ML20100Q612
| ML20100Q612 | |
| Person / Time | |
|---|---|
| Site: | San Onofre  |
| Issue date: | 10/05/1993 |
| From: | Elakily N SOUTHERN CALIFORNIA EDISON CO. |
| To: | |
| Shared Package | |
| ML20100Q610 | List: |
| References | |
| M-DSC-280, M-DSC-280-R01, M-DSC-280-R1, NUDOCS 9603120060 | |
| Download: ML20100Q612 (292) | |
Text
-.. -
CALCULATIONggg TITLE PAGEh /j PRELIM.CCNNO. PAGE OF r L A ,_ i , . a 2 eu CCN CONVERSION :
Calc. No. -DM- 2 6 O DCP/MMP/FIDC . & Rev. - - -- g-- r-' CCN NO. CCN.
Subject 90N GR 2 PRINAR V PLAttr M Arr-1iP QTBe e GG rA N K f)F ARA DfF Sheet /
System Number / Primary Station System Designator i2o3/EGA SONGS Unit 2. . . O. ass. If Tech. Spec. Affectmg? NO YES, Section No. Equipment Tag No. N/k CONTROLLED PROGRAM IDATABASE NAME(S)
COMPUTER ]#ROGRAM VERSIOM7tELEASE NO.(S)
PROGRAM / DATABASE @LSO. LISTED BELOW DATABASE IN ACCORDANCE WTTH NES&L 41-5-1 RECORD OF ISSUES REV. PREPARED APPROVED DISC. (Print name/ initial) (Signature) 3 3 ,
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This calc. was prepared lor the identded DCP/MMP. DCP comple6on and furnopt acceptance to verited by reevet of a mornorandum dweeting DCN Corwersson, upon seempt,this caic. s.preserva the a.euia condition. Wemo date ,Ify, , 7 ; by [hyc h SCE 24121-1 REY. 991 y,g, g //
9603120060 960307 O " " "*'** '*"
CALCULATION CROSS-INDEX I ICCN NO./"
eactiu. CCN No.
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Eq S023-407-3-97 0 S023-407-3-97 0 YES IDCN S-1
[ #/e/r:M. 5 S023-407-3-64 1 S023-407-3-63 3 S023 407-3-63 3 YES IDCN S-2 <
S023 407-3-61 2 h 43 FCN F-7522M d24 FCN F-7854M FCN F 8348M FCN F-7521M S023-407-3-63 pt.k FCN F-7800M d\ d ""'*"
FCN F-8186M FCN F-8591M p FCN F-7520M FCN F-7836M g' AYq > FCN F-7866M
' FCN r.3233M (CN F-8235M FCN F-8591M FCN F-8591M CE 20-424 REV O 7/92 [
REFERENCE:
NES&L 24 715]
NES&L DEPARTMENT CALCULATION SHEET =Lo. ,A, C, l CCN CONVER$10N Project or DCP/lG4P SONGS 2 Calc No. M-DSC-280 CCN No. CCN -
subject See Title Sheet Sheet No. S j REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AKILY 7/27/1993 JUNGAORdd. 7/27/1993 i V El -JikILY 10)il43 FC- /%1n l
l l
l TABLE OF CONTENTS I Sheet Number CALCULATION TITLE SHEET . . .............. 1 CALCULATION CROSS REFERENCE .............. 2 TABLE OF CONTENTS ................... 3 1 PURPOSE ........................ 4 2 RESULTS/ CONCLUSIONS .................. 6 )
3 ASSUMPTIONS . . .................... 10 4 DESIGN INPUT . . . . . . . . . . . . . . . . . . . . . . 11 5 METHODOLOGY . . .................... 17 l
6 REFERENCES . . . . . . . . . . . . . . . . . . . . . . . 27 7 NOMENCLATURE . . . . . . . . . . . . . . . . . . . . . . 29 8 CALCU LATIONS . . . . . . . . . . . . . . . . . . . . . . 31 9 APPENDICES APPENDIX A - PPMS DESIGN REPORT . . . . . . . . . . . 84 APPENDIX B - PPMS TANK STICK MODEL ......... 179 APPENDIX C - ANSYS INPUT FILES . . ......... 194 APPENDIX D - REFERENCE DOCUMENTS . ......... 204 APPENDIX E - STATISTICAL ANALYSIS OF RADIOGRAPHIC EXAMINATION DATA . . . . . . . . . . . . 236 APPENDIX F - FRACTURE MECHANICS EVALUATION ..... 264 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n ,. . ,, ,
Project or DCP/>NP SONGS 2 Calc No.
CCN CONVERSION M-DSC-280 cCN NO, CCN -
subject See Title Sheet Sheet No. h REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE 0 NABIL M. EL At:ILY 7/27/1993 JUNGAOR((. 7/27/1993 1 y-n-gku-y w)sje3 pg. '%s
- 1. PURPOSE / BACKGROUND 1
The existing Component Cooling Water (CCW) system at SONGS 2 and 3 consists of I two redundant trains (critical loops), and one non-critical loop which can be aligned to either one of the critical loops. The make-up water to the CCW surge tank is supplied by the seismically-qualified mobile fire tankers to ensure adequate water supply for a 7-day period, using the temporary connection, as required by NRC Q&R 010.49. This arrangement, however, is very labor intensive to operate, and the tankers may require several refills to perform their function for the desired 7-day time period.
4 To eliminate the reliance of the CCW system on the fire tankers for the make-up water, the primary make-up water system will be integrated into the CCW system to provide the necessary supply of make-up water. The make-up system will be modified to supply water to the CCW critical loops following loss of normal make-up from the nuclear service water system. It will provide the necessary water inventory to compensate for the maximum allowable leak from both CCW critical loops for a period of seven days.
The make-up system of each unit includes a Primary Plant Make-Up Storage (PPMS) tank, T-056 for Unit 2 and T-055 for Unit 3. These tanks were originally designed to API-620, 5th. Edition, and constructed and tested to API-650, 5th.
Edition; and were classified as. Seismic Class II components. Both tanks will be upgraded to Quality Class II, Seismic Category I to establish ASME Code,Section III, Class 3 equivalency without ASME stamping. This tank upgrade is necessary in order to qualify as an integral part of the CCW system, as explained above.
Comparison between the API 650 Code, which was the basis for the original tank construction and testing, and the ASME Code was made to identify and reconcile the differences between the requirements of the two codes. These differences will be resolved, as part of the tank upgrade analysis.
The purpose of this calculation is to document the analyses, and the Code reconciliation performed to upgrade SONGS 2 PPMS tank to seismic class I, and to qualify these tanks per ASME Code,Section III, Class 3 to meet the requirements described above. This calculation includes the analyses and ASME Code reconciliation performed to achieve the desired tank upgrade.
SCE 26-426 NEW 4/90
l i
NES&L DEPARTMENT l CALCULATION SHEET =n No . ,Ax ,,
l CCN CONVERSION l Pr2 ject or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN N3. CCN -
subject See Title Sheet sheet No. I REV ORIGINATOR DATE IKE DATE REV ORIGINATOR DATE IRE DATE 1 NA81L M. EL AKILY 8/20/1993JUNCA04[f, ##hg j l
?* .6
! 4 1
Additional supporting calculations are provided in section 8. The design calculation performed by Structural Integrity Associates is provided in Appendix A. Appendix B, provides the development of the tank shell stick model. ANSYS i input files are provided in Appendix C; and in Appendix D some reference i documents are compiled. The statistical analysis for the radiographic sampling results are provided in Appendix E. Appendix F provides the results of the
- fracture mechanics evaluation made for a bounding size defect.
Revision 1 is issued to incorporate comments made by Quality Assurance (QA).
These comments have minor impact on the results, and do not impact the previous conclusions.
This analysis is for SONGS Unit-2 only.
4 1
I 4
1 SCE 26426 NEW 4/90 i
NES&L DEPARTMENT CALCULATION SHEET ="me. _ ,,
Project or DCP/MMP SONGS 2 cale No.
CCN CONVIR$10N M-DSC-280 CCN No. CCN -
subject See Title Sheet 5 sh t No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NASIL N. EL-AX:!LY 7/27/1993 JUNGAOR[f, 7/27/1993
- / f> cc-4by W3/43 f G. "/dn I
{ 2. RESULTS/ CONCLUSIONS i
- 1. For the existing tanks to meet the seismic loads and Generic Implementation Procedure (GIP) it is recommended that each tank be reinforced by 36 i
vertical stringers and 34 additional anchor bolts. Details can be found in i
Appendix A and Reference 1 (a copy is attached in Appendix D).
1
' 2. Anchor bolt chairs are to be replaced by a new ring-type chairs. Details can be found in Appendix A, and Reference 1 (a copy is attached in Appendix 4
D).
4 4
' 3. The water inside the tank is expected to slosh against the roof. However, the roof was shown to be capable of withstanding the sloshing loads during a DBE seismic event.
- 4. A 1/4" thick reinforcing pad is to be added to the man hole of each tank.
Details are given in Appendix A, and Reference 1 (a copy is attached in Appendix D).
- 5. Reinforcing pads are to be added to some nozzles so that local stresses in the shell do not exceed their allowables. See Section 8 for a list of the j nozzles requiring reinforcing pads.
i
- 6. Some anchor bolts may be moved radially out a distance up to 15/16" to avoid interference with the rebars in the concrete base without exceeding any of the allowable stress limits. Similarly, anchor bolt chairs may be 4
i moved up to 4" in the circumferential direction from their nominal position to avoid interference with tank attachments.
1
- 7. The existing tank wall-to-bottom weld is within the allowable of the we.1d j material .
SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ==iC,.. ,Ax ,,
CCN CONVERSION Project or DCP/ftqP SONGS 2 cate no. M-DSC-280 CCN No. CCN -
subject See Title Sheet sheet No. 7 )
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL Aa:!LY 7/27/1993 JUNGAORh(,, 7/27/1993 I V-GL.-A kt(J( !*ll}93 TL 'il093 '
- 8. The modified tank has been evaluated for buckling per the Generic Implementation Procedure (GIP) for Seismic Verification of Nuclear Plant Equipment, Revision 2 (Reference 17, Appendix A). This evaluation shows that the modified tank meets the GIP recuirements.
Furthermore, the tank has been evaluatec for buckling at higher elevations, l
above the reinforcing stringers, using Code Case N-284 and shown to be '
acceptable. It should be noted that this additional evaluation, at higher elevations, is not required by the GIP. It was performed basically to ensure that the analysis covers the entire tank shell height.
Also, the tank does not have any large asymmetric openings; therefore, axisymmetric analysis techniques should be applicable.
l 1
- 9. ASME Code reconciliation is summarized below:
e A detailed ASME Code reconciliation is included in the PPMS tank design report (Appendix A, Sections 10 and 11). Results can be summarized as follows:
(a) Tank Shell Design, the minimum tank shell requirements of ND-3324.3, which is referred to by ND-3842, are satisfied at all elevations.
(b) Tank Bottom Design, the requirements of ND-3831 are satisfied by the tank bottom. The foundation also meets the requirements of ND-3831, since the PPMS tanks were built to the standards of API-650.
(c) Tank Roof Design, the tank roof satisfies all the requirements of ND-3856. Furthermore, it is shown in Appendix A that the roof, and the junction to the cylindrical shell will withstand the water pressure caused by sloshing.
sCE 26-426 NEW 4/90
l NES&L DEPARTMENT l CALCULATION SHEET =m. ,Au ,, !
CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CcN no. cCN -
subject See Title Sheet sheet No. b REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 NABIL M. EL-AKILY 8/20/1993 JUN GAOR b .
@fs.+
1
(
(d) Tank Manway, the tank manway, reinforced by a 0.25" thick plate, meets the requirements of ND-3332.
(e) Code Stress Limits, the stresses in the tank shell meets the l requirements of ND-3821.5 under Design, Operating Basis Earthquake (OBE), and Design Basis Earthquake (DBE) conditions.
1
- A survey of SONGS-2 tank, T056, was performed for roundness at elevations l 7' above the bottom and 6' below the top. Results of the survey are attached in Appendix D. Based on these results, it is concluded the tank A meets the out-of-roundness requirements of the ASME Code (maximum out-of- /'\
roundness is 0.22' per the survey results; maximum allowed per Section ND-4224 is 0.4', as shown in Section 8).
e The National Board Inspection Code (NBIC) procedure for State approval is not applicable since atmospheric tanks are exempted by the State of California (California Code of Regulations, Title 8, Chapter 4, dated 5/1/1992). However, tank design and modification will be performed to the ASME Code,Section III.
- The Certified Material Test Reports (CMTRs), and all other documentation required to establish ASME Code equivalency are not part of the scope of this calculation. This issue is addressed separately. l l
- The tank will be pressure tested according to ASME Code,Section III, l Subsection ND-6000 requirements after the modifications are implemented. l Details of the tank structural modifications can be found in the attached l Interim Design Change Notice (see Appendix D for a copy of this IDCN). i 1
1 e The results of the radiographic survey of the weld seams of Unit-2 PPMS tank revealed unacceptable defect sizes that range from 1/32" long to 4.875". The bulk of the defects is below 1/4" long. A statistical analysis I was performed to attempt to describe tN worst defect that can exist in the welding with 95% reliability and 95% confidence level. Result of the SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::,: ;NNO. ,A , ,, l l
CCN CONVERSION Project or DCP/MHP SONGS 2 Calc No. M-DSC-280 cCN he. CCN - l i
subject See Title Sheet 4 sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 NABIL M. EL-AKILY 8/20/1993 JUNGAOR[-[, '0/
4
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\
l statistical analysis, based on sample size of 60 radiographs that represent a population of defects of flaws 283, showed that the worst defect h described above to be less than 1.625". l i
l e The statistical analysis was followed by fracture mechanics analysis of maximum defect size 5", that was assumed to exist at the highest stress location of the tank shell. The defect was analyzed by two methods: (1) l l
The defect was assumed to be infinitely long, and its depth is equal to ;
half the thickness of the shell, and (2) a 5" through-wall defect was l assumed. Results of the analysis showed that such a defect is acceptable with factor of safety 3.
Revision 1 results are in agreement with previous results with only minor differences, which do not impact the calculation conclusions. As mentioned in I Section 1 of this calculation, Revision 1 is issued to incorporate the comments made by Quality Assurance.
Results of this calculation do not impact Technical Specifications or Surveillance Procedures.
SCE 26-426 NEW 4/90
NES&L DEPARTMENT
- CALCULATION SHEET = "1 & ,. . ,,
Project or DCP/letP SONGS 2 Calc No.
CCN CONVER$10N '
M-DSC-280 CcN No. CCN -
subject See Title Sheet sheet No.
I REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE !RE DATE D NABIL M. EL AKILY 7/27/1993 JUN GAOR k . 7/27/1993
/ p G L-% u_ f bl!M3 76 ~/645
- 3. ASSUMPTIONS
- 1. The nozzles, and the ladder attached to the PPMS tank were not included in the finite element models. It is assumed that their effect on the anchor bolt load distribution is negligible, since their weight is very small compared to the weight of the tank and its contents.
j 2. For calculating the maximum stress in the PPMS tank shell due to hydrostatic pressure, the maximum water height in the tank is conservatively assumed to be 34 ft, which is the maximum height of the tank (2 ft higher than the overflow line elevation per 5023-407-3-97-0). Hydrostatic water head of 34 ft, therefore, exceeds the maximum possible water head in the tank.
- 3. Design Basis Earthquake (DBE) = 2
- Operating Basis Earthquake (0BE).
- 4. The WRC Bulletin 297 is the best practical method presently available for estimating tank nozzle stiffness values. However, it provides data en a !
narrow range of parameters and therefore some interpolation and estimation are performed to obtain approximate stiffness values. The magnitude of nozzle stiffness obtained are adequate to provide a realistic translational and rotational restraint conditions at the tank connections.
l (Note : The ASME code flexibility factor equations are not sufficient to !
calculate nozzle flexibilities in tanks with D/T ratio > 100, and do not have !
flexibility guidance on thrust loadings). l Based on the data available, only the translations 1 load (radial), in-plane moment load and out-plane moment load cause significant tank shell j deformations.
- 5. Stresses due to dead weight of the tank shell are not included in the local l
i stress check at the nozzle locations. Per Appendix A the combined weight of '
the tank roof and the cylindrical shell is 53,077 lb. The corresponding compressive stress at the base of the cylindrical shell is only 113 psi, which is considerably smaller than the other stress components.
1 l
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l I
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = = ,. ,,, ,,
CCN CONVERSION Project or DCP/lWP SONGS 2 Calc No. M-DSC-280 ccN No. CCN -
subject See Title Sheet sheet No. Il REV ORIGINATOR DATE IRE DATE REV CRIGINATOR DATE !RE DATE D NA81L M. EL-AKILY 7/27/1993 JUNGAOR'[de. 7/27/1993 I U ~ E u-9k I L'-7 \o/s/f3 T G~ YGn
- 4. DESIGN INPUT l
4.1 Tank Description and Geometry
, The Primary Plant Make-Up Storage Tank (PPMS) is a 40 ft inside diameter x 34 ft
- high atmospheric tank with capacity of 300,000 gallons (Reference 25). The tank is made up of stainless steel, SA 240-304, plates; and is anchored to the foundation by 36 equally-spaced anchor bolts. The anchor bolt chair material is A-36 (Reference 24). A more detailed description of the tank and the anchor bolt assemblies can be found in Appendix A of this calculation.
Figure 4.1 shows the main dimensions of the PPMS tank. It shows the tank diameter, height, and plate wall thickness of the bottom, wall, and roof (Reference 25).
I i l l
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l CCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =:L. ,A,, ,,
CCN CONVER$10N Project or DCP/lelP SONGS 2 Calc No. M-DSC-280 ccN No. CCN -
Subject See Title Sheet Sheet No. !b REV CRIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA8IL M. EL-AKILY 7/27/1993 JUN CAOR h'. 7/27/1993 I P Ei--Avu.V l*lS/9'1 1; & . I'ls145 9 I h !
J,/
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.T I D.= 40
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Figure 4.1 Main Dimensions of the PPMS tank i SCE 26426 NEW 4/90 l
NES&L DEPARTMENT CALCULATION SHEET = ;W No . , , , ,,
CCN CONVER$!0N Project or DCP/MiP SONGS 2 Calc No. M-OSC-280 ccm No. CCN -
subject See Ticle Sheet Sheet No. !
