or a portion of these functions, sign and initial below.
Based on the foregoing, the calculation is adequate for the purpose intended.
Verifier Signature(s)/Date                                                                       Verifier Initials
                                                          /d6   ys 988-25280 R I (3/98)
 
Page            Cont'd On Page WASHINGTON tulLIC POWER CALCULATIONOUTPUT


==SUMMARY==
==SUMMARY==
Page eicuietion No.CMR-98-0243 Cont'd On Page C Discussion of Results Revision No.0 Four computer runs were used to evaluate the indication in the N1 nozzle safe-end.The first modeled the indication using the normal operational loads of the system.The second model used three transients that could possibly occur in one year interval.These transients were the thermal discontinuity stress, OBE and SSE.This model was used to determine the crack growth expected from the fatigue loading at different crack depths allowing determination of when the cracking would become a significant contributor to crack growth.This allowed the determination that the crack growth would only become significant at the end of the interval selected for the next inspection.
 
The third and fourth models used the adjusted crack length (20:1 ratio)as required by NUREG 0313 Rev.2.The third model used 870 days for the end of the IGSCC crack growth and the fourth used 970 days of operation for the end of IGSCC crack growth as input.The required fatigue cycles for OBE and SSE were then applied to this~crack dimension to determine acceptability for the interval.The results of the computer runs are as follows: The indication will grow to a depth of 1.05" by the end of 970 days if IGSCC is active and the fatigue cycles are experienced.
I>      SUPPLY SYSIVM                                                                        eicuietion No.
In comparing the results to the 1989 ASME Section XI Code Tables IWB-3641-5 and-6.Indication is acceptable for continued operation until for 970 days of operation.
CMR-98-0243 C
The weld will be reinspected prior to 970 days of operation, see PERA 298-0600 CAP 1 PTL A149503.Conclusions Taking into account the following conservatism's:
Discussion of Results                                                                         Revision No.
The weld residual stress distribution used is for an as welded component.
0 Four computer runs were used to evaluate the indication in the N1 nozzle safe-end. The first modeled the indication using the normal operational loads of the system.
The stainless steel safe-end to nozzle weld had MSIP performed on it during R 9.The distribution should be compressive at the ID.2.The stresses are conservatively high due to the use of OBE stresses for steady state therfnal.Also the pressure stress used is the hoop stress not the axial pressure stress.3.No facets are evident during the weld examination that would indicate IGSCC is active.It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld is required.The evaluation demonstrates that under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6.The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking.If the IGSCC phenomena is active the indication will increase in depth to 1.05" by the end of 970 days of operation which is less than the ASME Code allowable.
The second model used three transients that could possibly occur in one year interval. These transients were the thermal discontinuity stress, OBE and SSE. This model was used to determine the crack growth expected from the fatigue loading at different crack depths allowing determination of when the cracking would become a significant contributor to crack growth. This allowed the determination that the crack growth would only become significant at the end of the interval selected for the next inspection.
Y 968 18852 R2 (3/98)  
The third and fourth models used the adjusted crack length (20:1 ratio) as required by NUREG 0313 Rev. 2. The third model used 870 days for the end of the IGSCC crack growth and the fourth used 970 days of operation for the end of IGSCC crack growth as input. The required fatigue cycles for OBE and SSE were then applied to this         ~
~,s 49 SUPPLY SYSTEM CALCULATION METHOD CONTINUATION PAGE Page Coni'd On page il 9 0 o I/i V o e w Caiculation No.CMR-98-0243 Revision No.0 The modeling applies the requirements identified in NRC Generic Letter 88-01.The flaw was evaluated as an intergranular stress corrosion crack using the crack growth rate equation provided in the generic letter.The weld residual stress distribution provided in the letter was also used even though the weld in question had Mechanical Stress Improvement (MSIP)performed on it in 1994.The weld residual stresses are developed from room temperature yield for 304 material (30 ksi)as the normalization stress outlined in the generic letter.The flaw aspect ratio was reviewed and compared to the requirements of NUREG-0313, Rev.2.The aspect ratio was determined to be 12:1 which requires correction in length as the crack grows until an aspect ratio of 20:1 is determined, Therefore, the final crack growth aspect ratio was corrected manually to comply with the requirements of NUREG-0313, Rev.2.The correction for aspect ratio was performed at each time period based upon the computer output for the IGSCC model.These intervals were determined as follows: 290 day intervals were used until final interval of an additional 100 days for a total of 970 days.The flaw length and depth of 970 day value was then used as input into the fatigue model.The fatigue model used one year of expected upset and faulted conditions as required by the Code to assure that the crack will remain within the Code allowable limits and NRC requirements.
crack dimension to determine acceptability for the interval.
REV.BAR Three input files were used to perform the IGSCC and fatigue evaluations.
The results of the computer runs are as follows:
These files were: N1IGSCC.IN IGSCC for normal operations N1FAT.IN Fatigue including one year of thermal discontinuity (1cycle), OBE (300 cycles), SSE (10 cycles)N1FAT1.IN Fatigue incorporating 870 days corrected crack length for NRC 20:1 ratio and the same fatigue cycles for N1FAT.IN N1FAT2.IN Fatigue model for 970 days of operation.
The indication will grow to a depth of 1.05" by the end of 970 days if IGSCC is active and the fatigue cycles are experienced.
The following assumptions and inputs were used in developing each of the models.All Models: The flaw model used was 703 for a semi-elliptical (circumferential) surface crack in a cylinder.(1)Raw Dimensions N1IGSCC.IN The crack used was 3.52" long and 0.29" deep.The half crack was calculated taking 3.52" and N1FAT.IN dividing it by 2 to yield 1.76".(2)N1FAT1.IN The crack.length for this model was the results of the 20:1 aspect ratio required by the NRC for IGSCC cracks.The value used is from the crack depth for 870 days of IGSCC growth that The values used in the model were a length of 17.8" and a depth of 0.89".The half crack was determined by dividing the length by 2 that results in a value of 8.9".N1FAT2.IN For 970 days a 0.935" depth and half crack of 9.35".Crack Growth Laws N1IGSCC.IN The Paris equation used for IGSCC growth was that provided in NUREG-0313 Rev.2.The (4)equation used: 359E-8(dX)'n ksi Pin N1FAT.IN The crack growth rate for fatigue in BWR water environment was determined using the following N1FAT1.IN Paris equation: (3)N1FAT2.IN 6.155E-18(6E)in psi Jin N1IGSCC.IN The LK~value used was 10.0 or 10000 for the fatigue N1FAT.IN N1FAT1 52.IN 968-2529 i R1 (3/98)
In comparing the results to the 1989 ASME Section XI Code Tables IWB-3641-5 and -6. Indication is acceptable for continued operation until for 970 days of operation.
WASHINGTON PUSLIC tOWKR 13 SUPPLY SYSTEM Prepared By/Date T.M.Erwin MANUAL CALCULATI Verified by/Da e Page r O Cont'd On Page BAR Calculation No.CMR-98-243 Revision No.As identified on the summary sheet this CMR is to evaluate the indication found in the N1A nozzle of the RPV for 970 days of operation.
The weld will be reinspected prior to 970 days of operation, see PERA 298-0600 CAP     1 PTL A149503.
The following provides the calculations in support of this evaluation.
Conclusions Taking into account the following conservatism's:
The weld residual stress distribution used is for an as welded component. The stainless steel safe-end to nozzle weld had MSIP performed on it during R 9. The distribution should be compressive at the ID.
: 2. The stresses are conservatively high due to the use of OBE stresses for steady state therfnal. Also the pressure stress used is the hoop stress not the axial pressure stress.
: 3. No facets are evident during the weld examination that would indicate IGSCC is active.
It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld is required. The evaluation demonstrates that under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6. The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking. If the IGSCC phenomena is active the indication will increase in depth to 1.05" by the end of 970 days of operation which is less than the ASME Code allowable.
Y 968 18852 R2 (3/98)
 
~ ,s Page           Coni'd On page CALCULATIONMETHOD                                  il 9 0oI          /i V o e w 49      SUPPLY SYSTEM                            CONTINUATIONPAGE                                Caiculation No.
CMR-98-0243 Revision No.               REV.
0                           BAR The modeling applies the requirements identified in NRC Generic Letter 88-01. The flaw was evaluated as an intergranular stress corrosion crack using the crack growth rate equation provided in the generic letter. The weld residual stress distribution provided in the letter was also used even though the weld in question had Mechanical Stress Improvement (MSIP) performed on it in 1994. The weld residual stresses are developed from room temperature yield for 304 material (30 ksi) as the normalization stress outlined in the generic letter. The flaw aspect ratio was reviewed and compared to the requirements of NUREG-0313, Rev. 2. The aspect ratio was determined to be 12:1 which requires correction in length as the crack grows until an aspect ratio of 20:1 is determined, Therefore, the final crack growth aspect ratio was corrected manually to comply with the requirements of NUREG-0313, Rev. 2. The correction for aspect ratio was performed at each time period based upon the computer output for the IGSCC model. These intervals were determined as follows: 290 day intervals were used until final interval of an additional 100 days for a total of 970 days. The flaw length and depth of 970 day value was then used as input into the fatigue model. The fatigue model used one year of expected upset and faulted conditions as required by the Code to assure that the crack will remain within the Code allowable limits and NRC requirements.
Three input files were used to perform the IGSCC and fatigue evaluations. These files were:
N1IGSCC.IN IGSCC             for normal operations N1FAT.IN             Fatigue including one year of thermal discontinuity ( 1cycle), OBE (300 cycles), SSE ( 10 cycles)
N1FAT1.IN Fatigue           incorporating 870 days corrected crack length for NRC 20:1 ratio and the same fatigue cycles for N1FAT.IN N1FAT2.IN Fatigue           model for 970 days of operation.
The following assumptions and inputs were used in developing each of the models.
All Models: The flaw model used was 703 for a semi-elliptical (circumferential) surface crack in         a cylinder. (1)
Raw Dimensions N1IGSCC.IN The crack used was 3.52" long and 0.29" deep. The half crack was calculated taking 3.52" and N1FAT.IN dividing it by 2 to yield 1.76".                                                                             (2)
N1FAT1.IN The crack. length for this model was the results of the 20:1 aspect ratio required by the NRC for IGSCC cracks. The value used is from the crack depth for 870 days of IGSCC growth that The values used in the model were a length of 17.8" and a depth of 0.89". The half crack was determined by dividing the length by 2 that results in a value of 8.9".
N1FAT2.IN For 970 days a 0.935" depth and half crack of 9.35".
Crack Growth Laws N1IGSCC.IN The Paris equation used for IGSCC growth was that provided in NUREG-0313 Rev. 2. The (4) equation used:
359E 8(dX)     'n   ksi Pin N1FAT.IN             The crack growth rate for fatigue in BWR water environment was determined using the following N1FAT1.IN             Paris equation:                                                                               (3)
N1FAT2.IN 6.155E 18(6E)       in psi Jin N1IGSCC.IN             The LK~ value used was 10.0 or 10000 for the fatigue N1FAT.IN N1FAT1 52.IN 968-2529 i R1 (3/98)
 