REV ORIGINATOR DAM IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AXILY 7/27/1 M3 JUNGAOR((. 7/27/1993
/ n -En.- A kt LY bM/ */ 3 'J-6 /f[S) l 4.2 Material Properties Tank Shell Material: Stainless Steel, SA 240-304 (Reference 25)
The following material properties of SA 240-304, at 120*F U ), were used in the l
analysis (Reference 2):
Young's modulus (E) = 28.0 x 10 6 psi, Poisson's ratio (v) = 0.3 Allowable stress intensity (S ) = 20,000 psi The anchor bolt chair material: A-36 (Reference 24)
The following material properties of A-36, at 110 F used for external members in I the design report, Appendix A, were used in the analysis:
Yield stress (f,) = 35.68 ksi (Reference 2)
Allowable stress (S) = 12.6 ksi The allowable stress above is at 120*F (see Note (1) below).
l Note (1): The actual design temperature, per FCN F-7519M for P&ID number 40133, is 104*F. Therefore, the use of 120'F as reference temperature for material properties is conservative.
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n No . ,m ,,
Project or DCP/MIP SONGS 2 CCN CONVERSION Cale No. M-DSC-280 CCN No. CCN -
, subject See Title Sheet 1 Sheet No. 4 REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE O #
NA81L M. EL AXILY 7/27/1993 JUNGAORJf 7/27/1993 l N 'EL-AlCI LY W}3lf3 T C. '#h]%
2 4.3 Anchor Bolt Assemblies
' Figure 4.2 shows the main dimensions of a typical anchor bolt assembly. Two different bolt sizes exist in the tank after modification:
1.1.5" bolts (36 existing anchor bolts),
- 2. 2" bolts (34 new anchor bolts).
Also, a ring will be welded to the outside edge of the bottom plate as shown in Figure 4.2. Holes for anchor bolts will be drilled in the ring (15/8" for the existing bolts, and 2 1/8" for the new bolts).
4.4 Reinforcina Bars Per Reference 4, the concrete base is reinforced by #18 size reinforcing bars (rebars). These rebars are 2.257" in diameter; and are separated by 16" center-to-center distance.
4.5 Not used.
SCE 26-426 NEW 4/90
l NES&L DEPARTMENT i
CALCULATION SHEET l = icN No. ,A,, ,,
CCN CONVERSION l Project or DCP/MP SONGS 2 Calc No. M-DSC-280 CcM NO. CCN -
subject See Title Sheet sheet No. Ib REV ORIGlWATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE
$ 0 NA81L M. EL-AKILY 7/27/1993 JUNCAoR[f. 7/27/1993 I u . e u-gicy w)sjg3 g (, . tejgj45 l
si le N //
j 2't o 7 76 //
4
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\ ban k y wall '
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l y,,6 bebrH 248'/tb# rad. -
l Figure 4.2 Modified Anchor Bolt Assembly l
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = " n ,. . ,Ax . l CCM CONVER$10N Project or DCP/MIP SONGS 2 Calc No. M-DSC-280 Ccn no. CCN - l subject See Title Sheet !
sheet No.
REV ORIGINATOR 1 DATE IRE DATE REV ORIGINATOR DATE !RE DATE 0 NAB!L M. EL-AK!LY 7/27/1993 JUNGAOR((. 7/27/1993 I o eu-9.a l'/IM] TC. '%f95 ,
1 4.6 Nozzle and Pioina Data The nozzle loads evaluated are given in data sheets, attached in Appendix D, which were extracted from various calculations as noted in the nozzle load data sheets.
Per References 23 and 24, the following piping is attached to the PPMS tank:
4" Sch. 40S SA-312 TP304 0 elev. 31'-0" 3" Sch. 40S SA-312 TP304 0 elev. 10'-7" 2-1/2" Sch. 40S SA-312 TP304 0 elev. 31'-0" 2" Sch. 805 SA-312 TP304 0 elev. 31'-0" (two places) 1" Sch. 80S SA-312 TP304 0 elev. 16'-0" 4.7 Out-of-Roundness Measurements Field tests were conducted on both PPMS tank, T-055 and T-056, to measure the diameter at different angles. These measurements were taken at two elevations I for each tank. Results of the survey are documented in Reference 26, and a copy is attached in Appendix D of this calculation.
l l
1 l
SCE 26426 NEW 4/S0
NES&L DEPARTMENT I CALCULATION SHEET = " n ,. .
. ,, i CCN CONVERSION Prtject or DcP/MMP SONGS 2 calc No. M-DSC-280 ccN NO. CCN -
subject See Title Sheet sheet No. O 1
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE o NA81L M. EL-AKILY 7/27/1993 JUNGAORJk, 7/27/1993
/ Nel-ntw Iou /93 %g, '%fo 1 I
- 5. METHODOLOGY The tank design report was prepared by Structural Integrity Associates, Inc. l This report is included, in its entirety, in Appendix A of this calculation. The ;
methodology of the analysis is based on " Generic Implementation Procedure (GIP) '
for Seismic Verification of Nuclear Plant Equipment," Reference 5; and ASME Boiler and Pressure Vessel Code, Reference 2. Details of the tank design methodology can be found in Section 5 of Appendix A. I i
1 The methodology of developing the tank stick model is included in Appendix B of this calculation. This stick model was used in the analysis of the piping attached to the PPMS tanks.
In addition to the above analyses, this calculation comprises the following supporting analyses:
- 1. Angular shear stress distribution in the anchor bolts,
- 2. Bolt location adjustment due to the rebars,
- 3. Calculation of translational and rotational nozzle stiffness,
- 4. Local stress check, and
- 5. Out-of-roundness check.
- 6. Statistical Analysis of Radiography data (Included in Appendix E).
- 7. Fracture Mechanics Evaluation (Included in Appendix F).
~
The methodologies used in items 1 through 5 above are summarized in the following subsections (Subsections 5.1 through 5.5). Methodologies for items 6 and 7 are contained in Appendix E and F respectively.
SCE 26-426 NEW 4/90
I NES&L DEPARTMENT '
CALCULATION SHEET = icN No. ,, ,
' CcN cCNVERSION Project or DCP/MHP SONGS 2 Calc No. M-DSC-280 ccN No. CCN - l subject See Title Sheet sheet No. / 2 REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE O NA8IL M. EL-AKILY 7/27/1993 JUN GA0R k , 7/27/1993
/ "-et-ek a villy] 0" c ,
/ffn .
- 5.1 Anoular Distribution of Shear Load in the Anchor Bolts A tank model was generated using the finite element program ANSYS. The model is
" made up of ANSYS element type STIF63, which is an elastic quadrilateral shell element (Reference 3). This element type has six degrees of freedom at each corner node: translations in the x, y and z directions, and rotations about the x, y and z axes. The element has stress stiffening and large deflection I
- capabilities. It is also capable of modeling plates on elastic foundations.
This feature was utilized to model the bottom plates.
f i
I
! Figure 5.1 shows a computer plot of the finite element model used in the
, analysis. The model dimensions and material properties are based on the tank data summarized in Section 4. Figure 5.1 also shows the locations of the anchor bolts.
4
{ Two modelf, with different loading conditions, were used:
- 1. In the first model, the horizontal seismic load is represented by a concentrated horizontal force, of 105 lb, applied near the top of the shell in the x-direction, as shown by Figure 5.2a.
- 2. In the second model, the horizontal seismic load is represented by a distributed horizontal load, as shown by Figure 5.2b. A force of 1000 lb, acting in the x-direction, was applied at each node of the tank shell above the bottom.
l In both models, all displacement components were constrained at the anchor bolt locations.
4 1
i
' Results of the analysis were obtained in the form of horizontal (shear) reaction 1 forces, and vertical (pull) reaction forces at all anchor bolt locations. These forces were normalized and plotted versus the angle (0) measured from the
- positive x-directions, as shown by Figure 5.1.
1 I
SCE 26 426 NEW 4/90
y NES&L DEPARTMENT CALCULATlON SHEE, ;;;,:NCNNo .
,AC, ,,
Project or DCP/MMP SONGS 2 CCN CCNVER$1CN Calc No. M-DSC 2 I O CCN No. CCN -
subject See Title Sheet
_ Sheet No.
REV ORIGINATOR DATE IRE l DATE REvl CRIGINATOR l DATE IRE !
DATE O lNABILM.ELAKILY l12/17/92 f,f , ,f/y/h l lu- EL-lt' h o ut .
lolil4'1 S C, l/"l$63 AZ
/
\ ', i / /,/,' \
C' __. > o .
-s j
t ) /, ,,
- '!' '\\
- NN
\ 'N
,y' &
. ~ )
6=l80 0
t- F. x K u-l
! , , , j
, Anchor Edh Locat ions Figure 5.1 Computer Plot of the Finite Element Model SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET : ::: L. ,Ax ,,
~
CCN CONVERSION Project or DCP/MHP SONGS 2 Calc No. 2 05C 'ff O cCN No. CCN -
subject See Title Sheet Sheet No. O REVf ORIGINATOR DATE IRE l DATE REV OR!CINATOR DATE IRE DATE O NA8IL M. EL AKILY 12/17/92 [f, 7htj)
I t' A +M <' f al1l4.? T-(, , '{dh
- ~
> - 3c c c,c c o /b
~
a .
Figure 5.2a Concentrated Force Near the Top of the Tank
- ~
r
- + . . . _ , . .+ .-.r.
o -*- -,- .-
r F~= I,00 0 /b
- -D- * =+-
r
- y .- , +
sr - ,A ,&
Figure 5.2b Distributed Force Acting on Shell of the Tank SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n , . ,, ,,
CCN CONVERSION Project or DCP/MMP SONGS 2 calc No. M-DSC-280 cCN NO. CCN -
subject See Title Sheet sh t no. 2 f REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NASIL M. EL AKILY 7/27/1993 JUN GAOR k , 7/27/1993 I u tu-awM M11]n 76. '%'fs, 5.2 Effect of Relocation of Some Anchor Bolts The nominal bolt circle diameter for the new bolts is 40'-8" per Appendix A of this calculation, which corresponds to eccentricity (e) of 3.6875". However, to avoid interference with the rebars, some of the new anchor bolts may have to be moved radially outward. The effect of increasing the eccentricity of the anchor bolts is evaluated in this subsection. This evaluation is based on the methodology of the design report (Appendix A of this calculation). This l methodology consists of several analysis steps, and only those steps impacted by the increased eccentricity are re-analyzed in this appendix, namely:
- 1. Tank Shell Stress Step 9, Section 9 of Appendix A is impacted. The allowable tensile bolt stress to compute the overturning moment (F,) is calculated based on the re-calculated tank shell stress. The new tank shell stress is obtained using the equations given in Appendix A with:
a) Modified eccentricity representing the relocated bolts, b) Modified chair height to account for the differences in geometry from the geometry used in Appendix A.
. 2. Vertical Stiffener Plate i
Step 10, Section 9 of Appendix A is impacted. The adequacy of the stiffener plates is evaluated using plate size (k) from the modified anchor bolt assembly.
- 3. Chair-to-Tank Weld l
Step 11, Section 9 of Appendix A is impacted. Modified weld stress (W,,
lb/in) is calculated based on the eccentricity of the relocated anchor bolts, and compared with the allowable specified by Reference 2.
l
- 4. Bucklina Bendina Moment Capacity Step 17, Section 9 of Appendix A is impacted. A modified value of the l bending moment capacity (M e ,p) is calculated based on the re-calculated value of Fr .
I SCE 26-426 NEW 4/90 i
NES&L DEPARTMENT CALCULATION SHEET gr" L . ,, ,,
Project or DCP/MMP SONGS 2 Calc No.
CCN CONVERSION
. M-OSC-280 ccN No. CCN -
subject See Title Sheet sheet No. 2 REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE 0 NABIL M. EL-AXILY 7/27/1993 JUNGAORjf,, 7/27/1993
/ 9 -ec-42, c r log /97 74. 'y h Mathematical formulas used in the above steps can be found in the tank design report (Appendix A of this calculation), or Reference 2.
Finally, methodology of Reference 7 (and Reference 8) was used to evaluate the added bottom ring. This ring, which is not included in the design re added for better constructibility of the modified anchor bolt chairs. port, The is methodology of these two references can be summarized as follows:
- 1. Tearcut Failure A tearout stress check is performed to calculate the shear stress on the area shown in Figure 5.3a. The allowable shear stress is conservatively taken equal to 13 ksi per Reference 2 (Subsection ND-3852.6).
- 2. Pure Tension Ruoture This failure mode is illustrated in Figure 5.3b. The tensile stress in the plate should not exceed the allowable stress (S=12.6 ksi per Reference 2). The use of this allowable is conservative since it is being used to evaluate Level D loading.
- 3. Failure by Crushina This failure mode is illustrated in Figure 5.3c. The stress acting on l the projected area should not exceed the yield stress (fy ).
l l
l l
ECE 26426 NEW 4/90
NES&L DEPARTMENT l CALCULATION SHEET grs .. ,, ,, !
Project or DCP/MMP SONGS 2 CCM COMYERS!C"4 I calc No. M-OSC _2 b, cCn no ccN - l Subject See Title Sheet
, She No REV ORIGINATOR DATE 1 IRE DATE REV ORIGINATOR DAfE IRE 0 lDATE !
NAall M. EL AKILY 12/17/92 [.6 , h7 (*)
/ 12- c ute M *'d IolSl'f1 -pf _ c'*/,7; , '
l 1
1 1
1/
5l16 //
I (w"
0 -7W - 6l16 .
l
,, \
g
{'
-735" J bou m y runq 2 75* ya J i bonk ' ' f iayk __.
wo /I l v>or Il 1 --
ii ,
ii
-w 4 /'g + '2'/g .L f
bo A m i fing i I
a Figure 5.3a Tearout Failure Figure 5.3b Tensile Failure s l/
j 5/I4
%_ .-7151
'M I 9F ,
)
6pek -5 'g r -
- l We ll 1 Y'j i .-
i 1
> %=v' -
/t
+ 2 '/g +
l Figure 5.3c Failure by Crushing sCE 26426 NEW 4/B0
NES&L DEPARTMENT CALCULATION SHEET =:MCNNo . m, ,,
1 CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN -
subject See Title Sheet 0 4.
sheet No. ~~ '
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA8IL M. EL-AXILY 7/27/1993 JUN CAOR Q , 7/27/1993
/ ^' -ci-# ki t r 45/U 7- (, , 'M70 5.3 Nozzle Stiffness Evaluation 1
The nozzle stiffness values are a roximated using'the methodology and formulas in WRC Bulletin 297 (Reference 14 1
Due to the narrow range of parameters given in the bulletin, interpolations and estimations will be used as appropriate. The magnitude of nozzle stiffness obtained by this process give a realistic translational and rotational end reactions at the nozzle-shell connections and therefore reasonable piping design i analysis.
l
)
l l
l SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = = ,. . ,A, ,,
CCN CCNVER$!ON Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccN No. CCN -
subject See Title Sheet sheet No. b b REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NASIL M. EL-AKILY 7/27/1993 JUNCAOR'j',f. 7/27/1993
/ N - EL-4 kil.y ':/3 /13 y 6, /%/O 5.4 Local Stress Check
, The local stresses were calculated using computer program ME101LS (Reference 12).
The maximum local stress intensities calculated are combined with the pressure and seismic stresses of the tank. The combined stresses are then compared against the ASME code allowables (Reference 2). It should be noted that the stresses due to the dead weight of the tank shell have been ignored in the local stress calculation since they are much smaller than the other stress components, as shown in Section 3.
DBE primary moment loads at the tank shell are used to evaluate primary stresses under Design conditions and will give conservative results.
I l
l l l l' l l
l l
l l
l l
SCE 26426 NEW 4/90
NES&L DEPARTMENT 1
CALCULATION SHEET =n .. ,A. ,,
t Project or DCP/MMP SONGS 2 Calc No.
CCN CONVERSION M-DSC-280 CCN No. CCN -
subject See Title Sheet Sheet No. 1 REV ORIGINATOR DATE IRE DATE REV ORIGlWATOR DATE IRE DATE f 0 NABIL M. EL AKILY 7/27/1993 JUN GAOR [4 7/27/1993
/ N et-4kiLP 910 56. '*/91; 3 a
5.5 Out-of-Roundness Recuirements I
Per reference 2, Subsection ND-4224, the tank must meet the out of roundness
! requirement outlined in that subsection. This can be summarized as follows:
! 1. Step 1 Calculate D,,,/100, where 0,,, is the average diameter of the tank in inches.
- 2. Steo 2 4
Based on field measurements, calculate the maximum diametral out-of-roundness for each tank.
1
' The PPMS tanks meet the Code requirements if the maximum measured out-of-roundness is less than the amount calculated in step 1.
l 2
i 1
i
+
F Note:
It should be noted that all calculations were carried out by hand or by verified computer programs; and the calculation capability of the word processing program was never used.
SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =" A .. ,A. ,,
CCN CONVER$!ON Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUN GAOR [ f , 7/27/1993
/ u c.+mt wM9.7 pg, i%%>
1
- 6. REFERENCES
- 1. Field Change Notice (FCN) number F-7520 M, 21 M, and 22 M.
- 2. ASME Boiler and Pressure Vessel Code,Section III, Division 1, 1989, no addenda.
- 3. ANSYS User's Manual, Revision 4.4, Swanson Analysis Systems Inc., May 1, 1989.
- 4. Calculation number C-258-9.10, Revision 0," Primary Plant Make-Up Storage Tank Evaluation."
- 5. " Generic Implementation Procedure (GIP) for Seismic Verification of Nuclear Plant Equipment," Revision 8, Corrected 2/14/1992, SQUG.
- 6. ASME Boiler and Pressure Vessel Code,Section II, Division 1,1989, Material Specifications (Ferrous).
- 7. Shigley, Joseph E.," Mechanical Engineering Design," Third Edition,1977, McGraw-Hill Book Company.
- 8. " Standard Handbook of Machine Design," Editors Shigley, J. E., and Mischke, C. R., 1986, McGraw-Hill Book Company.
- 9. Manual of Steel Construction, Eighth Edition, American Institute of Steel Construction, Inc., 1980.