Page            Cont'd On Page WASHINGTON PUSLIC tOWKR MANUALCALCULATI                                    r    O 13     SUPPLY SYSTEM                                                                       Calculation No.
CMR-98-243 Prepared By/Date                               Verified by/Da e                               Revision No.
T.M. Erwin BAR As identified on the summary sheet this CMR is to evaluate the indication found in the N1A nozzle of the RPV for 970 days of operation. The following provides the calculations in support of this evaluation.
From ME-02-98-04 computer output for the IGSCC evaluation (pages 22 and 23 of file N1IGSCC.OUT) the following numbers were used to determine the crack depth for 970 days of operation.
From ME-02-98-04 computer output for the IGSCC evaluation (pages 22 and 23 of file N1IGSCC.OUT) the following numbers were used to determine the crack depth for 970 days of operation.
Duration (days)976.3 955.2 Crack Depth 0.9382531 0.9289635 delta of 21.1 days delta of 0.0092896 inches To determine the crack growth/day delta in inches/21.1 days=0.00044026 inches/day 976.3 days-970 days=6.3 days 6.3 days x 0.00044026 inches/day
Duration (days)     976.3           955.2               delta of 21.1 days Crack Depth         0.9382531       0.9289635           delta of 0.0092896 inches To determine the crack growth/day delta in inches /21.1 days = 0.00044026 inches/day 976.3 days - 970 days = 6.3 days 6.3 days x 0.00044026 inches/day = 0.0027736 inches for 970 days 0.9382531- 0.0027736 = .9354824 inches Therefore the crack depth for 970 days is 0.935 inches that was used for input into the OBE and SSE model for the fatigue evaluation to determine the flaw size after the event.
=0.0027736 inches for 970 days 0.9382531-0.0027736=.9354824 inches Therefore the crack depth for 970 days is 0.935 inches that was used for input into the OBE and SSE model for the fatigue evaluation to determine the flaw size after the event.The crack length used was determined by multiplying the flaw depth by 20 to maintain the aspect ratio as required by NUREG 0313 Rev.2.The new input for the flaw depth and half crack for the input file for OBE and SSE is 0.935 inches deep and a half crack of 9.35 inches (file N1FAT2.IN).
The crack length used was determined by multiplying the flaw depth by 20 to maintain the aspect ratio as required by NUREG 0313 Rev. 2. The new input for the flaw depth and half crack for the input file for OBE and SSE is 0.935 inches deep and a half crack of 9.35 inches ( file N1FAT2.IN). All other inputs stay the same as those identified in the calculation.
All other inputs stay the same as those identified in the calculation.
 