- 10. " Design of Welded Structures," Omer W. Blodgett, The James F. Lincoln Arc Welding Foundation, Cleveland, Ohio, March 1982.
- 11. Design Bases Document S023-TR-EQ, Revision 0," Environmental Qualification Topical Report."
- 12. Computer program HE101LS Version M10.
- 13. Design of Piping Systems, NW Kellogg, Revised 2nd Edition.
- 14. Welding Research Council Bulletin 297 September 1987.
- 15. MW Kellogg Company, Design of Piping Systems, Revised 2nd Edition r
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n ,0 . ,Au 0, CCN CONVERSION Project or DCP/MP SONGS 2 Calc No, M-DSC-280 ccN No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUN GAOR h d , 7/27/1993
) u-eu- n at tolsj e3 FC, "/OSS
- 16. Calculation number M-1203-476-2A, Revision 0.
- 17. Calculation number M-1203-478-2A, Revision 0.
- 18. Calculation number S-1415-22, Revision 0.
- 19. Calculation number 844, Revision 0.
- 20. Calculation number S-1415-06, Revision 0.
- 21. Calculation number S-1415-37, Revision 0.
- 22. Calculation number S-1415-56, Revision 0.
- 23. Piping Material Specifications 90004 Rev. 53
- 24. Drawing number S023-407-3-61-2, 40' dia. x 34' high Primary Plant Make-Up Storage Tank Shell Plate Layout.
- 25. Drawing number S023-407-3-62-3, 40' dia. x 34' high Primary Plant Make-Up Storage Tank Roof and Bottom Layout.
- 26. Construction Work Order number 92092078000, Out-of-Roundness Test Results (attached in Appendix D).
Additional references are listed in the reference sections of Appendix A and Appendix B.
l SCE 26-426 NEW 4/90
)
NES&L DEPARTMDJT CALCULATION SHEET :=L . ,A E ,,
CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccN No. CCN -
subject See Title Sheet 4
SheetNo.2 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUN GAOR h , 7/27/1993 1
/ u et-AWutY loHf93 y, /*/Q3
- 7. NOMENCLATURE A = Area, in C1 = Maximum length of nozzle in circumferential direction, inch C2 = Maximum length of nozzle in longitudinal direction, inch d = Outside diameter of nozzle, in.
I Di = Inside diameter, inch.
D, = Outside diameter, inch.
DBE Design Basis Earthquake e = Bolt eccentricity, in E = Modulus of elasticity, psi.
F = Force, lb F3 = Allowable bolt stress, psi F, = Allowable bolt stress after applying a reduction factor, psi f, = Yield stress, psi 1
h = Height, in j = Distance between stiffener plates, in k = Stiffener plate width, in L = Height of tank, in.
M = Overturning moment, in-lb MA = Resultant moment at the tank shell due to primary loads, ft-lbs MB = Resultant moment at the tank shell due to primary + secondary loads, ft-lbs Mei , = Overturning moment capacity, in-lb SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;rn No . ,A. ,,
CCN CONVERSION Proje:t or DCP/> DIP SONGS 2 cale No. M-OSC-280 CcN No. CCN -
- subject See Title Sheet Sheet No. 3O REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AXILY 7/27/1993 JUN GAOR f [,, 7/27/1993 I V- eu -/}k t L Y MUJ43 f.f , /*/yg y i
MC = Circumferential, moment, in-lbs ML = Longitudinal moment, in-lbs NT = Torsional moment, in-lbs OBE Operating Base Earthquake P = Radial load, lbs R = Radius, inch S = Allowable stress, psi SHA Shape of nozzle (CIR = circular) t = Thickness, inch VC = Circumferential load, lbs VD = Mean diameter of tank, inch VL = Longitudinal load, lbs VT = Tank wall thickness, inch w = Radial deflection due to P, inch l v = Poisson's ratio o = Stress, psi 0 = Angle, degrees 0 = Rotation at centerline of nozzle, radians i
t = Shear stress, psi SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;;r n ,.. ,A E ,,
CCN CONVERSION
. Project or DCP/MMP SONGS 2 Calc No. M-OSC-280 CCN No. CCN -
1 i
subject See Title Sheet Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUN CAOR ((, , 7/27/1993 l M -EL-Gict L.'t to l9] pg /*/fh$
- 8. CALCULATIONS 1 The following analyses are covered in this section:
., 1. Angular shear stress distribution in the anchor bolts, j 2. Bolt location adjustment due to the rebars,
- 3. Calculation of translational and rotational nozzle stiffness,
- 4. Local stress check, and
- 5. Out-of-roundness check.
i I
d 1
SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = " n ,.. ,A,E ,,
Project or DCP/MMP SONGS 2 Calc No.
CCN CONVERSION M-DSC-280 ccN NO. CCN -
subject See Title Sheet sheet No. 3 A REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AXILY 7/27/1993 JUN GAOR h, 7/27/1993 1 U. EL -r& sky 4)Spff f,$ , fo(gg 8.1 Anoular Distribution of Shear Load in the Anchor Bolts i
Analysis was performed using the general purpose finite element analysis program ANSYS. Description of the model is given in Section 5 of this appendix; and a computer plot of the model is shown by Figure 5.1. Figures 5.2a and 5.2b show the two analyzed cases with concentrated and distributed external loading.
Results of the analysis confirm the validity of the sinusoidal shear force distribution in the angular direction used in the tank design report (Appendix A). Results were obtained for the two models described in Section 5:
- 1. Model with concentrated horizontal shear force, i
- 2. Model with distributed horizontal force.
Figures 8.1 and 8.2 show the normalized shear force in the anchor bolts for both models plotted versus the angle (0) measured from the positive x-direction, as shown in Figure 5.1. These two figures also show a true sinusoidal distribution plotted for comparison purposes. Both figures show that the actual distribution matches the true sinusoidal distribution. Figures 8.3 and 8.4 show the corresponding plots for the axial (pull) force distribution plotted along with a true sinusoidal distribution. These figures show that the actual distribution and the true sinusoidal distribution are identical.
Therefore, the sinusoidal load distribution of bolt loads is supported by the analysis results.
SCE 26 426 NEW 4/90
Project or DCP/9MP CALEN5T5bbSHEET =",' . ,,, o, SONGS 2 .
Calc No. M-OSC 2 $ O _
ccx couvraston s:bject See Title Sheet Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA8IL St. EL AtlLY 3/5/1993 [ [ ', h)/fqg, I ' W - EL - A k t L 'f 1915/ 11 ['d, ty'ifq3
- ,i _ . . . _ . . . _ . . . . - - _ .. .
0.9 -
g-
/ 3-- - \
i y - - - - -
g 0.8 -
Si/16
$ 0.7 - - - - -- -- - - -
~
Wd W 7
/
E on _. _ _ - ._ _.5 _ _ _ _ _ . __ _ ._ F a N in 0.5 g - -
--- --- b o l b b 0:4 - - - - - - - - -- - - - - - -- -- ! OO" h
e t (no rrnorIIz e<A o.3 ___ __ _ _ _ _ _ _ _ _ _
0.2 7 3 - - - - - - -- - - - -
i- 3 0.1 t
- -- - - - - - - - - 1 1r--
0 0 20 40- 60 80 100 120 140 160 180 ANCI E (DEGRE ES)
I1 0 01I *.111 All l OAll f Sif41 Il#S IloN Figure 8.1 Normalized Bolt Shaar Force (Model with Concentrated Force)
NES&L DEPARTMENT Project or DCP/mP CALCULATION SHEET SONGS 2
>:g;at . ,A, ,,
Calc No. M-DSC .280 cc,co,,,,3,,,
s4 ject See Title Sheet Sheet No. 3 k REV ORIGINATOR DATE IRE DATE REV ORIGlWATOR DATE 0 IRE DATE NAtlL M. El-AKILY 3/5/1993 [C /s p,d; y i
F1- EL-19tCt! Y 10}$/ff3 Q M{fy g,3 . _ . _
g f
0.9 - -
g 0.8 -
O
' g 0.7 -
Sirle w
e y Wotve.
en /
06 -- - - - -- -- - -- - - - - -
D -
O 05 - - -
a
} e _ bglg 0.4 - - -
m 03 l f -- -
(normalized)
O - .
O.2 -- - -
( - -
- o. /
7
/ -
- - - - - ( \
t )
g .. -
I 0 20 ~ 40 60 80 100 120 140 160 180 Ars;t i (orCRrts)
Figure 8.2 Normalized Bolt Shear Force (Model with Distributed Force)
Project or DCP/MP CALEddTSOESHEET =:t. ,, ,,
SONGS 2 cale no. M-DSC *2,9 O ccn convrRslon subject See Title Sheet Sheet No. 3 5 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE' 0 .NAsit M. EL AKILY 3/5/1993 JT g, 3- 2,/r. 7 I u - E t.- s% k l t-Y 'ofsJ13 7 g, '7gfg,,
ii _ _ _ _ _ ._ .. .. . . . __ ..
i I
g9 tit--i ! - i
, 4B ' "
o.9 --
-- .,m '
o 0.8 a -
/ ,
O a
)( ,
g,7 3
_/- . _ _ _ . . . _ _ _ _ . _ .
0 (> - - - - - -- - - - - - - - - - - - - - - - - - - ' - - - - - - ---
e--- * - - -
o_s __ .. . - _ .
O i y og
> [.
s o 0.3 --
o.2 f - - -
o.i o .. -
90 110 130 150 I/0 ANGl1 (lli(.141Lt.)
iI 0011 i OAll e COSINE I IIHe ' lit 8H Figure 8.3 Normalized Bolt Tensile Force (Model with Concentrated Force) '
NES&L DEPARTMENT Project or DCP/felP CALCULATION SHEET SONGS 2
':::,;a ic . ,, ,,
Calc No. M-DSC 2 O O ccm convtRston schjeet See Title Sheet CCM NO.
sheet No. 3 6 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE O DATE NA81L M. EL-AKILY 3/5/1993 J' (( , fyy[g yj i f t- Et_- A ge t L y P)J/93 [g , /%fg) g,g _ _ _ . . . . . . - . . _ . . . . .
I V u - 88'--i ' ---
0.9 --
a 1[
g 0.8 a -- -
.s
-j o.7 - - - - -- -
a 06 -- - - - - - - - ---
j i
, 05 --
n
-' O.4 -
O o.3 ) -
0.2 0.1 --
o ._
90 110 130 150 I/0 ANGI l (llfGREE S) fI NORMAL I/I () ItDAll I COSINI Ilifit 'ilOtt Figure 8.4 Normalized Bolt Tensile Force (Model with Distributed Force)
l NES&L DEPARTMENT CALCULATION SHEET : nN ,,. ,A,E ,,
Project or DCP/MMP SONGS 2 CCN CONVER$10r Calc No. M-DSC-280 CCN NO. CCN -
sebject See Title Sheet sheet No. 3 7 REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE o NABIL M. EL AK!LY 7/27/1993 JUN GAOR M. 7/27/1993 I u - c L- A e n. V \o)rl92 pc , /*/QS-}
8.2 Effect of Relocation of Some Anchor Bolts As explained in Section 5, the bolt eccentricity (e), for the new anchor bolts, may be increased to 5" to avoid interference with the reinforcing bars in the tank base. To assess the effect of the increased eccentricity, some steps of the design repor' (Appendix A) are repeated using the modified value of e (=5") to ensure that stress limits are not exceeded. Similarly, some anchor bolt chairs may have to be moved, in the circumferential direction, from their nominal position to avoid interference with tank attachments.
. 8.2.1 Tank Shell Stress l iv 1
Using tank shellthe stress formula g(a)en in Appendix A of this calculation, Section 9, Step 9, the was re-calculated based on Reference 5 using the following input:
- a) Eccentricity (e) = 5", and b) Adjusted chair height (h) = 12" instead of the 12.75" used in Appendix A.
This adjustment reflects the modified geometry of the anchor bolt chair
- shown in Figure 8.6.
All other input is per Appendix A.
d It follows that l
o = 74,062 psi )
a>f y F, = F3 Uy/o)
= 33,941 (29,000/74062)
= 13,290 psi l Figure 8.5 shows the geometr definition of the height (h)y used , and in theeccentricity the design report (e).(Appendix A); and the sCE 26 426 NEW 4/90
CALCbT $N dHEET j ,::L. ,A,, ,,
Project or DCP/MP SONGS 2 CCN CONVER$10N Calc No. M-DSC-280 CCN NO. CCh .
subject _
See Title Sheet
__ sheet No. 3 I REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE CATE 0 l NA81L M. EL*AXILY 7/27/1993 JUNCAORf'b. 7/27/1993
} N - GL-A 4tLY 10} /) 9 3 j~~~f . /Ygc$ i l
I l
l Top Plate a
_ y
- c- ,
1 4
e-m ts n
~
I 1
P. " i
! h j
4 stiffenerg-l h Tank Vall i
- k h 2 7 Tank Base
! i
, u !
' n i n
4 1 .J tb i
l (a) Typical Plan and (b)~ Side View l
l i
Outside Views i
1 l
J Figure 8.5 Anchor Bolt Chair Geometry Used in j
the Design Report (Appendix A) f l SCE 26426 NEW 4/90
NES&L DEPARTMENT ,
CALCULATION SHEET > =" ~ o '
,m rN. xN . .
... ,, i l
Project or DCP/MP SONGS 2 CCN CCNy(R$ ION l
Calc No. M-OSC- 2 8 o C:n No. CCN - l l
subject See Title Sheet l Sheet No. N REv ORIGinaroR DATE IRE DATE REV ORIGl=ATOR O =4:st m. EL uity f DATE lif
! Daft 3/s/ m 3 ff . ,7/w/g ,
i W Et -%n.y 10/1 / 9 3 Sc . l!%%5 l
//
ll .
Y+ / -
3 sbA*+ere vin o g
U 2 A* N~
, ,- r
_/ \
k / : A l t i'
i s
fork
, % -Y
>w ll 5 l I l
. 1 jussee l i g '
r - p la be. \
i N
sbiNener rin
/
i A
! t :
If I I
k!
h
- % h Y'
?
g.o-.-
d . . g e O, ,l- o o. . c1 c ..
i t 4 y e o.
.6
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.3 6 e.- a
\ Y+ # {
koddom > ancbr g rou t.-
l bulb J I rad 1
249 /16 w
N Nidimum cdisbaM(E bo C C.
i Figure 8.6 Details of the Added Cicumferential Ring 4
NES&L DEPARTMENT CALCULATION SHEET : = m o. ,A , ,,
Project or DCP/MMP CCN CONVERSION SONGS 2 Calc No. M-DSC-280 CCN NO. CCN -
subject See Title Sheet N sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR
_ DATE !RE DATE 0 NA8IL M. EL AKILY 7/27/1993 JUNGAOR((. 7/27/1993
/ N EL-AkIl-T N/s/1.7 pg , "/(/f3 8.2.2 Vertical Stiffener Plate The vertical stiffener plates were checked in Appendix A of this calculation, Section 9, Step 10. This check is repeated using the modified plate width (k) of 7.5".
k/j = 7.5/0.75
= 10 < 95/(!fy /1000 ) = 15.9 Also, P,/(2kj) = 76,368/(2*7.5*0.75)
= 6,788 < 21,000 psi Thus, the vertical stiffener plates meet Reference 5 requirements.
8.2.3 Chair-to-Tank Weld i
Per Appendix A, Section 9, Step 11, the chair-to-Tank weld is checked as follows
! (using e=5"):
W, = P, [1/(a+2h)]2+ [e/(ah+0.667h')]
i
- where, i
a (circumferential distance between bolts) = 20.94" h (chair height) = 12" (modi fied)
, e (eccentricity) = 5" It follows that:
W, = 2,024 lb/in < 30,600 t,/b = 5,409 lb/in Thus, the chair-to-tank weld meets Reference 5 requirements.
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;;;"nNNO. ,A,E ,,
l CCN CONVER$!ON Project or DCP/M1P SONGS 2 Calc No. M-DSC-280 CCN No. CCN - l subject See Title Sheet Sheet No. h/ l REV ORIGINATOR CATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 NA81L M. EL-AX:lLY 8/20/1993 JUN GAOR J.g, huhg l
8.2.4 Bucklina Bendina Moment Capacity Per Appendix A of this calculation, Section 9, Step 17, the parameter M'c,, is I calculated as follows:
I (oc /F,)(h e/h3 ) = (10,938/13,290)(12/40.75) j
= 0.23 c' = 0.1 (per Appendix A) where values above are per Appendix A, except for F, and he. From Reference 5, Figure 7-12, M'c,,is given by:
M ' cap = 0.2 It follows that, Mca , = M'c,p(2F,) (R t,,)(h3 /he ) e 2
I where, 1
Fr = 13,290 psi, (per Section 8.2.1)
M ' cap = 0.2 he = 12" All other quantities are per Appendix A, Section 9, Step 17.
Therefore, Mca , = 4.95 x 108 in-lb > M (M=3.82x10 8 in-lb) [0. K.]
l l
l l
SCE 26 426 NEW 4/90 l
NES&L DEPARTMENT CALCULATION SHEET 4
= = ,0 . ,A. ,,
! Project or ocP/MMP SONGS 2 CCM CONVERSION Calc No. _ M-DSC- O 80 CCM NO. CCN -
subject _ See Title Sheet sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 9 NA51L M. EL AKILY 6/10/1993 [g, hg3
/ v -n.-Ak e L-Y 10/3/ ff Q /%7r3 8.2.5 Bottom Plate Shear Evaluation As part of the anchor chair modification, a circular ring is welded to the outside of the bottom plate, as shown by Figure 8.6. Through-holes, for the anchor bolts, will be drilled in this ring. Per Appendix A of thi'., calculation, part of the shear load is taken by the anchor bolts; and it is assumed that the shear load is sinusoidally distributed around the circumference with a maximum value of 28,620 lb. Stress analysis of the ring, shown below, is based on calculating average stresses on different sections; and comparing these average stresses with material allowables. This methodology is detailed in References 7 and 8.
l An edge distance of 2.75", shown by Figure 8.6, which exceeds the requirements of Reference 9 for plates with rolled edges (1.25 x bolt diameter). The thickness of the ring is calculated as follows:
- Assuming a tearout failure mode at the existing anchor bolts, as shown in
- Figure 5.3a. The average shear stress is given by
' t = F/A, where, F = 28,620 lb, A = 2 x (2.75-2.125/2) x t (see Figure 5.3a, b and c)
, = 3.375 t For x = 13,000 psi (per Reference 2, Subsection ND-3852.6),
it follows that:
t = 0.65" let t = 3/4"
- Assuming a tensile mode failure, illustrated in Figure 5.3b, the area (A) subjected to tension is given by:
A = 7.75 x 3/4 - 2.125 x 3/4
= 4.21875 in' SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET nrn No. ,A E ,,
CCN CONVERSION i
Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN -
subject See Title Sheet sheet No. h3 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE
, O NABIL M. EL AXILY 7/27/1993 JUN GAOR E d . 7/27/1993
- I W Et.-oktLY 1015) 1 3 7" c. '%f%
(
Therefore, the average tensile stress is given by a = 28,620/4.21875 f = 6,784 psi < S (per Sectior. 4, S=12.6 ksi) i
- Assuming a crushing type failure, illustrated in Figure 5.3c, the minimum bearing area (a) corresponding to the smaller size existing bolts is given by:
A = 1.5 (3/4)
= 1.125 in 2 Therefore, the average stress is given by a = 28,620/1.125
= 25440 psi < f y (f, = 36,000 psi) [0. K.]