WASHINGTON tUbLIC tOWKR 43 SUPPLY SYSTEM Prepared By/Date T.M.Erwin MANUAL CALCULATI Verified by/Dat Page i+005 Calculation No.CMR-98-0243 Revision No.0 Cont'd On Page r oat Table 5 contains the crack growth adjustments made to the computer calculated values as required by NUREG 0310 Rev.2.For IGSCC crack growth the NRC requires an aspect ratio (crack length to depth)to be a minimum of 20:1.To calculate this new length the initial value as found during R13 was first multiplied by 20 to obtain the new crack length.This was repeated for subsequent intervals and by reviewing the output data for the IGSCC crack growth depth for estimated operational days between outages.The maximum length and depth used to complete the fatigue evaluation was determined after 970 days of operation, these values are 0.935" deep and 18.7" in length.Days 290 580 870 970 Table 5 Depth=in.0.29 0.544 0.746 0.89 0.935 New Crack Length=in.
Page            Cont'd On Page WASHINGTON tUbLIC tOWKR MANUALCALCULATI                                      i+005                    r  oat 43     SUPPLY SYSTEM                                                                         Calculation No.
5.8 10.88 14.92 17.8 18.7 The Input file for N1FAT1.IN contains the flaw length of 18.7" and depth of 0.935".This flaw depth and length was then ran for one year of fatigue cycles due to discontinuity, OBE and SSE in accordance with ASME Code 1989 Section XI Rules.The final length was determined to be 18.712" and 1.05" deep.These values for Section XI Table IWB-3641-5 and IWB-3641-6 are: lf=18.71" a~=1.05" To determine the Code acceptability of the flaws Tables IWB-3641-5 and-6 are used to determine aand a,.These are the maximum flaw depths for normal and faulted loading conditions.
CMR-98-0243 Prepared By/Date                                 Verified by/Dat                               Revision No.
Acceptability is based on af being less than these two values.The following calculations are used in conjunction with the referenced Section XI Tables to determined aand a<.The indication falls into what is classified as weld zone per Fig.IWB-3641-1.
T.M. Erwin                                                                                      0 Table 5 contains the crack growth adjustments made to the computer calculated values as required by NUREG 0310 Rev. 2. For IGSCC crack growth the NRC requires an aspect ratio (crack length to depth) to be a minimum of 20:1. To calculate this new length the initial value as found during R13 was first multiplied by 20 to obtain the new crack length. This was repeated for subsequent intervals and by reviewing the output data for the IGSCC crack growth depth for estimated operational days between outages. The maximum length and depth used to complete the fatigue evaluation was determined after 970 days of operation, these values are 0.935" deep and 18.7" in length.
This requires the flaw to be evaluated using Tables IWB 3641-5 and-6.The use of these Tables requires the calculation of the defined stress ratio and the flaw length to circumference ratio to determine the allowable depth to thickness ratio.This value is used to determine the maximum flaw depth.
Table 5 Days                    Depth=in.       New Crack Length=in.
W I%V'g 49 SUPPLY SYSTEM Prepared By/Oate T.M;Efwin MANUAL CALCULATION Verified by/0 t Page oo (.Conrd On Page REV.BAR Calculation No.CMR-98-0243 Revision No.0 Circumference of the nozzle is equal to 24+3.14=75.36" (based on a nominal diameter of 24")Depth/Thickness ratio=1.05/2.0"=.525 I</Circumference ratio=18.7"/75.36"=.248 NORMAL OPERATING (INCLUDING UPSET AND TEST)CONDITIONS For Table IWB-3641-5 the stress ratio is determined by the following equation: Stress Ratio=M(P+Ps+P)I 2 77 I S(From the referenced Table)Using the previous define stresses and an M value of 1.0 (for shielded metal arc welds when OD<24")the above equation for normal operating and upset conditions is equal to: DWT+OBE+Pressure
0.29                  5.8 290                        0.544                10.88 580                        0.746                14.92 870                        0.89                  17.8 970                        0.935                  18.7 The Input file for N1FAT1.IN contains the flaw length of 18.7" and depth of 0.935". This flaw depth and length was then ran for one year of fatigue cycles due to discontinuity, OBE and SSE in accordance with ASME Code 1989 Section XI Rules. The final length was determined to be 18.712" and 1.05" deep.