I l
l l
l 1
1 CCE 26-426 NEW 4/90 l l
NES&L DEPARTMENT i
CALCULATION SHEET
- :::: n ,.. ,, ,, l 1
Project or DCP/ M P SONGS 2 CCN CONVERSION l Calc No. M-DSC-280 CCN NO. CCN - '
subject
, See Title Sheet --
Sheet No. W REV ORIGINATOR DATE tRE DATE REV ORIGINATOR DATE IRE DATE o NA81L M. EL AKILY 7/27/1993 JUN GAOR5s 5 7/27/1993 l 11 EL-A W-IL-Y M}')ff f*d". '('/9 > \
8.2.6 Wall-to-Bottom Weld t
//
\
240" ~l-k/6 ,i i
s
//
\ -
t V4 , sante. wo II
- " ? *~
- 4 A i
[
kleig l
t i.
1 9
1 J
l
' bohhom Figure 8.7 Tank-Wall-to-Bottom Weld (Reference 24)
As shown in Figure 8.7, the tank shell is welded to the bottom by a double 1/4" filet weld. The weld was checked for bothy shear load and moment load as
- follows
l l
1 (a) Shear Load f
The total weld throat area is, therefore, given by Total throat area = 2 x 480 x x (0.25)/(2)" 5
= 533 in 2 Average base shear load = 2,048,175 (see Appendix A, Section 9, Step 5)
I l
SCE 26 426 NEW 4/90 1
NES&L DEPARTMENT CALCULATION SHEET ;;;" n No. ,A. ,,
CCN CONVER$!ON Project or DCP/MMP SONGS 2 Cale No. M-DSC-280 CCh No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA8IL M. EL AKILY 7/27/1993 JUN GAOR [ [,. 7/27/1993 I tt E L-fs kluY l0)'/ 93 JA. & 5 It follows that, Average shear stress in the weld (t.,,) = 2,048,175/533
= 3,842 psi A factor of 1.5 to the average shear stress to account for the non-uniform shear stress distribution, Maximum shear stress (t,x) = 1.5 x 3,842
= 5,763 < 13,600 psi [0. K.]
Where the allowable of 13,600 is per Reference 2, Subsection ND-3852.6.
Similarly, the maximum shear stress in the base metal is given by, 5,763 x 0.707 = 4,075 < 13,000 psi [0.K.]
(b) Moment Load Per Appendix A, Section 8, Step 6, the overturning moment load (M) at the base of the tank shell is given by:
M = 3.82 x 108 in-lb The section modulus (S) of the weld is given by, S = 2x (0.707 x 0.25)(480)2/4
= 6.4 x 10" in' It follows tnat, Normal stress (o) = M/S = 5,972 psi The normal stress (o) and the maximum shear stress (x,x) are combined to obtain the maximum normal stress (o,x) as follows:
Maximum normal stress (o,x) = o/2 + N (o/2)2 , ,2
= 9,477 psi < allowable (=13,000 psi) [0. K.]
Where the shear allowable was conservatively used.
cCE 2H26 NEW 4/90
1 NES&L DEPARTMENT l CALCULATION SHEET = n ,.. ,, ,,
Project or DCP/MMP SONGS 2 CCN CONV[R$10N
_ Cale No. M-DSC-280 CCN NO. CCN -
j subject See Titie Sheet sh. g x3, 46
, REV ORIGINATOR DATE tRE DATE REV ORIGINATOR DATE IRE DATE l 0 NA8IL M. EL-AKILY 7/27/1993 JUN CAOR J 4 7/27/1993 I IJ EL-AkiLY Q, l0N/ 99 (%f3 1
8.2.7 Deviation from Nominal Position in the Cicumferential Direction The design report (Appendix A) assumes that the teak is anchored to the i foundation by equally-spaced anchor bolts. Few anchor bolts 4EEID may have to be
' moved, up to 4" in the circumferential direction, to avoid interference with the tank attachments. This small adjustment in the anchor bolt location is considered acceptable based on:
- 1. ,
7 N l wu ' " " * %ln al !
bo I k- lo A d \.c a hw '
bo S l ,d
[
A l ' c # si ri h 4i %
I I I i
A
- l l
l
% deeiabin
- #rm nm.,.I
. >. n' b(m l
y '
- I., .
\
1 ,l! j Figure 8.8 Bolt Load Distribution Figure 8.8 shows the bolt load distribution, based on the results of the finite element analysis, Section 8.1. It can be seen that the change in bolt load is gradual since a large number of closely-spaced anchor bolts are used. Therefore, a slight deviation from the nominal location in the circumferential direction should not result in any appreciable change in bolt load, including the maximum bolt load.
- 2. Per Appendix A, Section 9, Steps 7 and 9, a large margin exists between the bolt tensile capacity (33,943 psi) and the reduced bolt capacity actually used for design purposes (19,509 psi).
It is, therefore, concluded that slight deviations, in the circumferential direction, from nominal bolt locations have no impact.
SCE 26-426 NEW 4/90
l i
l NES&L DEPARTMENT l CALCULATION SHEET : n ,.. ,,,E ,,
CCN CONVERSION l I Project or DCP/M4P SONGS 2 Calc No. M-DSC-280 CCN No. CCN - '
s subject See Title Sheet sheet No. h7 REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AXILY 7/27/1993 JUN GAOR h , 7/27/1993 l M-EL-AltsLY l0}s]q3 FC, "/5fg 8.3 Tank Nozzle Stiffness Calculations The equations and figures used in the stiffness calculations are based on WRC 297 l (Reference 14).
Tank Data (Bottom of Tank Elevation is 9'-0"):
Inside diameter = 480" shell thickness, t = 5/16" (el. 9.0' to 16.97')
= 1/4" (el. 16.97' to 22.94')
=
3/16" (el. 22.94' to el. 43')
Height of cylindrical shell = 34' i 1. 4" Nozzle - Suction Line Elev. 31'-0".
d = 4.5", t = 0.237", Mean tank diameter, D = 480.1875"
, L1 = (31'-0") - (9'-0") = 22*12 = 264" i L2 = 34*12 - 264 = 144" i L = 8L1L2/( L11/2 + L2 / )*
= 8*264*144/( 2641/2 + 144t/2 )2 = 381" A = L/(DT)1/2 = 381/(480.1875*0.1875) /2 = 40.15 A = (d/D)(D/T)1/2 = (4.5/480.1875)(480.1875/0.1875)1/8 2
= 0.47 T/t = 0.1875/0.237 = 0.79 a = 1.2 (Fig. 59)
Mt /ET3 e = 0.9 (Fig. 60)
He /ET3 0 = 0.49 (Fig. 60)
- l l
SCE 26-426 NEW 4/90 1
NES&L DEPARTMENT CALCULATION SHEET :::" n NO. ,m O, :
Project or DCP/MMP SONGS 2 Calc No.
CCN CONVERSION I M-OSC-280 ccN NO. CCN -
Subject See Title Sheet Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL-AKILY 7/27/1993 JUN GAOR f6 7/27/1993 I u - EL.-f&I LY 10}flff FC . 'W/S 5 P/w == a(4.95 ET*/(DA8) 2 1.2(4.95*28.3E6*0.1875 )/(480.1875*40.15l/2)
Nozzle Stiffness due to Radial Loads :
P/w = 1942 lbs/in.
i Nozzle Stiffness due to Loncitudinal (In-olane) Moment Loads :
3 Mt /0 = E(3.14*d *t/8)/(d*k) k = (1/0.9)(3.14/8)(d/t)2(t/T)3
= (1/0.9)(3.14/8)(4.5/0.237)2(0.237/0.1875)3
= 317 3
Mt /0 = 28.3E6*(3.14*4.5 *0.237/8)/(4.5*317)
Mt /0 = 1.68E5 in-lbs/ rad Nozzle Stiffness due to Circumferential (Out-plane) Moment loads :
Mc /0 = 1.68E6*0.49/0.9 Mc /0 = 9.15E4 in-lbs/ rad SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = n NO. ,A. O, CCN CONVERSION Project or DCP/M(P SONGS 2 Calc No. M-DSC-280 CCN NO. CCN -
subject See Title Sheet Sheet No. b$
REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE O NASIL M. EL AKILY 7/27/1993 JUN GAOR ff, 7/27/1993 l 9 E1-MILY )*DIY3 7.-c , 'p{f9 y
- 2. 2-1/2" Nozzle - Line 011 0 el. 31'-0".
d = 2.875", t = 0.203", D = 480.1875" L = 381" (same as for 4" nozzle above)
A = 40.15 1 = (2.875/480.1875)(480.1875/0.1875)uz
= 0.30 T/t = 0.1875/0.203 = 0.92 a = 1.1 (Fig. 59) 3 Mt /ET 0 = 0.68 3
Mc /ET 0 = 0.42 (Fig.60) 2 P/w = 1.1(4.95*28.3E6*0.1875 )/(480.1875*40.15uz)
P/w = 1780 lbs/in.
3 Mt /0 = (28.3E6*3.14*2.875 *t/8)/(2.875*k) k == (1/0.68)(3.14/8)(2.875/0.203)2(0.203/0.1875)3 147 i Mt /0 = 1.27E5 in-lbs/ rad Mc /0 = 1.27E5*0.42/0.68 Mc /0 = 7.84E4 in-lbs/ rad i
SCE 26-426 NEW 4/90 1
NES&L DEPARTMENT CALCULATION SHEET :: = No. ,,, ,, l CCN CONVERSION Project or DCP/M P SONGS 2 Calc No. M-DSC-280 CCN NO. CCN -
subject See Title Sheet O l Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AKILY 7/27/1993 JUN GAOR ((, , 7/27/1993
/ u EL-9V M l*lf/13 f:G , !$fg y l
l
- 3. (a) 2" Nozzle - Line 023 0 el. 31'-0".
l d = 2.375", t = 0.218", D = 480.1875" L = 381" 1 A = 40.15 1 == (2.375/480.1875)(480.1875/0.1875) /2 l 0.25 )
T/t = 0.1875/0.218 = 0.86 a = 1.05 (Fig. 59)
Mt /ET3 0 = 0.6 (Fig.60) 3 Mc /ET 0 = 0.39 (Fig.60) 2 P/w = 1.05(4.95*28.3E6*0.1875 )/(480.1875*40.15 /2)
P/w = 1700 lbs/in.
3 Mt /0 = (28.3E6*3.14*2.375 *0.218/8)/(2.375*k) k == (1/0.6)(3.14/8)(2.375/0.218)2(0.218/0.1875)3 122 Mt /0 = 1.12E5 in-lbs/ rad Mc /6 = 1.12E5*0.39/0.6 Mc /0 = 7.28E4 in-lbs/ rad SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET : n No . ,A , ,,
CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-OSC-280 ccN No. CCN -
subject See Title Sheet sheet No. O REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA8IL M. EL-AX!LY 7/27/1993 JUN CAOR [-[,, 7/27/1993 i N n - A k iL- Y IO)S/93 -pg , !*/G&5
- 4. 1" Nozzle - Miniflow 0 el .16'-0".
d = 1.315", t = 0.179", D = 480.3125" L1 = 7*12 = 84" L2 = 34*12 - 84 = 324" )
t l
l I
L = 8*84*324/( 841/2 + 324t/2 ) = 295" '
A = 295/(480.3125*0.3125)t/2 = 24 1 = (1.315/480.3125)(480.3125/0.3125) /2 = 0.107 T/t = 0.3125/0.179 = 1.75 a = 1.0 (Fig. 59)
Mt /ET3 0 = 0.4 (Fig. 60)
Mc /Et3 0 = 0.3 (Fig. 60) 2 1 P/w = 1.0(4.95*28.3E6*0.3125 )/480.3125*24 )
P/w = 5814 lbs/in 3
Mt /0 = (28.3E6*3.14*1.315 *0.179/8)/(1.315*k)
I k = (1/0.4)(3.14/8)(1.315/0.179)2(0.179/0.3125)3
= 9.95 Mt /0 = 3.45E5 in-lbs/ rad Mc /0 = 3.45E5*0.3/0.4 Mc /0 = 2.59E5 in-lbs/ rad ECE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =L. ,Am ,,
Project or ocP/MMP SONGS 2 Calc No, M-OSC-280 c!"I ccE-N subject See Title Sheet Sheet No.
RfV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA81L M. EL-AXILY 7/27/1993 JUN CAOR 7/27/1993 l U E s. - & k-I L Y )olsJ92 Sc . 'yd ,,
- 5. 3" Nozzle - Suction Line 0 el .10-7".
d = 3.5", t = 0.216", D = 480.3125" L1 = 19" L2 = 389" L = 8*19*389/( 19t/2 + 3891/2)2 = 102" A = 102/(480.3125*0.3125)1/2 = 8.32 1 = (3.5/480.3125)(480.3125/0.3125)2/2 = 0.286 T/t = 0.3125/0.216 = 1.45 a = 1.17 (Fig. 59 use A = 10) 3 Mt /ET 0 = 0.6 (Fig.60)
Mc /ET3 0 = 0.4 (Fig. 60) 2 P/w = 1.17(4.95*28.3E6*0.3125 )/(480.3125*8.32 /2)
P/w = 11553 lbs/in 3
Mt /0 = (28.3E6*3.14*3.5 *0.216/8)/(3.5*k) k == (1/0.6)(3.14/8)(3.5/0.216) (0.216/0.3125)'
56.72 Mt /0 = 5.18E5 in-lbs/ rad Mc /0 = 5.18E5*0.4/0.6 Mc /0 = 3.45ES in-lbs/ rad CCE 26-426 NEW 4,90
NES&L DEPARTMENT ,
CALCULATION SHEET ;;:n . ,A. ,,
Project or DCP/ M P SONGS 2 Calc No. M-DSC-280 c!n" NEcS[".
1 subject See Title Sheet Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA81L M. EL AXILY 7/27/1993 JUN CAOR ((, 7/27/1993 l t El-A kt LY 'o)3/93 C6, "/(f99 Summary of Tank Nozzle Stiffness Values Nozzle Radial Longitudinal Circumferen-Size, Sch. Elev. Loads, Homent, tial Moment, i
NPS Lbs/in in-lbs/ rad in-lbs/ rad 4" 40S 31'-0" 1942 1.68E5- 9.15E4 2-1/2" 40S 31'-0" 1780 1.27E5 7.84E4 2" 80S 31'-0" 1700 1.12E5 7.28E4 !
1" 80S 16'-0" 5814 3.45ES 2.59E5 3" 40S 10'-7" 11553 5.18E5 3.45E5 l l
l l
i
)
l l
1 l
l l
l l
SCE 26-426 NEW 4/90 ,
l l
NES&L DEPARTMENT CALCULATION SHEET =% ,. . ,A. ,,
CCN CONVERSION Preject or DCP/MP SONGS 2 cale No. M-DSC-280 CCN NO. CCN -
]
sub.iect See Title Sheet sheet No. N REV ORIGINATOR 'DATE IRE DATE REV ORIGINATOR DATE !RE DATE O NA8IL M. EL-AXILY 7/27/1993 JUN GAOR Q , 7/27/1993 i H. E L- A kt t. Y tols)43 f.g , '%f5 >
a i
d 8.4 Local Stress Check The hydrostatic pressure at the base (elevation 9'-0") and at elevation 31'-0" i
(22' from the base of the tank are) :
Po = (34') * (ti2.4 lbs/cu.ft)/144 = 14.73 psi use 15 psi.
I
- P22 = (34'-22') * (62.4)/144 = 5 psi.
The maximum moment load due to DBE seismic at the base of the tank is taken from
- Appendix A (design report),
4 Ms = 382,172,097 in-lb = 31,847,675 ft-lbs.
The maximum moment load due to DBE at elevation 31' (22' above the tank base) is obtained by linear interpolation as follows :
a l The seismic load is zero at the top of the tank (34' high) and maximum (M,) at
{ the base of the tank. Therefore, by ratio, at elevation 31', the moment load is, Ms . = 382,172,097 * (34-22)/34
! = 134,884,270 in-1b = 11,240,356 ft=1bs.
For Nozzles A, B, and J, Po = 15 psi and M, = 31,847,675 ft-lbs.
! For Nozzles F, G and H, P22 = 5 psi and M s . = 11,240,356 ft-lbs.
The pressure and moment loads are included in the local stress analysis using ME101LS program.
Reinforcing pads 3/8" thick at nozzle F and reinforcing pads 1/2" thick at nozzles G and H are required to meet stress limits. To account e r the reinforcing pad in the local stress analysis, an effective loca* shall wall thickness equal to the square root of the sum (SRSS) of the sheH chickness and i pad thicknn s is used. This effective local wall thickness is conservative when
{ compared to the effective wall thickness (shell thickness + pad thickness) i recommended in Reference 15 for local stress analysis.
To facilitate construction, one size (1/2" thick) reinforcing pads will be l specified for nozzles F, G, and H.
SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =&c. . ,,
Project or DCP/M P SONGS 2 Calc No.