+OBE+Thermal Discontinuity 0.286+2.76+7.79+2.76+18.73
These values for Section XI Table IWB-3641-5 and IWB-3641-6 are:
=32.326 ksi NOTE: OBE is added twice conservatively to bound the normal operating and thermal stresses.Stress Ratio=32.326/2.77/16.65
lf =18.71" a~ = 1.05" To determine the Code acceptability of the flaws Tables IWB-3641-5 and -6 are used to determine         aand a,.
=.701 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.6.Therefore the maximum flaw=2.0*.6=1.2" deep since 1.05"<1.2'he flaw is acceptable per Table IWB-3641-5 EMERGENCY AND FAULTED CONDITIONS For Table IWB-3641-6 the stress ratio is determined using a similar equation as above with the exception of the SSE stress being substituted for one of the OBE and 2.77 being replace with 1.39.(7)Stress Ratio=M(P+Ps+P)/I (39/S (From the referenced Table)Therefore:
These are the maximum flaw depths for normal and faulted loading conditions. Acceptability is based on af being less than these two values. The following calculations are used in conjunction with the referenced Section XI Tables to determined aand a<.
34.021/1.39/16.65=1.47 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.54 using linear interpolation as allowed by the table.Therefore tha maximum flaw=2.0*0.54=.1.08" since 1.05"<1.08'he flaw is acceptable per Table IWB-3641-6 Conclusion The flaw meets all the Code Section XI requirements and the N1 nozzle safe-end is acceptable for use without examination for 970 days of operation.
The indication falls into what is classified as weld zone per Fig. IWB-3641-1. This requires the flaw to be evaluated using Tables IWB 3641-5 and -6. The use of these Tables requires the calculation of the defined stress ratio and the flaw length to circumference ratio to determine the allowable depth to thickness ratio. This value is used to determine the maximum flaw depth.
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Page           Conrd On Page MANUALCALCULATION                                oo (.
49      SUPPLY SYSTEM                                                                    Calculation No.
CMR-98-0243 Prepared By/Oate                                    Verified by/0 t                        Revision No.
T.M; Efwin                                                                                0 REV.
BAR Circumference of the nozzle is equal to 24+3.14 = 75.36" (based on a nominal diameter of 24")
Depth   / Thickness ratio = 1.05/2.0" = .525 I< / Circumference ratio = 18.7" /75.36" = .248 NORMAL OPERATING (INCLUDING UPSET AND TEST) CONDITIONS For Table IWB-3641-5 the stress ratio is determined by the following equation:
Stress Ratio = M(P+ Ps + P ) I 2 77 I S(From the referenced Table)
Using the previous define stresses and an M value of 1.0 (for shielded metal arc welds when OD<24")the above equation for normal operating and upset conditions is equal to:
DWT+OBE+Pressure +OBE+Thermal Discontinuity 0.286+2.76+7.79+2.76+18.73 = 32.326 ksi NOTE: OBE is added twice conservatively to bound the normal operating and thermal stresses.
Stress Ratio = 32.326   /2.77/16.65 =   .701 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.6.
Therefore the maximum flaw = 2.0       *.6 = 1.2" deep since 1.05" <   1.2'he   flaw is acceptable per Table IWB-3641-5 EMERGENCY AND FAULTED CONDITIONS For Table IWB-3641-6 the stress ratio is determined using a similar equation as above with the exception of the SSE stress being substituted for one of the OBE and 2.77 being replace with 1.39.                           (7)
Stress Ratio =     M(P+ Ps +P )/I ( 39/S         (From the referenced Table)
Therefore: 34.021 /1.39 /16.65 = 1.47 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.54 using linear interpolation as allowed by the table.
Therefore tha maximum flaw = 2.0
* 0.54 =.1.08" since 1.05" <   1.08'he flaw is acceptable   per Table IWB-3641-6 Conclusion The flaw meets all the Code Section XI requirements and the N1 nozzle safe-end is acceptable for use without examination for 970 days of operation.
 