CCN CONVERSION M-DSC-280 CCN No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL AXILY 7/27/1993 JUNGAOR'f.f. 7/27/1993 l Al E"l-S MIL Y 1*g, f*/ffg5 101s/ 93'l The local stress allowables, shown below, are based on the stress intensity concept equivalent to the allowables for Class 1 components (ASME Code Subsection NB-3200). These allowables can be summarized as follows:
Primary membrane plus bending stress = 1.5 Sm Primary plus secondary stress = 3.0 Sm Where, Sm = allowable design stress intensity (=20 ksi, as shown in Section 4.2).
No detailed analysis was performed for the following nozzles:
- 1. Nozzle K This is a 3"acceptable are judged drain line connected at thereasons:
for the following bottom of the tank. The local stresses (a) this nozzle is reinforced; and it is located far from the highly stressed area of the bottom, which occurs in the vicinity of the anchor bolt chairs and the shell to bottom weld.
(b) the calculated piping stress at the nozzle connection is small (about 3,600 psi for combined weight and OBE per piping stress calculation number S-1415-56, Revision 0).
(c) Since the primary stress allowable is 30,000 psi, the nozzle is judged acceptable. No further analysis is required.
- 2. Nozzle L These are two 2" instrument taps at elev. 9-6" and 42'-0". A 2" X 3/4" swage reducer and a 3/4" gate valves is welded to each nozzle and tubing attached for instrumentation. Nozzle loads are judged acceptable by inspection and comparison to the loads and stress results calculated for Nozzle B which is a 1" unreinforced nozzle and therefore more restrictive than the 2" nozzle.
- 3. The support connections at the tank are reinforced by 1/2" X 8" X 8" pad. The maximum local stresses at the tank due to the support loads are judged acceptable by comparison to the loadings obtained for the 4" nozzle H (see References 16 through 22 for nozzle and support loads).
Results of the local stress analyses using HE101LS are shown in the following pages.
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = n No. ,A E 0, CCN CONVERSION Project or DCP/MMP SONGS 2 & 3 Cale No. M-OSC-t W CCN NO. CCN -
subject See Title Sheet Sheet No. 5 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AKILY 3/5/1993 p( . 7Mg l H. E L-.h ks L M ln/ sl$3 ff . ^/Qq$
- 1. Tank 055/56 - Nozzle A ME101LS Version M10 start on 02/25/93 at 07:25:56 BIJLAARO STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 1 02/25/93 PG2556 LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056, N0Z2LE A
, 1 N P U T 0 A T A
........ 1........ 7........ 3........ 4........ 5........ 6........ 7...-.... 8 1 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE A 2 LOC 3 V0 480. 312 5,V T=0. 3125,C1 = 3. 5.C2 =3. 5, SHA =C I R ,
4 P=927,VL=126,VC=361 ML=4726,MC=3972,47 1884, 5 CAS.SO, 6 MA=31847675, 7 PO=15, 8 SM 20, 9 LOC 10 P=927,VL=126,VC=361,ML=4726,MC=3972,MT=1884, 11 CAS=$E.
12 MB=31847675, 13 PO=15, 14 SM=20, 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 02/25/93 PG2556 PAGE 2 LOCAL STRESS ANALYSIS FOR CCS TANK T.055/T.056, N0ZZLE A I N P U T 0 A T A P F. MC MT VL VC MA MB STRESS (LSS) (IM.LBS) (!N.LBS) (IN.LBS) (LBS) (LBS) (FT.LBS) (FT.LBS) LEVEL I 927.0 4726.0 3972.0 1884.0 126.0 361.031847676.0 .0 50 2 927.0 4726.0 3972.0 1884.0 126.0 361.0 .031847676.0 SE VESTHK VES0!A C1 C2 SHAPE SCALE SM PRESSURE BEND R (IN) (!N) (IN) (IN) FACTOR 1 (KSI) (PSI) (IN)
I hkb 48b$ bib bIbbb b$5bb b5RCbk bbb bb$b kbb bbb 2 .312 480.312 3.500 3.500 CIRCULAR .000 20.0 15.0 .000
~
1 BIJLAARO STRESS ANALYS!$ FOR CYLINDERS ME101/M10 S. C. Edison 02/25/93 PG2556 PAGE 3 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T-056 N0ZZLE A CASE 1 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET gr1LO. ,Au 0, CCM CONVER$10N Project or DCP/MMP SONGS 2 & 3 Calc No. '
M-DSC-. 2- E o CCN NO. CCN -
subject See Title Sheet Sheet No. b ^7 !
REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL.AKILY V SL-fraI LY' 3/5/1993 J. C hh i l 9/G/93 ff. l/%fp . . .
VESSEL DIAMETER = 480.312 INCHES C1 = 3.500 INCHES C2
- GAteA = 768.500 3.500 INCHES BETA 1 = .006 BETA 2 = .006
)
- C0MBINED STRE$S ! N T E N $ I T Y. 5 (K $ I). AT ***
INWARO END OF LONG. MOM. DUTWARD END OF LONG. MOM.
OF CIRC. MOM. INWARD END OF CIRC. MOM. OUTWARD END VESSEL THICKNESS OUTSIDE INSIDE OUTSIDE INSIDE INSIDE OUTSIDE INSIDE QUTSIDE (INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL 0F SHELL OF SHELL OF SHELL i ..........-.....
MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.3125 26.29 19.08 15.72 6.96 9.84 30.24 23.78 10.48 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY
-6.36 6.36 4.71 4.71 3.59 2.12 3.59 2.12 d
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 5 02/25/93 PG2556 LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056. N0ZZLE A
[ CASE 1 THIS CALCULATION !$ FOR A LUG ON STRAIGHT PIPE l
MAXIMUM PRIMARY P! PING STRESS INTENSITY............................... 12.5(KSI)
MAXIMUM PRIMARY LOCAL MEMBRANE STRESS INTENSITY....................... 6.4 (KSI)
MAXIMUM COMBINED PRIMARY MEMBRANE STRESS INTENSITY....................
18.9 (KSI) 1 ALLOWABLE ( 1.500 Se ).....-.......................................... 30.0 (KSI)
B1JLAARD STRESS ANALYS!$ FOR CYLINDERS ME101/M10 S. C. Edison PAGE 6 02/25/93 PG2556 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056. N0ZZLE A CASE 2 VESSEL DIAMETER = 480.312 INCHES C1 = 3.500 INCHES C2 = 3.500 INCHES CAPHA = 768.500 BETA 1 = .006 BETA 2 = .006 C0MBINED 5TRE$5 I N T E N S ! T Y. $ (K $ I). AT ***
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = " % 0. ,A0E 0, CCN CONVERSION Project or DCP/MMP SONGS 2 & 3 Calc No. M-DSC '2-8 O CCN NO. CCN -
subject See Title Sheet Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL.AKILY 3/5/1993
- 76. h/$$
l t/. E L- M IL.Y MGl93 fg* l'/f/S5 INWARD END OF LONG. MOM. OUTWARD END OF LONG. MOM. INWARO END OF CIRC. MOM.
OF CIRC. MCM. CUTWARD END VESSEL THICXNESS OUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE INSIDE INSIDE OUTSIDE (INCHES) 0F SHELL 0F SHELL OF SHELL OF SHELL OF SHELL 0F SHELL OF SHELL OF SHELL MAXIMUM PRIMARY PLUS SECONDARY STRESS INTEPS!TY
.3125 26.29 19.08 15.72 6.96 30.24 23.78 9.84 10.48 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY 6.36 6.36 4.71 4.71 -3.59 3.59 2.12 2.12 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 02/25/93 PG2556 PAGE 8 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T-056. N0ZZLE A CASE 2 THIS CALCULATION IS FOR A LUG ON STRAIGHT PIPE MAXIMUM SECONDARY PIPING STRESS INTENSITY..-.........-................
18.3 (KS!)
MAXIMUM PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY....... 30.2 (KSI)
MAXIMUM COM8INED PRIMARY PLUS SECONDARY MEMBRANE STRESS INTENSITY..... 48.5 (KSI)
A L LOWAB L E ( 3 . 000 Sm ) .... .. ..-..... . . .. - . . .. . . ...... ... .. . . . .. ..... . . 60.0 (KS!)
1 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 02/25/93 PG25S6 PAGE 9 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE A SUP+uRY TABLE (KSI)
PIPING LOCAL CASE PRIMARY SEC1NDARY PRIMARY SECONDARY COMBINED ALLOWABLE MAX SHEAR ALLOWABLE
+ PRIMARY 1 12.5 .0 6.4 .0 18.9 30.0 .0 .0 2 .0 18.3 .0 30.2 48.5 60.0 .0 .0 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 02/25/93 PG2556 PAGE 10 SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =:~i;,,0. ,Ax ,,
Project or DCP/MMP SONGS 2 & 3 CCN CONVER$!ON Cale No. M-DSC L P C CCN NO. CCN -
subject See Title Sheet Sheet No. f Y REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE O NA8!L M. EL AKILY 3/5/1993 76, '/tg/h i H EL -h21LY DJs)93 pc, /*/rf43 l
ME101LS version M10 stop on 02/25/93 at 07:25:56 l NE101LS Version M10 run time .00 seconds I I
I 1
l l
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;g","MC,,0 . , A, ,,
CCN CONVER$!ON Project or DCP/MMP SONGS 2 Calc No. M.DSC ' % 8 C CCN No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE !RE DATE ORIGINATOR DATE REVl 1RE DATE O NABIL M. EL.AKILY 3/5/1993 [. f , QM l W. n~0k EL.Y IOlS/9b Q, /*///S-1,
- 2. Tank T055/56 - Nozzle B 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 01/19/93 JJ3456 PAGE 1 LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056, N0ZZLE B I N P U T 0 A T A
........1........2........3........4........5-.-.....6........7........8 1 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE B 2 LOC 3 VD=480.3125,Yi=0.3125,C1=1.315,C2=1.315,$HA.CIR, 4 P=66,VL*32,VC=55 ML*264.MC=1560,MT=72, 5 CAS=50, 6 MA=31847675, 7 PD=15, 8 SM=20, 9 LDC 10 P=66,VL=32,VC=55 ML*264,MC=1560,MT=72, 11 CAS=SE, 12 MB=31847675, 13 PD=15, 14 SM=20, 1
B!JLAARD STRESS ANALYSIS FOR CYLINDERS mil 01/M10 5. C. Edison 01/19/93 JJ3456 PAGE 2 LOCAL STRESS ANALYSIS FOR CCW TANK T-055/T.056, N0ZZLE B 1 N P U T 0 A T A P ML MC MT VL VC MA MB STRESS (LBS) (IN.LBS) (IN.LBS) (IN.LBS) (LBS) (LBS) (FT.LBS) (FT.LBS) LEVEL 1 66.0 264.0 1560.0 72.0 32.0 55.031847676.0 .0 50 2 66.0 264.0 1560.0 72.0 32.0 55.0 .031841676.0 SE VESTHK VE501A Cl C2 SHAPE SCALE SM PRESSURE BEND R (IN) (IN) (!N) (IN) FACTOR 1 (KSI) (PSI) (!N) 1 .312 480.312 1.315 1.315 CIRCULAR .000 20.0 15.0 .000 2 .312 480.312 1.315 1.315 CIRCULAR .000 20.0 15.0 .000 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 01/19/93 JJ3456 PAGE 3 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE B CASE 1 SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =:% NO . ,,,, ,,
Project or DCP/MMP SONGS 2 CCN CONVERSION Calc No. M-DSC 1 2I o CCN NO. CCN -
subject See Title Sheet REV CRIGINATOR DATE Sheet No. b IRE DATE REV ORIGINATOR DATE IRE DATE O NASIL M. EL-AKILY 3/5/1993 Q, TyMS
} H.EL-fs k iLY nh'}D VC /7Y'S 3 i
r 4
VESSEL DIAMETER = 480.312 INCHES C1 = 1.315 INCHES GAM 4A
- 768.500 C2 e 1.315 INCHES BETAl = .002 BETA 2 = .002
- C0MBINED 5TRE$5 I N T E N S I T Y, 5 (K $ !), AT ***
INWARD END OF LONG. MOM. OUTWARD END OF LONS. MGM.
OF CIRC. MON. INWARO END OF CIRC. MOM. CUTWARD END a
VESSEL THICKNESS CUTSIDE INSIDE QUTSIDE INSIDE INSIDE OUTS!0E INSIDE QUTSIDE (INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL MAXI M PRIMARY PLUS SECONDARY STRESS INTENSITY 1
.3125 -3.80 2.54 2.99
-17.67 1.49 -21.95 18.73 20.34 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY
. 93 .93 .75 .75
, 2.54 2.66 -2.66 2.54 i
B!JLAARD STRESS ANALYS!$ FOR CYLINDERS ME101/M10 i PAGE 5 S. C. Edison 01/19/93 JJ3456 LOCAL STRESS MALYS!$ FOR CCW TANK T 055/T-056. N0ZZLE B h
CASE 1 THIS CALCULATION IS FOR A LUG ON STRA!GHT PIPE 1
MAXIM PRIMARY PIPING STRESS INTENSI TY-----......-----...~...-~.-.- 12.5 (KSI)
MAXIM PRIMARY LOCAL MEMBRANE STRESS INTENSITY-.-----.....--.--.--... 2.7 (KSI)
MAXIMJM COMBINED PRIMARY MEMBRME STRESSINTENSITY-.-------...-----
15.2 (KSI) 1 ALLOWABLE ( 1.500 Se )-----....--------------...----..---------------. 30.0 (KSI)
BIJLAARD STRESS ANALYSIS FOR CYLIN0ERS PAGE 6 ME101/M10 5. C. Edison 01/19/93 JJ3456 LOCAL STRESS MALYSIS FOR CCW TMK T-055/T-056. N0ZZLE B CASE 2 VESSEL DIAMETER = 480.312 INCHES C1 = 1.315 INCHES C2
- GAPMA
- 768.500 1.315 INCHES BETA 1 = .002 BETA 2 = .002 C0MBINEO 5TRE5S I N T E N $ I T Y, 5 (K S !). AT ***
SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =~"'
PRELIM. CCN No. PAGE OF CCN CONVERSION Project or DCP/MMP SONGS 2 Cale No. M-DSC 18'8 CCN NO. CCN -
subject See Title Sheet Sheet No.
1 REV ORIGlWATOR DATE !RE DATE REV ORICINATOR DATE 1RE DATE O NA8IL M. EL-AKILY 3/5/1993 f~f , h tg,/43
/ N - a.- A k.I L Y 10)S/ 9) J-g **/(l%
l INWARD ENO 0F LONG. MOM. OUTWARO END OF LONG. MGM. INWARD END OF CIRC. MOM.
OF CIRC. MOM. OUTWARD END i
VESSEL THICKNESS CUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE l INSIDE (INCHES) CF $ HELL OF SHELL OF SHELL CF SHELL OF SHELL OF SHELL OF SHELL CF SHELL 1 MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.3125 3.80 2.54 2.99 1.49 21.95 18.73 17.67 20.34 MAXIMUM PRIMARY MEMBRANE STRESS INTEhSITY
. 93 . 93 .75 .75 2.66 2.66 2.54 2.54 BIJLAARO STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 01/19/93 JJ3456 PAGE 8 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N022LE B CASE 2 THIS CALCULATION IS FOR A LUG ON STRAIGHT PIPE MAXIMUM SECONDARY PIPING STRESS INTENSITY.............................
18.3 (KSI)
MAXIMLN PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY....... 21.9 (KSI)
MAX! MUM COM8INED PRIMARY PLUS SECONDARY MEMBRANE STRESS INTENSITY..... 40.2 (KSI) 1 ALLOWABLE (3.000Se)................................................ 60.0 (KSI) )
BIJLAARD STRESS ANALYSIS FOR CYLIN0ERS ME101/M10 5. C. Edison 01/19/93 JJ3456 PAGE 9 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, NO22LE B SLPNARY TABLE (KSI)
PIPING LOCAL CASE PRIMARY SECONDARY PRIMARY SECONDARY COMBINIO ALLOWABLE MAX SHEAR ALLOWABLE
+ PRIMARY 1 12.5 .0 2.7 .0 15.2 30.0 .0 .0 2 .0 18.3 .0 21.9 40.2 60.0 .0 .0 1
SCE 26-426 NEW 4/90
NES&L DEPARTMENT 1
4 CALCULATION SHEET g;: n NO. ,A , ,,
Project or DCP/MMP SONGS 2 ' ~ CCN CONVFRSION Cale No. M-DSC 78 C CCN NO. CCN -
- Subject See Title Sheet Sheet No.
REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 3/5/1993 pd , 7[yh
- I y -EL-AKo LV 10}sfy p g, to/(jn B!JLAARD STRESS ANALYSIS FOR CYLINDERS
- PAGE 11 ME101/M10 5. C. Edison 01/19/93 JJ3456 k
ME101LS version M10 stop on 01/19/93 at 10:34:56 j ME101LS version M10 run time .00 seconds i
u i
N i
4 9
SCE 26-426 NEW 4/90
NES&L DEPARTMENT i CALCULATION SHEET =L . ,m 0, Project or DCP/NMP 4 CCN CONVER$10N SONGS 2 - Calc No. M.0SC. D0 CCN No. cCN .
Subject See Title Sheet sheet No. N REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR l DATE IRE DATE O NAs!L M. EL.AKILY 6/10/1993 f,4 , ~2/M g I n .m.- A gn.y als/93 pc, if%
- 3. Tank T055/56 - Nozzle C (This nozzle is no longer used and is capped.
a Analysis included here are from orevious pipino loads and for information only).
8!JLAAAD STRESS ANALYi!S FOR CYLIN0ERS ME101/M10 5. C. Edison 01/20/93 KJ1428 PAGE 1 LOCAL STRESS ANALYSIS FOR CCW TMK T.055/T.056. N0ZZLE C
! N P U T 0 A T A 1
........1........2........3........4........5........6........7........8 1 LOCAL STRESS ANALYS!S FOR CCW TMC T.055/T.056, N0ZZLE C 2 LDC 3 VD=480.1875,VT=0.42,C1=2.375.C2=2.375.SHA=CIR, 4 P=159.YL=491,VC=280,ML=11508,MC=7848,MT=696, 5 CAS=50, 6 M4=11240356, 7 PO=5 8 SM*20, 9 LDC 10 P=159,VL*491 YC=280,ML=11508,MC=7848,MT=696, 11 CAS=SE.