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Latest revision as of 12:57, 29 October 2019

Calculation Mod Record CMR-98-0243, Fracture Mechanics Evaluation of N1A Nozzle Safe End.
ML17292B659
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Issue date: 10/06/1998
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CMR-98-0243, CMR-98-243, NUDOCS 9905130172
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SUPPLEMENTAL INFORMATION ANALYTICALEVALUATIONOF INSERVICE INSPECTION EXAMINATIONRESULTS Attachment B CMR-98-0243, "Fracture Mechanics Evaluation of N1A Nozzle Safe End."

9905i30i72 990429 PDR ADOCK 05000397 8 PDR

BDC Page WA5HINGTON FUSLIC POWER CALCULATIONMODIFICATIONRECORD A//F/

49 SUPPLY SYSI'l& Qp/jo) q~g,L CMR Page Cont'd On Page Gale. Modification No. Applies lo: Calcuhtion No. Rev.

CMR-98-0243 ME-02-98-04 0 This CMR has been filed against the current revision of the identified calculation, and must be closed out at a future date. All technical data needed to actually update the calculation has been included in this CMR package.

1. Purpose of CMR This CMR provides the new fracture mechanics calculations and computer runs required to adjust the examination schedule for the N1 nozzle indication to 970 days versus 870 days evaluated in the initial calculation. The change to the examination time interval was required because of the change in the outage date.
2. Input Data Summary (Use additional sheets if necessary)

The data inputs were the same as those used in the original calculations for the IGSCC and Fatigue evaluations. The change was made to the initial crack length used in the fatigue evaluation for the OBE and SSE computer run. The initial crack depth was taken from the IGSCC computer output for 970 days of operation. The initial length was determined as in the original calculation by multiplying the depth by 20 as required by NUREG 0313 Rev 2. The applied cycles required for OBE and SSE were then applied to this crack size and the resulting final crack depth compared to the ASME Code tables as in the original calculation to determine acceptability. It was determined that the 970 days of operation is acceptable base on the results of this CMR.

3. Predicted Result or conclusion When this CMR is incorporated into the calculation, the resultslconclusions viill be:

It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld has to occur. The evaluation demonstrates under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6. The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking. If the IGSCC phenomena is active the indication will increase in depth to 1.05" (including OBE and SSE) by the end of 970 days of operation, which is less than the ASME Code allowable.

Qereare No o.<her C/ri/rs erron'rrst C ic- I>/- '8/ "<rr ro'/.

'Ae/ nra A/,;+or(e egal+ h/ '

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Prepared by I Date Verified by I Date Tom Erwin I 0/5/88 c lad gs This CMR has been incorporated into Revision of the identified calculation Signature Date 968-19954 R2 (3/98)

Conrd On Page WASHINGTON bUbLIC ?OWER VERIFICATIONCHECKLIST FOR Page k3 SUPPLY SYSTEM CALCULATIONSAND CMRs Calculation/CMR CMR-.98-0243 Revision 0 was verified using the following methods:

g Checklist Below Q Alternate Calculations Checklist Item Initial Clear Statement of purpose of analysis Methodology clearly stated and sufficiently detailed and appropriate to proposed application Logical consistency of analysis

~ Completeness of documenting references

~ Completeness of documenting and updating output interface documents Completeness of input Accuracy of input data Consistency of input data with approved criteria Completeness in stating assumptions Validity of assumptions Calculation sufficiently detailed

~ Arithmetical accuracy

~ Physical units specified and correctly used Reasonableness of output conclusion Supervisor independency check (if acting as Verifier)

- Did not specify analysis approach

- Did not rule out specific analysis options

- Did not establish analysis inputs

~ If a computer program was used:

- Is the program appropriate for the proposed application?

- Have the program error notices been reviewed to determine ifthey pose any limitations for this application'

- ls the program name, revision number and date of run inscribed on the output?

- Is the program identified on the Calculation Method form' If so, is it listed in chapter 10 of the Engineering Standards Manual?

Other Elements Considered

~ If a separate verifier was used for validating these functions or a portion of these functions, sign and initial below.

Based on the foregoing, the calculation is adequate for the purpose intended.

Verifier Signature(s)/Date Verifier Initials

/d6 ys 988-25280 R I (3/98)

Page Cont'd On Page WASHINGTON tulLIC POWER CALCULATIONOUTPUT

SUMMARY

I> SUPPLY SYSIVM eicuietion No.

CMR-98-0243 C

Discussion of Results Revision No.

0 Four computer runs were used to evaluate the indication in the N1 nozzle safe-end. The first modeled the indication using the normal operational loads of the system.

The second model used three transients that could possibly occur in one year interval. These transients were the thermal discontinuity stress, OBE and SSE. This model was used to determine the crack growth expected from the fatigue loading at different crack depths allowing determination of when the cracking would become a significant contributor to crack growth. This allowed the determination that the crack growth would only become significant at the end of the interval selected for the next inspection.

The third and fourth models used the adjusted crack length (20:1 ratio) as required by NUREG 0313 Rev. 2. The third model used 870 days for the end of the IGSCC crack growth and the fourth used 970 days of operation for the end of IGSCC crack growth as input. The required fatigue cycles for OBE and SSE were then applied to this ~

crack dimension to determine acceptability for the interval.

The results of the computer runs are as follows:

The indication will grow to a depth of 1.05" by the end of 970 days if IGSCC is active and the fatigue cycles are experienced.

In comparing the results to the 1989 ASME Section XI Code Tables IWB-3641-5 and -6. Indication is acceptable for continued operation until for 970 days of operation.

The weld will be reinspected prior to 970 days of operation, see PERA 298-0600 CAP 1 PTL A149503.

Conclusions Taking into account the following conservatism's:

The weld residual stress distribution used is for an as welded component. The stainless steel safe-end to nozzle weld had MSIP performed on it during R 9. The distribution should be compressive at the ID.

2. The stresses are conservatively high due to the use of OBE stresses for steady state therfnal. Also the pressure stress used is the hoop stress not the axial pressure stress.
3. No facets are evident during the weld examination that would indicate IGSCC is active.