12 M8=11240356, 13 P0 5, 14 SM=20, 1
BIJLAARD $ TRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 01/20/93 KJ1428 PAGE 2 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE C l
! N P U T 0 A T A
................................. 6 P ML MC MT VL VC MA M8 STRESS (LBS) (IN.L85) (IN.L8S) (IN.LBS) (LBS) (LBS) (FT.LBS) (FT.LBS) LEVEL I 159.0 11508.0 7848.0 696.0 491.0 280.011240356.0 .0 50 2 159.0 11508.0 7848.0 696.0 491.0 280.0 . .011240356.0 SE VESTHK VES0!A C1 C2 SHAPE SCALE SM PRESSURE BEND R
(!N) (!N) (!N) (!N) FACTOR 1 (KS!) (PSI) (!N) 1 .420 480.188 2.375 2.375 CIRCULAR .000 20.0 5.0 .000 2 .420 480.188 2.375 2.375 CIRCULAR .000 20.0 5.0 .000 1
BIJLAARD STRESS ANALYS!$ FOR CYLINDERS ME101/M10 5. C. Edison 01/20/93 KJ1428 PAGE 3 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE C CASE 1 1
l SCE 26 428 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET lis1&0. Pm 0, Project or DCP/WiP SONGS 2 Calc No. M-DSC. 1 f(J CCN CONVERSION CCN No. CCN - I Subject See Title Sheet Sheet No. G REV CRIGINATOR DATE 1RE DATE REV ORIGINATOR DATE !RE DATE O NA81L M. EL.AKILY 3/5/1993 y 6, h/$3
) M . EL -kkIL.Y 10) S / 9 1 f c. 'nffy CASE 1 VESSEL O!AMETER = 480.188 INCHES C1 = 2.375 INCHES C2 =
GAPHA = 571.652 2.375 INCHES BETA 1 = .004 BETA 2 = .004
- COMBINE 0 $ TRESS I N T E N 5 I T Y, 5 (K S !), AT ***
INWARD END OF LONG. MOM. OUTWARO END OF LONG. MON. INWARD END OF CIRC. MOM. CUTWARO END
{
VESSEL THICKNESS OUTS!DE INSIDE OUTSIDE INSIDE OUT510E INSIDE INSIDE OUTSIDE -
1 (INCHES) 0F SHELL CF SHELL OF SHELL OF SHELL OF SHELL CF SHELL OF SHELL OF SHELL
)
MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY 1
4200 43.13 30.82 41.90 29.35 32.78 28.56 30.62 l 27.13 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY 9.94 9.94 9.71 9.71 3.13 3.09 3.13 3.09 1
BlJLAARD STRESS AN LYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 5 01/20/93 KJ1428 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE C CASE 1 THIS CALCULATION IS FOR A LUG ON STRAIGHT PIPE MAXIMUM PRIMARY P! PING STRESS INTENSITY...............................
3.2 (KS!)
MAXIMUM PRIMARY LOCAL MEMBRANE STRESS INTENSITY....................... 9.9(KSI)
MAXIMUM COMBINED PRIMARY MEMBRANE STRESS INTENSITY....................
13.1(KSI) 1 ALLOWABLE ( 1.500 Se )................................................ 30.0(KSI)
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 01/20*93 KJ1428 PAGE 6 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE C CASE 2 VESSEL O!AMETER = 480.188 INCHES C1 = 2.375 INCHES C2 = 2.375 INCHES GAP 9tA = $71.652 BETA 1 = .004 BETA 2 = .004 SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n NO. ,A , ,, l Project or DCP/MHP SONGS 2 CCN CONVER$!ON !
Cale No. M-DSC. % f C CCN No. CCN -
subject See Title Sheet sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL.AK!LY 3/S/1993 y(, hj l u- EL.-6k l L'f 101S} 9.? 7 4. Ifr/95 l
- COMBINED $TRE55 INTEN5ITY. 5 (K S !). AT ***
INVAR0 END OF LONG. MCM. DUTWARD END OF LONG. MOM.
0F CIRC. MOM. INVAR0 END OF CIRC. MOM. OUTWAR3 EN0 VESSEL THICKNESS OUTSIDE. INSIDE OUTSIDE INSIDE INSIDE OUTSIDE INSIDE OUTSIDE (INCHES) 0F SHELL OF SHELL OF SHELL i 0F SHELL OF SHELL OF $ HELL OF SHELL '
OF SHELL MAXI >tJM PRIMARY PLUS SECONDARY STRESS INTENSITY 4200 .43.13 30.82 41.90 27.13 29.35 -32.78 28.56 30.62 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY 9.94 9.94 9.71 9.71 3.09 3.13 3.13 3.09 l
1 BIJLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 8 ME101/M10 S. C. Edison 01/20/93 KJ1428 '
. LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056, N0ZZLE C 4
CASE 2 TH15 CALCULATION IS FOR A LUG ON STRAIGHT PIPE MAXIMUM SECONDARY P! PING STRESS INTENSITY............................. 4.6 (KSI)
MAXIMUM PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY....... 43.1 (KSI)
MAXI >LJM COMBINED PRIMARY PLUS SECONDARY MEMBRANE STRESS INTENSITY...-. 47.8 (KS!)
ALLOWABLE ( 3.000 Sm )................................................ 60.0 (KSI)
(
BIJLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 9 ME101/M10 5. C. Edison 01/20/93 KJ1428 LOCAL STRESS ANALYSIS FOR CCW TANK T-055/T.056, N0ZZLE C SUPfiARY TABLE (KSI)
PIPING LOCAL CASE PRIMARY SECONDARY PRIMARY SECONDARY COMBINED ALLOWA8LE MAX SHEAR ALLOWABLE
+ PRIMARY 1 3.2 .0 9.9 .0 13.1 30.0 2 .0 4.6 .0 .0
.0 43.1 47.8 60.0 .0 .0 SCE 26 426 NEW 4/90
4 l
NES&L DEPARTMENT l
CALCULATION SHEET =:n NO . ,,, 0, !
1 l
4 Project or DCP/MMP SONGS 2 . CCN CONVER$10N Calc No. M-DSC '2 # c CCN NO. ccN -
! l subject See Title Sheet }
Sheet No. 67 l i
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 3/5/1993 [ (, , 7kg i N . EL-A k t GV 10lSl% [C, M/fffy, i l l
1 BIJLAARD STRESS ANALYSIS FOR CYLlhDERS PAGE 11 ME101/M10 S. C. Edison 01/20/93 KJ1428 i ME101LS Version M10 stop on 01/20/93 at 10:14:28
- ME101LS Version M10 run time .00 seconds I
I i )
1 i I
2 t
4 :
i r
} .
t l I l 1
f r
l I
i i
l l
SCE 26-426 NEW 4/9o l
NES&L DEPARTMENT CALCULATION SHEET grA0. P,0E C, Project or DCP/MMP SONGS 2 CCN CONVER$!CN Calc No. M-DSC. M C .
CCN NO. CCN .
subject See Title Sheet Sheet No. 66 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AKILY 3/5/1993 'j~, -f , hjh l ll- E/.- AM i L V 1ClSl4.3 [g, /*/hg
- 4. Tank T055/56 - Nozzle F 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison PAGE 1 01/27/93 RQ1456 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZILE F
! N P U T 0 A T A
........1........2........3........4........5........6...-....7......-.8 1
2 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056. N0ZZLE F LOC 3 VD=480.1875,VT=0.42 C1=2.875,C2=2.875,SHA=CIR, 4 P=231,VL=554,VC=149,ML=14352 MC=3228,MT=852, S CAS SO, 6 MA=11240356, 7 P0a5 8 SM 20, 9 LOC 10 P=231,VL=554,VC=149,ML=14352,MC=3228,MT=852, 11 CAS=$E.
12 M9=11240356, 13 PD=5,
- 14 SM=20, 1
BIJLAARD STRESS ANALYS15 FOR CYLINDERS ME101/M10 S. C. Edison PAGE 2 01/27/93 RQ1456 l
l LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056. N0Z2LE F 1 l
I N P U T 0 A T A P ML MC MT VL VC MA MB STRESS (LBS) (IN.L85) (IN LBS) (!N.LBS) (LBS) (LBS) (FT.LBS) (FT.LBS) LEVEL 1 555$b 55bbh$b bhhb$b b55$b hhk$b 5k9$b55h$b3hb$b b bb 2 231.0 14352.0 3228.0 852.0 554.0 149.0 .011240356.0 SE 1
VESTHK VE50!A C1 C2 SHAPE SCALE SM PRESSURE BEND R (IM) (IN) (1N) (1N) FACTOR 1 (PSI) 1
.420
....................................................(KSI) 480.188 2.875 (IM) 2.875 CIRCULAR .000 20.0 5.0 .000 2 .420 480.188 2.875 2.875 CIRCULAR .000 I 20.0 5.0 .000 .
l BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison PAGE 3 01/27/93 RQ1456 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056. N0ZZLE F SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET -
nrt: iCNNO. ,A. O, CCN CONVIRSION Project or DCP/MMP SONGS 2 Calc No. M.0SC 'LF O CCN No. CCN -
Subject See Title Sheet Sheet No. 59 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA8!L M. EL-AKILY 3/5/1993 [-g , fuh3
) N .n-A u-Y Gls)?2 f/C. //f/S >
+
CASE 1 VESSEL DIAMETER = 480.188 "NCHES C1 = 2.875 INCHES C2 = 2.875 INCHES l GA* A = 571.652 BETA 1 = .005 BETA 2 = .005 j l
- COMB!NED $ TRESS I h T E N S I T Y, S (K S !), AT ***
l l
INWARD END OF LONG. MOM. OUTWARD END OF LONG. MOM. IhWARD END OF CIRC. MOM. OUTWARD END 1 0F CIRC. MOM. l VESSEL THICKNESS OUTSICE INS!DE OUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE 1 EkMPT l
(INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL 07 SHELL ' 0F SHELL OF SHELL CF SHELL MAXIMLN PRIMARY PLUS SECONDARY STRESS INTENSITY 4200 -43.87 31.43 42.13 29.34 12.27 10.43 9.22 '
8.42 '
MAX! MUM PRIMARY MEMBRANE STRESS INTENSITY 10.22 10.22 9.91 9.91 1.24 1.24 1.14 1.14 1
1 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 01/27/93 RQ1456 l PAGE 5 l
l LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE F l
l l
CASE 1 THIS CALCULATION IS FOR A LUG ON STRAIGHT P!PE l
MAXIMUM PRIMARY PIPING STRESS INTENSITY. -.............--............. 3.2 (KSI)
MAXIMLN PRIMARY LOCAL MEMBRANE STRESS INTENSITY.--.................... 10.2 (KSI)
MAXIM.N COMBINED PRIMARY MEMBRANE STRESS INTENSITY.................... 13.4 (KSI) l 1
ALLOWABLE ( 1.500 Se )..................................... ..........
30.0 (KS!)
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 01/27/93 RQ1456 PAGE 6 j
1 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0Z2LE F CASE 2 YESSEL DIAMETER = 480.188 INCHES C1 = 2.875 INCHES C2 = 2.875 INCHES gam A = 571.652 BETA 1 = .005 BETA 2 = .005 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET t&O. ,A , 0, Project or DCP/MMP SONGS 2 O CCN CONVER$!0N Calc No. M-DSC > C CCN No. CCN .
, subject See Title Sheet Sheet No. 70 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE
' DATE O NA8IL M. EL AKILY 3/5/1993 Kf hfg /
} M-EL.- A k iLY 10/5/O 7 (, /M-fn i
- COMBINED STRE$$ 1NTEN$!TY, 5 (K S !). AT ***
INWARD END OF LONG. MCH. OUTWARD END OF LONG. MOM.
4 0F CIRC. NOM. INWARD END OF CIRC. MOM. OUfWARD ENO
- VESSEL THICKNE33 OUTS!0E INSIDE OUTS!0E INSIDE INSIDE OUTS!0E INSIDE
( OUTSIDE (INCHES) 0F SHELL OF SHELL OF SHELL
- OF SHELL OF $ HELL 0F SHELL OF SHELL OF SHELL t ..............................................................................................................
4 MAXIMLN PRIMARY PLUS SECONDARY STRESS INTENSITY 4 .4200 -43.87 31.43 42.13 4
8.42 29.34 12.27 10.43 9.22 i
MAXIMLN PRIMARY MEM8RANE STRESS INTENSITY 10.22 10.22 9.91 9.91 1.24 1.24 1.14 i
I BIJLAARD STRESS ANALYSIS FOR CYLIN0ERS PAGE 8 ME101/M10 S. C. Edison 01/27/93 RQ1456 LOCAL STRESS ANALYSIS FOR CCW TANK T 055/T.056, N0ZZLE F 2
CASE 2 f TH13 CALCULATION IS FOR A LUG ON STRAIGHT PIPE 1
MAXIMLN SECONCARY PIPING STRESS INTENSITY................-............. 4.6 (KSI)
MAXIl4.N PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY....... 43.9 (KS!)
?
MAXIMUM COMBINED PRIMARY PLUS SECONDARY MEM8RANE STRESS INTENSITY..... 48.5 (KSI) l 1
ALLOWABLE ( 3.000 Sm )................................................ 60.0 (KSI) i 81JLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 9 ME101/M10 S. C. Edison 01/27/93 RQ1456 !
l LOCAL STRESS ANALYS15 FOR CCW TANK T.055/T 056, N0ZZLE F \
i SUPNARY TABLE j (KSI) I P! PING LOCAL l CASE I PRIMARY SECONDARY PRIMARY SECONDARY COMBINEO ALLOWABLEMAX SHEAR ALLOWABLE '
+ PRIMARY 1 3.2 .0 10.2 .0 13.4 30.0
\
2 .0 4.6 .0 .0 '
.0 43.9 48.5 60.0 .0 .0 I 1
SCE 26-426 NEW 4/90 ,
I l
I
NES&L DEPARTMENT CALCULATION SHEET ::r ,; L O. , ACE ,,
Project or DCP/ HHP SONGS 2 CCN CONVERSION Cale No. M-OSC .> i'O CCN NO. CCN -
Subject See Title Sheet Sheet No. 7I REV CRIGINATOR DATE IRE OATE REV ORIGINATOR DATE IRE DATE O WAstL M. EL AKILY 3/5/1993 7,,,,f , 7/qfg#
i 1
H-EL 19 kIL Y 1015) 93 Sc r+
'3fk 4
l 1 I
BIJLAARD STRESS ANALYSIS FOR CYLINDERS
, PAGE 11 ME101/M10 S. C. Edison 01/27/93 RQ1456 l
ME101LS version M10 ' top on 01/27/93 at 17:14:57 s
ME101LS version M10 run time .00 seconds 4
J 1
I l
l f
i J
a f
SCE 25-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET t n ,0. ,AO, ,,
Project or DCP/MMP SONGS 2 CCN CONVERSION Cale No. M-DSC 80 CCN No. CCN -
Subject See Title Sheet Sheet No. D I REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NABIL M. EL.AKILY 3/5/1993 f,g, Q/g i , H .EL- A K V-Y l0)S] 93 7-6. /p/ffq1,
- 5. Tank T055/56 - Nozzle G 1
B!JLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 1 ME101/M10 5. C. Edfson 01/27/93 R03318 i
LOCAL STRESS MALYS!$ FOR CCW TMK T.055/T.056, N0ZZLE G l
! N P U T 0 A T A
.........t........ 2........ 3........ 4........ 5........ 6........
7........ 8 I
1 LOCAL STRESS MALYS!$ FOR CCW TMK T.055/T.056, NQZZLE G 2 LOC 3 V0 480.1875,VT=0.53,C1=2.375,C2 2.375.SHA=CIR, 4
P=122,VL=1088,VC=167,ML=15852,MC=4788,MT=840, 5 CAS=50, 6 MA=11240356, 7 PC S. ,
8 SM=20, l 9 LOC 10 P=122,VL=1088,YC=167,ML=15852.MC=4788,MT=840, 11 CAS=$E, 12 M8=11240356, 13 Po=5 14 SM 20, 1
BIJLAAR0 STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 2 01/27/93 RQ3318 LOCAL STRESS MALYSIS FOR CCW TMK T.055/T.056, N0ZZLE G
! N P U T 0 A T A P ML MC MT VL VC MA MB STRESS (LBS) (IN.LBS) (IN.LBS) (IN.LBS) (LBS) (LBS (FT.LBS)
I ..........................................................)....(FT.LBS) 122.0 15852.0 LEVEL 4788.0 840.0 1088.0 167.011240356.0 .0 50 2 122.0 15852.0 4788.0 840.0 1088.0 167.0 .011240356.0 SE VESTHK VES0!A C1 C2 SHAPE SCALE SM PRESSURE BEND R (1N) (IM) (IN) (IM) FACTOR 1 (PSI) (!N) 1
.................................................................(KS!)
.530 480.188 2.375 2.375 CIRCULAR .000 20.0 5.0 .000 2 .530 480.188 2.375 2.375 CIRCULAR .000 20.0 5.0 .000 1
8!JLAAR0 STRESS ANALYSIS FOR CYLINDERS MC101/M10 S. C. Edison PAGE 3 01/27/93 RQ3318 LOCAL STRESS MALYSIS FOR CCW TANK T.055/T.056, N0Z2LE G SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET = = NO. , AGE 0, l
Project or DCP/MMP SONGS 2 CCN CONVERSION Calc No. M-DSC ,V O CCN No. CCN -
subject See Title Sheet Sheet No. D 1 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 3/5/1993 3/g j/y 3
- f 4- l I H .6L-f k I LV 101Gl43 Fc. '*&/n CASE 1 VESSEL DIAMETER = 480.168 INCHES C1 =
)
2.375 INCHES C2 = 2.375 INCHES I GA M A = 453.007 BETA 1 = .004 BETA 2 = .004 1 1
- COMBINED $TRE$$ ! N T E N S I T Y, S (K $ !), AT ***
1 INWARD END OF LONG. MOM. CUTWARD END OF LONG. MOM.
OF CIRC. MON. INWARD END OF CIRC. MOM. OUTWARD END VESSEL THICKNESS OUTSIDE INSIDE OUTSIDE INSIDE INSIDE OUTSIDE INSIDE OUTSIDE (INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL 0F SHELL OF SHELL l
MAXI >tJM PRIMARY PLUS SECONDARY STRESS INTENSITY
.5300 36.74 30.29 36.03 -29.55 10.51 12.62 11.13 11.65 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY 7.99 7.99 7.87 7.87 1.25 1.49 1.25 1.49 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 5 01/27/93 RQ3318 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056 N0ZZLE G CASE I THIS CALCULATION !$ FOR A LUG ON STRAIGHT P!PE MAXIMUM PRIMARY PIPING STRESS INTENSITY.......-....................... 2.5 (KSI)
MAXIHLN PRIMARY LOCAL MEMBRANE STRESS IN TENSITY....................... 8.0 (KSI)
MAXIMUM COMBINEO PRIMARY MEMBRANE STRESS INTENSITY...-...-............ 10.5 (KSI) 1 ALLOWABLE ( 1.500 Se )................................................ 30.0 (KSI)
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 6 01/27/93 RQ3318 LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056, N0ZZLE G .