It has been determined that WNP-2 may operate for 970 days before reexamination of the nozzle to safe-end weld is required. The evaluation demonstrates that under the worst imposed loading conditions the flaw meets the acceptance criteria of the ASME Section XI IWB-3641-5 and 3641-6. The main fracture mechanism that will propagate the flaw is intergranular stress corrosion cracking. If the IGSCC phenomena is active the indication will increase in depth to 1.05" by the end of 970 days of operation which is less than the ASME Code allowable.

Y 968 18852 R2 (3/98)

~ ,s Page Coni'd On page CALCULATIONMETHOD il 9 0oI /i V o e w 49 SUPPLY SYSTEM CONTINUATIONPAGE Caiculation No.

CMR-98-0243 Revision No. REV.

0 BAR The modeling applies the requirements identified in NRC Generic Letter 88-01. The flaw was evaluated as an intergranular stress corrosion crack using the crack growth rate equation provided in the generic letter. The weld residual stress distribution provided in the letter was also used even though the weld in question had Mechanical Stress Improvement (MSIP) performed on it in 1994. The weld residual stresses are developed from room temperature yield for 304 material (30 ksi) as the normalization stress outlined in the generic letter. The flaw aspect ratio was reviewed and compared to the requirements of NUREG-0313, Rev. 2. The aspect ratio was determined to be 12:1 which requires correction in length as the crack grows until an aspect ratio of 20:1 is determined, Therefore, the final crack growth aspect ratio was corrected manually to comply with the requirements of NUREG-0313, Rev. 2. The correction for aspect ratio was performed at each time period based upon the computer output for the IGSCC model. These intervals were determined as follows: 290 day intervals were used until final interval of an additional 100 days for a total of 970 days. The flaw length and depth of 970 day value was then used as input into the fatigue model. The fatigue model used one year of expected upset and faulted conditions as required by the Code to assure that the crack will remain within the Code allowable limits and NRC requirements.

Three input files were used to perform the IGSCC and fatigue evaluations. These files were:

N1IGSCC.IN IGSCC for normal operations N1FAT.IN Fatigue including one year of thermal discontinuity ( 1cycle), OBE (300 cycles), SSE ( 10 cycles)

N1FAT1.IN Fatigue incorporating 870 days corrected crack length for NRC 20:1 ratio and the same fatigue cycles for N1FAT.IN N1FAT2.IN Fatigue model for 970 days of operation.

The following assumptions and inputs were used in developing each of the models.

All Models: The flaw model used was 703 for a semi-elliptical (circumferential) surface crack in a cylinder. (1)

Raw Dimensions N1IGSCC.IN The crack used was 3.52" long and 0.29" deep. The half crack was calculated taking 3.52" and N1FAT.IN dividing it by 2 to yield 1.76". (2)

N1FAT1.IN The crack. length for this model was the results of the 20:1 aspect ratio required by the NRC for IGSCC cracks. The value used is from the crack depth for 870 days of IGSCC growth that The values used in the model were a length of 17.8" and a depth of 0.89". The half crack was determined by dividing the length by 2 that results in a value of 8.9".

N1FAT2.IN For 970 days a 0.935" depth and half crack of 9.35".

Crack Growth Laws N1IGSCC.IN The Paris equation used for IGSCC growth was that provided in NUREG-0313 Rev. 2. The (4) equation used:

359E 8(dX) 'n ksi Pin N1FAT.IN The crack growth rate for fatigue in BWR water environment was determined using the following N1FAT1.IN Paris equation: (3)

N1FAT2.IN 6.155E 18(6E) in psi Jin N1IGSCC.IN The LK~ value used was 10.0 or 10000 for the fatigue N1FAT.IN N1FAT1 52.IN 968-2529 i R1 (3/98)

Page Cont'd On Page WASHINGTON PUSLIC tOWKR MANUALCALCULATI r O 13 SUPPLY SYSTEM Calculation No.

CMR-98-243 Prepared By/Date Verified by/Da e Revision No.

T.M. Erwin BAR As identified on the summary sheet this CMR is to evaluate the indication found in the N1A nozzle of the RPV for 970 days of operation. The following provides the calculations in support of this evaluation.

From ME-02-98-04 computer output for the IGSCC evaluation (pages 22 and 23 of file N1IGSCC.OUT) the following numbers were used to determine the crack depth for 970 days of operation.

Duration (days) 976.3 955.2 delta of 21.1 days Crack Depth 0.9382531 0.9289635 delta of 0.0092896 inches To determine the crack growth/day delta in inches /21.1 days = 0.00044026 inches/day 976.3 days - 970 days = 6.3 days 6.3 days x 0.00044026 inches/day = 0.0027736 inches for 970 days 0.9382531- 0.0027736 = .9354824 inches Therefore the crack depth for 970 days is 0.935 inches that was used for input into the OBE and SSE model for the fatigue evaluation to determine the flaw size after the event.