CASE 2 VESSEL DIAMETER = 480.188 INCHES C1 = 2.375 INCHES C2 = 2.375 INCHES GA>94A = 453.007 BETA 1 = .004 BETA 2 = .004 SCE 26 426 NEW 4/90
NES&L DEPARTMENT
- CALCULATION SHEET = n NO. ,A , 0, Project or DCP/MMP CCN CONVERS10N SONGS 2 Calc No. M-DSC 'l 70 CCN NO. CCN -
subject See Title Sheet Sheet No. ' 7 9 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-ACILY 3/5/1993 Q. 7,Q[g
/ N -E L-@'3 LV 10/ 5/ 93 R. /"/@ -)
1 1
i
- COMB!NED 5 TRESS I N T E N 5 I T Y, 5 (K $ 1). AT ***
INWARD END OF LONG. MOM. QUTWARD END OF LONG. MOM.
0F CIRC. MOM. INWARD END OF CIRC. MOM. OUTWARD END VESSEL THICKNESS OUTS!DE INSIDE OUTSIDE INSIDE i INSIDE OUTSIDE INSIDE QUTSIDE 1
(INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.5300 36.74 30.29 36.03 10.51 29.55 12.62 11.13 11.65 l
MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY
! 7.99 {
7.99 7.87 7.87 1.25
- 1.49 -1.25 1.49 l
4
] 1 I d
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 1, PAGE 8 01/27/93 RQ3318 i ,
i LOCAL STRESS ANALYS!$ FOR CCW TANK T-055/T.056, N0ZZLE G I
i !
- 1 CASE 2 THIS CALCULATION 15 FOR A LUG ON STRA!GHT PIPE 1 i
a MAXIMUM SECONDARY PIPING STRESS INTENSITY.-..-..--..-...-.-...-...-... 3.7(KSI) i 1
1 MAXIMUM PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY.......36.7 (KSI)
MAXIMUM COMBINED PRIMARY PLUS SECONDARY MEMBRANE STRESS INTENSITY..... 40.4 (KS!)
1 ALLOWAB LE ( 3.000 Se ) . . -- ..-- .-.---...----- . -- . .----- . . .. . ..... ... . 60.0 (KSI) a BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 9 01/27/93 RQ3318 LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T-056. N0ZZLE G i'
SUPHARY TABLE (KSI) a PIPING LOCAL CASE PRIMARY SECONDARY PRIMARY SECONDARY COMBINED ALLOWABLE MAX SHEAR ALLOWABLE
+ PRIMARY I 2.5 .0 8.0 .0 10.5 30.0 .0
.0 .0 2 3.7 .0 36.7 40.4 60.0 .0 .0 i,
- SCE 26 426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :::,:oiCNNO . ,, 0, CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. CCr, No. CCN -
M-OSC- E YO subject See Title Sheet 7D" Sheet No.
REV ORIGINATOR DATE IRE l DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL-AKILY 3/5/1993 f 4, 7[gp.7
\ U c~L- A k t W lCl5l @] [4. f*ff4 '$
1 1
BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison PAGE 11 01/27/93 RQ3318 ME101LS Version M10 stop on 01/27/93 at 17:33:18 NE101LS Version M10 run time .00 seconds SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ="n No. ,, ,,
Project or DCP/MMP SONGS 2 M.DSC ~2.go CCN CONVERSION Calc Ho. CCN NO. CCN .
Subject _ See Title Sheet Sheet No. b REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NABIL M. EL-AKILY 3/5/1993 f 4. ~2Qg l N.El. .&kt L Y C]J/tf] pt, M/gfy
- 6. Tank T055/56 - Nozzle H l
1 BIJLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 1 ME101/M10 5. C. Edison 01/25/93 PP3443 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.C56, N0ZZLE H I N P U T 0 A T A
........1........2....-...3-.......4........-5........6....,....7........8 1 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE H 2 LOC 3 v 0 =480.187 5, VT =0. 53.C 1 4. 5,C2 =4. 5, SHA =CIR, 4 P=291,VL 1265,VC=476,ML=43740,MC=15912,MT=1380, 5 CAS=SO, 6 MA=11240356, 7 PO=5, 8 SM 20, 9 LOC 10 P=291,VL=1265,YC=476,ML*43740,MC=15912.MT=1380, 11 CAS=SE, 12 M8=11240356, 13 PD=5, 14 SM=20, 1
BIJLAARD STRES$ ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 2 01/25/93 PP3443 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE H 1 N P U T 0 A T A P ML MC MT VL VC MA MB STRESS (LBS) (IN.LBS) (IN LBS) (IN.LBS) (LBS) (LBS) (FT.LBS) (FT LBS) LEVEL 1 bhk b khhkb b [h9kb b [b8bb [2hhb kh6bk[hkbbb6b b kb 2 291.0 43740.0 15912.0 1380.0 1265.0 476.0 .011240356.0 SE VESTHK VE50!A C1 C2 SHAPE SCALE SM PRESSURE BEND R
(!N) (IM) (IM) (IN) FACTOR 1 (KSI) PSI !N 1
............................................................................(....)......(...)...
.530 480.188 4.500 4.500 CIRCULAR .000 20.0 5.0 .000 2 .530 480.188 4.500 4.500 CIRCULAR .000 20.0 5.0 1
.000 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 3 01/25/93 PP3443 LOCAL STRESS ANALYSIS FOR CCW TANK T 055/T.056, N0ZZLE H SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =,:LO. , AGE 0, CCN CONVER$10N Project or DCP/MMP SONGS 2 Calc No. M-OSC- M C CCN NO. ccN -
sebject See Title Sheet N Sheet No.
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE t
0 NA81L M. EL-AK!LY 3/5/1993 % 4, ]/2th t
~~~
} F1. EL- A k l L.Z 1D}1] J g. lo&43 i
L CASE 1 VESSEL O!AMETER = 480.188 INCHES C1 = 4.500 INCHES C2 = 4.500 INCHES GAM 4A = 453.007 BETA 1 = .008 BETA 2 = .008 9
- COM8INED STRE$$ ! N T E N 31 T Y, S (K $ !), AT ***
INWARD END OF LONG. MOM. OijiWARD END OF LONG. MOM. INWARD END OF CIRC. MOM. OUTWARD END OF CIRC. MGM.
VESSEL THICKNESS OUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE INSIDE OUTSIDE INSIDE i
(INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL j OF SHELL OF SHELL i
i ..............................................................................................................
MAXIMUM PRIMARY PLLS SECONCARY STRESS INTENSITY l
.5300 l 50.10 41.02 48.56 39.37 -21.80 19.10 19.34 17.47 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY t 4
11.47 11.47 11.20 11.20 1.90 -1.90 1.73 1.73 1
BIJLAARD STRESS ANALYS!$ FOR CYLINOERS ME101/M10 5. C. Edison 01/25/93 PP3443 PAGE $
LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056, N0ZZLE H CASE 1 THIS CALCULATION IS FOR A LUG ON STRAIGHT P!PE MAX IMLN PRIMARY P! PING STRESS INTEN SITY............................... 2.5 (KSI) i 1
MAXIMJM PRIMARY LOCAL MEM8RANE STRESS INTENSITY....................... 11.5 (KS!) l MAXIMJM COM8!NE0 PRIMARY MEMBRANE STRESS INTENSITY.................... 14.0 (KS!)
A L LOWA8 L E ( 1. 500 Se ) ..... . . .. -......... - . . . .- .. .. . . .. .. . -. . . . . .. .... 30.0(KSI) 1 B!JLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison 01/25/93 PP3443 PAGE 6 LOCAL STRESS ANALYSIS FOR CCW TANK T-055/T.056, N0ZZLE H CASE 2 VESSEL O!AMETER = 480.188 INCHES C1 = 4.500 INCHES C2 = 4.500 INCHES GAPNA = 453.007 BETA 1 = .008 BETA 2 = .008 l
l SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =&O. ,A,E ,,
Project or DCP/MMP CCN CONVERSION SONGS 2 ._, Cale No. H-DSC "Lf o CCN NO. CCN -
Subject See Title Sheet Sheet No. ~7 6 l REV ORIG!WATOR DATE !RE DATE REV CRIGlWATOR DATE IRE DATE O NABIL M. EL AKILY 3/5/1993 Q, 7kg 9
) u .El.-94 Ly fDM/'l] T G. '*s/gs
/
i
- C0MSINED $ TRESS INTENSITY, 5 (K S !). AT ***
INWARD END OF LONG. MOM. OUTWARD END OF LONG. MCM.
OF CIRC. MOM. INWARD END OF CIRC. MOM. QUTWARD END VESSEL TH!CKNESS OUTSIDE INSIDE ClJTSIDE INSIDE OUTSIDE INSIDE INSIDE OUTSIDE
(!NCHES) CF SHELL OF SHELL OF SHELL OF SHELL CF SHELL OF SHELL OF SHELL OF SHELL d
4 MAX! MUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.5300 50.10 41.02 48.56 -39.37 21.80 17.47 19.10 19.34 I
MAXIMUM PRIMARY MEM84ANE STRESS INTENSITY 11.47 11.47 11.20 11.20 -1.90 1.73 1.90 1.73 -
1 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 8 01/25/93 PP3443 LOCAL STRESS ANALYSIS FOR CCW TANK T-055/T.056, N0ZZLE H CASE 2 THIS CALCULATION !$ FOR A LUG ON STRAIGHT PIPE a
J
- MAXIMUM SECONDARY PIPING STRESS INTENSITY.....---.....---.--...--..... 3.7 (KS!)
i
, MAXI >tJM PRIMARY PLUS SECONDARY LOCAL MEM8MNE STRESS INTENSITY....... 50.1 (KS!)
d MAX!MLM COM8!NEO PRIMARY PLUS SECONDARY MEMBRANE STRESS INTENSITY..... 53.8 (KS!)
4 1
ALLOWABLE ( 3.000 Se )---.--. -.-.-.--.-.--.---.-..-.....---..-.. --.. 60.0 (KSI)
)
' BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 5. C. Edison 01/25/93 9P3443 PAGE 9 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE H I
SUPHARY TABLE (KS!)
PIPING LOCAL CASE PRIMARY SECONDARY PRIMARY SECONDARY COMBINED ALLOWABLE MAX SHEAR ALLOWABLE
+ PRIMARY
- 1 2.5 .0 11.5 .0 14.0 30.0 .0 .0 2 .0 3.7 .0 50.1 53.8 60.0 .0 .0 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET 1:::,:%0. ,A,, ,,
i Project or DCP/MMP SONGS 2 CCN CONVERSION Calc No. M-DSC- L 80 CCN NO. CCN -
subject See Title Sheet Sheet No. 29 REV ORIGINATOR I DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 NA8IL M. EL AKILY 3/5/1993 Kf 7k/g I
n -et.-6 k t LV 1011/ 9] fg , tejg' p 1
- 1 v
B!JLAARD STRESS ANALYSIS FOR CYLINDERS
, PAGE 11 ME101/M10 5. C. Edison 01/25/93 PP3443 l
MC101LS Version M10 stop on 01/25/93 at 16:34:43 ME101LS Version M10 run time .00 seconds l
9 l
l
\
1 1
l l
l l
i l l
SCE 26 426 NEW 4/90 l
l
1 NES&L DEPARTMENT CALCULATION SHEET =mo. ,m 0, Project or DCP/MMP SONGS 2 CCN CONVERSION Calc No. M.0SC- t 8 O CCN No. CCN .
subject See Title Sheet Sheet No. 80 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA8IL M. EL.AKILY 3/5/1993 f-f, yM$
l U.EL-hv.ILY FC .
lo/S/41 /-fd%
7.
1 Tank T055/56 - Nozzle J 81JLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 1 ME101/M10 S. C. Edison 02/17/93 H05443 LOCAL STRESS ANALYSIS FOR CCW TANC Y.055/T.056, N0ZZLE J
! N P U T 0 A T A
........1........2........3........4........5........6........7........8 1
LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE J 2 LOC 3 VD=480.3125,v7=0.3125,C1=4.5.C2=4.5.SHA=CIR, 4
Pa93.VL=1183,VC=90,ML=8976.MC=1236,MT=2040, 5 CAS=SO, 6 MA=31847675, i 7 P0=15, 1 8 SM.20, 9 LOC 10 I P*93,VL=1183,VC=90,ML=8976,MC=1236,MT=2040, 11 CAS.SE, 12 M8=31847675, 13 PO=15, 14 SM=20, 1
BIJLAARD STRESS ANALYSIS FOR CYL!NDERS PAGE 2 ME101/M10 S. C. Edison 02/17/93 H05443 LOCAL STRZ$$ ANALYSIS FOR CCW TANK T.055/T.056, N0ZZLE J l
I N P U T 0 A T A 1
................................. )
P ML MC MT VL VC MA MB STRESS 2
1 ...!!!!!...!!":i!5!..!!":!!'.0!..!!":i!!!...!!!!!......!!!!!...!'!:5!!!..!":!!!!....tE!!..
93.0 93.0 8976.0 4976.0 1236 1236.0 2040.0 2040.0 1183.0 90.031847676.0 .0 SO i
1183.0 90.0 .031847676.0 SE 1
VESTHE VESDIA C1 C2 SHAPE SCALE SM PRESSURE BEND R (IN) (IN) (1N) (IN) FACTOR 1 l 1
.................................................................(KSI)
.312 480.312 4.500 (PSI) ([N) i I
4.500 CIRCULAR .000 20.0 15.0 .000 2 .312 480.312 4.500 4.500 CIRCULAR 1
.000 20.0 15.0 .000 BIJLAARD STRESS ANALYSIS FOR CYLINDERS ME101/M10 S. C. Edison PAGE 3 02/17/93 H05443 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056, N02ZLE J CASE 1 .
l 1
I SCE 26 426 NEW 4/90 l l
l l
NES&L DEPARTMENT CALCULATION SHEET ::en No . ,A. O,
~
Project or DCP/MHP SONGS 2 CCN CONVER$10N Calc No. H-OSC- ? Y o CCN NO. ccN -
Subject
, See Title Sheet Sheet No. Of REV ORIO!WATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE D NA8IL M. EL.AK!LY 3/5/1993 f, f , $g'g l.
l H n- A W tLY 'ois/n R, to/gn o
Y VESSEL O!AMETER = 480.312 INCHES C1 = 4.500 INCHES GAmA = 768.500 C2 = 4.500 INCHES BETA 1 = .008 BETA 2 = .008
- C0MSINED STRE$$ ! N T E N $ ! T Y. S (K S !). AT ***
INWARD END OF L0hG. M:M. CUTWARO END OF LONG. MCM.
OF CIRC. MCM. INWARD END OF CIRC. MOM. QUTWARD END VESSEL THICKNESS CUTSICE lNSIDE OUTSIDE INSIDE INSIDE OUTSIDE INSIDE CUTS!0E (INCHES) 0F SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL OF SHELL MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.3125 -30.01 17.69 29.02 3.67 16.31 5.78 4.73 4.17 MAXIM.lM PRIMARY MEMBRANE STRESS INTENSITY 7.88 7.88 7.68 1.52 7.68 . 95 . 95 1.52 !
f BIJLAARD STRESS ANALYSIS FOR CYLINDERS !
PAGE 5 ME101/M10 5. C. Edison 02/17/93 H05443 1
LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.U56. N0ZZLE J l i
CASE 1 THIS CALCULATICN IS FOR A LUG ON STRA!GHT PIPE MAX IMUM PRIMARY P !,' INS STRESS !
INTEN$1TY....-.......................... 12.5 (KS!)
MAX! MUM PRIMARY LOCAL MEMBRANE STRESS INTENSITY.....................-. 7.9 (KSI)
MAXIMUM COMBINED PRIMARY MEMBRANE STRESS INTENSITY.................... 20.4 (KSI) 1 ALLOWABLE ( 1.500 Se )................................................ 30.0(KS!)
BIJLAARD STRESS ANALYS1$ FOR CYLINDERS PAGE 6 ME101/M10 S. C. Edison 02/17/93 H05443 i LOCAL STRESS ANALYS!$ FOR CCW TANK T.055/T.056. N0ZZLE J CASE 2 YESSEL DIAMETER = 480.312 INCHES C1 4.500 INCHES C2 =
GAMA = 768.500 4.500 INCHES SETA1 * .008 BETA 2 = .008 COMBINED STRESS I N T E N S ! T Y. 5 (K $ !). AT ***
SCE 26 426 NEW 4/90 1
v - ' ' = = = ~ -- " ~~
_ _ _ _ w .._, a n,.A, NES&L DEPARTMENT i
i CALCULATION SHEET : : n NO. ,,,, 0, Project or DCP/MMP SONGS 2 CCN CONVERSION
, Calc No. M.0SC- 7 EO CCN NO. CCN . ,
1 subject See Title Sheet o, Sheet No. 5 t-REV ORIGINATOR DATE !RE DATE REV CRIGINATOR DATE !RE DATE 0 NA8!L M. EL.AXILY 3/5/1993 %6. 7/g/4 y l N *EL-6k.I L.f W/S/43 pg, /f %
INWARD END OF LONG. MCM. OUTWARD END OF LONG. MCM.