The crack length used was determined by multiplying the flaw depth by 20 to maintain the aspect ratio as required by NUREG 0313 Rev. 2. The new input for the flaw depth and half crack for the input file for OBE and SSE is 0.935 inches deep and a half crack of 9.35 inches ( file N1FAT2.IN). All other inputs stay the same as those identified in the calculation.

Page Cont'd On Page WASHINGTON tUbLIC tOWKR MANUALCALCULATI i+005 r oat 43 SUPPLY SYSTEM Calculation No.

CMR-98-0243 Prepared By/Date Verified by/Dat Revision No.

T.M. Erwin 0 Table 5 contains the crack growth adjustments made to the computer calculated values as required by NUREG 0310 Rev. 2. For IGSCC crack growth the NRC requires an aspect ratio (crack length to depth) to be a minimum of 20:1. To calculate this new length the initial value as found during R13 was first multiplied by 20 to obtain the new crack length. This was repeated for subsequent intervals and by reviewing the output data for the IGSCC crack growth depth for estimated operational days between outages. The maximum length and depth used to complete the fatigue evaluation was determined after 970 days of operation, these values are 0.935" deep and 18.7" in length.

Table 5 Days Depth=in. New Crack Length=in.

0.29 5.8 290 0.544 10.88 580 0.746 14.92 870 0.89 17.8 970 0.935 18.7 The Input file for N1FAT1.IN contains the flaw length of 18.7" and depth of 0.935". This flaw depth and length was then ran for one year of fatigue cycles due to discontinuity, OBE and SSE in accordance with ASME Code 1989 Section XI Rules. The final length was determined to be 18.712" and 1.05" deep.

These values for Section XI Table IWB-3641-5 and IWB-3641-6 are:

lf =18.71" a~ = 1.05" To determine the Code acceptability of the flaws Tables IWB-3641-5 and -6 are used to determine aand a,.

These are the maximum flaw depths for normal and faulted loading conditions. Acceptability is based on af being less than these two values. The following calculations are used in conjunction with the referenced Section XI Tables to determined aand a<.

The indication falls into what is classified as weld zone per Fig. IWB-3641-1. This requires the flaw to be evaluated using Tables IWB 3641-5 and -6. The use of these Tables requires the calculation of the defined stress ratio and the flaw length to circumference ratio to determine the allowable depth to thickness ratio. This value is used to determine the maximum flaw depth.

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Page Conrd On Page MANUALCALCULATION oo (.

49 SUPPLY SYSTEM Calculation No.

CMR-98-0243 Prepared By/Oate Verified by/0 t Revision No.

T.M; Efwin 0 REV.

BAR Circumference of the nozzle is equal to 24+3.14 = 75.36" (based on a nominal diameter of 24")

Depth / Thickness ratio = 1.05/2.0" = .525 I< / Circumference ratio = 18.7" /75.36" = .248 NORMAL OPERATING (INCLUDING UPSET AND TEST) CONDITIONS For Table IWB-3641-5 the stress ratio is determined by the following equation:

Stress Ratio = M(P+ Ps + P ) I 2 77 I S(From the referenced Table)

Using the previous define stresses and an M value of 1.0 (for shielded metal arc welds when OD<24")the above equation for normal operating and upset conditions is equal to:

DWT+OBE+Pressure +OBE+Thermal Discontinuity 0.286+2.76+7.79+2.76+18.73 = 32.326 ksi NOTE: OBE is added twice conservatively to bound the normal operating and thermal stresses.

Stress Ratio = 32.326 /2.77/16.65 = .701 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.6.

Therefore the maximum flaw = 2.0 *.6 = 1.2" deep since 1.05" < 1.2'he flaw is acceptable per Table IWB-3641-5 EMERGENCY AND FAULTED CONDITIONS For Table IWB-3641-6 the stress ratio is determined using a similar equation as above with the exception of the SSE stress being substituted for one of the OBE and 2.77 being replace with 1.39. (7)

Stress Ratio = M(P+ Ps +P )/I ( 39/S (From the referenced Table)

Therefore: 34.021 /1.39 /16.65 = 1.47 Using the Stress Ratio and the Circumferential Ratio the allowable Depth to thickness ratio from Table IWB-3641-5 is 0.54 using linear interpolation as allowed by the table.

Therefore tha maximum flaw = 2.0

  • 0.54 =.1.08" since 1.05" < 1.08'he flaw is acceptable per Table IWB-3641-6 Conclusion The flaw meets all the Code Section XI requirements and the N1 nozzle safe-end is acceptable for use without examination for 970 days of operation.

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