OF CIRC. MCM. INWARD END OF CIRC. MON. CUTWARD END VESSEL THICKhESS OUTSIDE INSIDE OUTSIDE INSIDE
' INSIDE OUTSIDE INS!DE OUTSIDE (INCHES) 0F SHELL OF SHELL OF SHEi.L OF $ HELL 0F SHELL OF SHELL OF SHELL OF SNELL i ..............................................................................................................
MAXIMUM PRIMARY PLUS SECONDARY STRESS INTENSITY
.3125 30.01 17.69 29.02 3.67 -16.31 5.78 4.73 4.17 MAXIMUM PRIMARY MEMBRANE STRESS INTENSITY 7.88 7.88 7.68 7.68 1.52 . 95 . 95 1.52 BIJLAARD STRESS ANALYSIS FOR CYLINDERS PAGE 6 ME101/M10 5. C. Edison 02/17/93 N05443 J
LOCAL STRESS ANALYSIS FOR CCW TANK T-055/T.056, N0ZZLE J CASE 2 THIS CALCULATION IS FOR A LUG CN STRAIGHT P!PE MAXIMLPt SECONOARY P! PING STRESS INTENSITY............................. 18.3 (KS!) .
f MAXIMUM PRIMARY PLUS SECONDARY LOCAL MEMBRANE STRESS INTENSITY......- 30.0 (KSI)
MAXIMUM COMBINED PRIMARY PLUS SECONDARY MEM8RANE STRESS INTENSITY..... 43.3 (KSI) i 1
ALLOWAB LE ( 3.000 Se ) . . .. . .. .. .. . ....... .. .. .. . . .. . . .. . . . .... . .- . ... . 60.0 (KSI)
BIJLAARD STRES$ ANALYS!$ FOR CYLINDERS ME101/M10 5. C. Edison PAGE 9 02/17/93 N05443 LOCAL STRESS ANALYSIS FOR CCW TANK T.055/T.056. N0ZZLE J StM1ARY TAFLE (KSI)
P! PING LOCAL a
CASE PRIMARY SECONDARY PRIMARY SECONDARY COM8!NED ALLOWABLE MAX SHEAR ALLOWABLE
+ PRIMARY
............g...........3.......g.........3........3........7...........................
2 .0 18.3 .0 30.0 48.3 60.0 .0 .0 3 .,,
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET g r n No. ,A. ,,
4 Project or DCP/MMP SONGS 2 CCN CONVERSION Calc No. - M-DSC-280 CCN No. CCN -
srbject See Title Sheet sheet No. O3 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE 1RE DATE D NABIL M. EL AKILY 7/27/1993 JUN GAOR N . 7/27/1993 l 9 EL-AkILY l*/'/ U Q, '*h i
d 8.5 Allowable Maximum Out-of-Roundness 4
, Per ASME Code, Subsection ND-4224 (Reference 2), the difference in inches between the maximum and minimum diameters at any cross section shall not exceed 1% of the
- average diameter, or D,y,/100, where D,,, is the average diameter of the PPMS tank under consideration or 12" whichever is less. The same Code Subsection also
! specifies bottom that diameter junctures, should be measured 6 ft or one plate width from top or respectively.
4 It follows that:
, D,y, = 480 + 0.2278 = 480.2278" where the average wall thickness is 0.2278" per Appendix A of this calculation.
It follows that the tolerance is given by:
1 D,y,/100 = 480.227/100 = 4.8" i
Therefore,themaximumallowabledifferenceincross-sectionaldiametersis4.8"j (0.4').
i '
L A survey of SONGS-2 tank, T056, was performed for roundness at elevations 7' I above the bottom and 6'below the top. Results of the survey (Reference 26) are
, attached in Appendix D. These results can be summarized as follows:
1 a) At elevation 7':
Maximum diameter = 40.1',
Minimum diameter = 39.94' i
l b) At elevation 6' below the top:
Maximum diameter = 40.065',
Minimum diameter = 39.845' The above measurements correspond to a maximum out-of-roundness of 0.22' (2.64"),
which meets the ASME Code requirements calculated above.
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ="n No. ,A E ,,
CCN CONVER$!ON Project or DCP/MP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN -
subject See Title Sheet Sheet No. [k REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL AKILY 7/27/1993 JUN GAOR ((. 7/27/1993 l M s ETL-4ksLy 10} ]/ 4 3 ~[- 6 . /*/rf9) s j
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1 3
l APPENDIX - A 1
- PPMS DESIGN REPORT SCE 26-426 NEW 4/90
l sheeb B'S Report No.: SIR-92-063 k : C4lgW M - O SC- 260 Revision No.: 0 Project No. : SCE-16Q
_- p i nu lou /43 WMy February, 1993 i
0-Class = I gy 9 A-el-4 k.ILY y /2e/93 2
m V-G. sungM,3/%
I
]
i 8
Evaluation and Modification of Primary Plant Make-Up Storage Tanks for SONGS, Units 2 & 3 l
Prepared for:
1 Southern California Edison Company Prepared by:
! Structural Integrity Associates, Inc.
.i .
i f
Prepared by: Date:
A. Y. Kuo Reviewed by: -
Date:
, R. A. Mattson J
INTEGRITY ASSOCIATEEINC
1 SbM d6-i SUPPLEMENT mg V1-DSC-1 Po 7I noe lofs/q,:1 Table of Contents BY "' *
- DATEW2ch Section CHECKED
,0-J' DATE 3N Pace 1.0 PURPOSE . . . . . . . . . .............. 1-1 2.0 RESULTS AND CONCLUSIONS .
.............. 2-1 1
3.0 ASSUMPTIONS . . . . . . . .............. 3-1 4.0 DESIGN INPUT . . . . . . . .............. 4-1 5.0 METHODOLOGY . . . . . . . .............. 5-1
6.0 REFERENCES
. . . . . . . . .............. 6-1 7.0 NOMENCLATURE . . . . . . . .............. 7-1 8.0 SEISMIC EVALUATION OF EXISTING TANKS ......... 8-1 8.1 General Design Information on Existing Tanks . . 8-1 8.2 Weight Calculation . ..............
8-2 8.3 Seismic Evaluation of the Existing Tank Design . 8-2 9.0 Evaluation of Modified Tanks . ............ 9-1 9.1 Proposed Modification to the Cylindrical Tank . . 9-1
, 9.2 Seismic Evaluation of the Reinforced Tank . ... 9-1 10.0 Qualification to ASME Code Design Rules . . . . ... 10-1 10.1 Tank Shell Design . .............. 10-1 10.2 Bottom Design . . . .............. 10-2 10.3 Roof Design . . . . .............. 10-2 10.4 Reinforcement of Shell Nozzles . . . . . . ... 10-4 10.5 Code Stress Limits of Tank Shells . . . . ... 10-5 10.6 Strength of Bolts . .............. 10-6 10.7 Code Stress Limits of Ring-Type Anchor Chair . . 10-7 11.0 Reconciliation with 1989 Edition ASME Code . . . ... 11-1 11.1 Material . . . . . . .............. 11-1 11.2 Design . . . . . . . .............. 11-1 11.3 Fabrication and Installation . ......... 11-1 11.4 Examination . . . . ............... 11-2 11.5 Testing . . . . . . .............. 11-2 11.6 Overpressure Protection ............ 11-2 11.7 Welding . . . . . . .............. 11-2 11.8 Stamping . . . . . . .............. 11-3 SIR-92-063, Rev. O i D1TEGEITY ASSOCIATESINC
Sh-?eh 0} '
12.0 Figures
. . . . . . . . . . . . . . . . . . . .... 12-1 Fiaure 1 Large Vertical Tank
. . . . . . . . . . . . . . . . . 12-2 i
2(a) Design Basis Earthquake Horizontal Acceleration Response Spectra at Node 1, Elevation 9'0" of Auxiliary Building
[13] . . . . . . . . . . . . . . . . . . . . . . . . . 12-3 2(b) Design Basis Earthquake Vertical Acceleration Response Spectra
[14]
at Node 1, Elevation 9'0" of Auxiliary Building
. . . . . . . . . . . . . . . . . . . . . . . . . 12-4 3(a) Operating Basis Earthquake Vertical Acceleration Response Spectra at Node 1, Elevation 9'0" of Auxiliary Building
[15] . . . . . . . . . . . . . . . . . . . . . . . . . 12-5 3(b) Operating Basis Earthquake Vertical Acceleration Response Spectra at Node 1, Elevation 9'0" of Auxiliary Building (16] . . . . . . . . . . . . . . . . . . . . . . . . . 12-6 4 Typical Anchor Bolt Chair
. . . . . . . . . . . . . . 12-7 5 Reinforcement Design of PPMST . . . . . . . . . . . . 12-8 6
Reinforcement Requirement of Tank Opening . . . . . . 12-9 7
Convective Mass (m,) and its Elevation (H,) [20] . . . 12-10 8
Parameters of the Mechanical Model [20] . . . . . . . 12-11 9
Mechanical Model of a Flexible Tank [20] . . . . . . 12-12 10 Buckling-stress Coefficient C, for Unpressurized Curved Panels subjected to Axial Compression [22] . . . . . . 12-13 11 Increase in Axial-compressive Buckling Stress Coefficient for curved Panels Due to Internal Pressure [22] . . . . . 12-14 12 Correlation Factors for Unstiffened Unpressurized Circular Cylinders subjected to Axial Compression [22] 12-15 13 Increase in Axial-compressive Buckling-stress Coefficient for Cylinders Internal Pressure [22] . . . . . . . . 12-16 14 Shear-Tension Interaction Limits of Bolts in the Modified PPMSTs (17] . . . . . . . . , . . . . . . . . . - . 12-17 SUPPUEMENT --
{
m g H- s cc.- b20 g Vi nws loIC/43 BY M E-## DME UN SIR-92-063, Rev. O ii CHECKED ES mm.a ASSOCIATESLC
Attachment A -
Overturning Moments and Shears Liquid Levels at various
............. A-1 Attachment 8 -
Diamond-Shape Buckling Stress Limits . . . . B-1 Attachment C -
Cases of ASME Boiler and Pressure vessel Code C-1 Attachment 0 -
Exasination Reconciliation with the ASME Code . . . . . . D-1 S d *C 88
~
SUPPla s t categ _ M -D sc- zeca REM 8KMYI hMe- IOl'l'17 BY# M E-AkaY m?/27/eg CHECKED. bd' DATE 'YD t
e#
SIR-92-063, Rev. O iii N
IllTEGBITY ASSOCIATESINC
i !
l List of Tables l' i !
1 Table i Ea.ste, 10-1 Reinforcement Requirement of Tank Penetrations......... 10-9 !
i i
.- SI1eeb 89 \
SUPPLEMENT ~ i i
CALC NO _M - DSC 2 Fo !
t REVISION #I I'" i l#/ 9 3 I BY N' M
- E l- A ;# C I _DATEp2o/c, i
{
CHECKED- N E DATE[23b l
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SIR-92-063, Rev. O iv INTEGBITY ASSOCIAmilNC
- 1.0 PURPOSE The two Primary Plant Makeup Storage Tanks (PPMST) at Southern California Edison's (SCE) San Onofre Nuclear Generating Station (SONGS), Units 2 and 3 were originally designed to American Petroleum Institute (API) Standard 620, 5th Edition; and constructed and tested to API Standard 650, 5th Edition (Reference l 3). These tanks were originally classified as Seismic Class II components.SCE desires to upgrade its PPMS tanks at SONGS 2 and 3 to Seismic Class I componen in order to qualify these tanks as ASME Section III, Class 3 tanks. Also, SCE i
desires to evaluate the PPMS tanks for the issues related to Nuclear Regulatory Commission (NRC) Unresolved Safety Issues (USI) A-46. This report provides the re-qualification analysis of the PPMS tanks at SONGS 2 and 3 as ASME Section III, l I
Class 3 tanks and the resolution of the USI A-46 issues. l si!L90 sumauerr -
mm M - D TC-28 0 g m V\ on solSic(7 gy N-M .5 L- A kn LY y~@2/43 CHECKED. I- # ' DATE 49
/
SIR-92-063, Rev. 0 1-1 DETBGRITY AssocumEINC
f 2.0 RESULTS AND CONCLUSIONS The existing PPMST design does not meet all requirements contained in the Generic Implementation Procedure (GIP) [17]. It is recommended that the existing PPMST be reinforced with thirty-six (36) vertical stringers and thirty-four (34) additional anchor bolts around the circumference of the tank, the existing anchor chairs be removed and replaced by a new, stronger, ring-type anchor chair, and annular pad plates as illustrated in Table 10-1 be added to the man-hole penetration of the tanks. Details of the tank modification are described in Section 9.1 and Figure 5 of this report. It is shown in this report that the reinforced tanks meet all the requirements of the GIP [17] except for the fact that water inside the tanks might slosh against the roof. However, the existing tank roof design was shown to be adequate to withstand the additional internal pressure caused by sloshing. Finally, a reconciliation study on the PPMSTs with the 1989 Edition of the ASME Code concludes that the existing PPMSTs may be classifiad as-ASME Section IJ'.I, Class 3 tanks, provided that (1) the Certified I Material Test Reports (CMTRs) and, original material examination i records can be rec. overed, (2) the existing fillet welds (instead of full penetration welds required by the ASME Code) at tank shell to bottom plate junctions of the PPMSTs be accepted, (3) compliance with the roundness requirements per ND-4220 of the ASME Code can be i assured, (4) the testing procedures provided by ASME Code ND-6000 are followed, and (5) the procedures specified in Appendix B of NBIC [21] are implemented.
Sheek 9 )
l SUPPLEMENT CALCNO M-Dsc. S & D D'I nue tolSlg3 gmy BY U M G L- h u ggg % g CHECKED b- DATE D l l
l l
SIR-92-063, Rev. 0 2-1 INTEGRITY l ASSOCIATESINC
3beeh q L SUPPLEMBtr -'-
7 tfO g g _ M - DSC REVISION Y# D'" o 3#/S/4 3 3.0 ASSUMPTIONS BYN M FL-Ak/tY m 2/u/g CHECKED N f' DATEY'>lM The following assumptions were made in his evaluation:
(1) The maximum operating temperature of the PPMSTs is 120'F and the maximum ambient' temperature is 110*F as required by [2].
(2) The tank foundation is uncracked and has a compressive strength ( ff) equal to or greater then 4,000 psi as required by (11].
(3) The tanks are constructed on a " thick" concrete foundation.
Therefore, further soil-structure interaction effects (i.e.,
shear wave velocity of soil) will not have to be considered.
(4) Material properties of the additional anchor bolts will be the same or comparable to the existing anchor bolts from an evaluation standpoint, namely material ductility, ultimate strength, Young's modulus, and yield strength. l (5) The circularity tolerance requirements of ND-4220 of the ASME Code are satisfied. The tanks have to meet the circularity tolerance requirements to be qualified as ASME Code Tanks.
(6) One horizontal and one vertical earthquake need to be considered, with response combined by the Newmark procedure
[25]. That is, 100% of the horizontal earthquake will be combined with 40% of the vertical earthquake [25]. l (7) The existing bolts and the additional bolts share the loads according to the ratio of their sizes.
(8) Weight of the reinforcement stringers (see Section 9.1) is negligible compared with weight of the overall tank.
SIR-92-063, Rev. 0 3-1 AEs DTTEGRITY ASSOCIATES,1NC
4.O DESIGN INPUT l
The following data were used as design input in the evaluation:
Name of the Tank : Primary Plant Makeup Storage Tank Original Constr. Code : API-650, 5th Ed. + Supp. #'. [1]
1 Original Design Code : API-620, 5th Ed. + Supp. #1 [1]
Applicable ASME Code : Section III, Class 3, 1989 Ed. [19]
Tank Size : 40 feet dia., 34 feet high [3 thru 9]
Roof Size : R=48 feet, Self-Supported, Dome [4] l Capacity : 300,000 Gallons [2]
Sheet 99
/ l Content Specific Gravity : 1.0 [2] [
, pf SUPPLEMENT- - i Design Temperature : 18 0'F [2] 43 Maximum External Temp. : 110'F [2] REVISIONEI "" Pl#/ 93 Maximum Operating Temp. O
- 120 F [2] DATEt/23/93 CHECKED- b- DATE Yf3 Design Pressure ,
- Atmospheric [2] ,.
Tank Material : SA-240, Type 304 [3]
Chair Material : A-36 [3]
Anchor Bolt Material : A-7 (A-307) [10]
Joint Efficiency : 0.85 [1, 19]
Original Stress Report : [1]
Original Tank Spec. : [2]
Original Design Drawings : [3 thru 12]
Response Spectra Curves : [13 thru 16] and Figures 2 and 3 Tank Schemetics : Figure 1 4 A chm.l design tempcmbtne pey FcM F-75/9M k P%70 sod 3 is 10Lt* F. tloveve 1, In %is, ca\ch-bro % a. de:(9n k-cwpahre o$
120* F 1s center w, kve 'y v.ce d . (See A opu aav b, %et .D-32-)
SIR-92-063, Rev. 0 4-1 DiTEGRITY ASSOCIKIMINC
l 1
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5.0 METHODOLOGY 1
The evaluation procedures contained in Chapters 4, 5, and 7 and i l
Appendix C of the GIP [17] were used to assess seismic design of the existing PPMSTs. The GIP is developed by SQUG (Seismic l Qualification User's Group) based on EPRI's reports [25] for resolving the Unresolved Safety Issue A-46. There are twenty-one (21) steps in the GIP procedures, including capacity checks of tank shells, anchor bolts, top plates and stiffener plates of anchor chairs, and sloshing height. Since the tanks have to b'e nodified and the GIP procedures are not directly applicable to l
l reinforced tanks, alternate but compatible methods were used to evaluate the reinforced tanks. In evaluating the lower portion of the tanks, the additional stringers were smeared into the tank shell and an equivalent thickness uas used in the evaluation.
Methods specified in ASME Code Case N-284 [18] and two books by i l
Baker, et al [22,23] were used to check seismic design of the higher elevations of the. reinforced tanks. Evaluation of the higher elevations of the tank is not required by the GIP. The analysis method developed by Haroun [20] for seismic evaluation of flexible tanks was used to confirm the overturning moment and shear at the bottom of the tank calculated per the GIP [17] method, and l to calculate overturning moments and shears at higher elevations of l the tank. Haroun's paper [20] is the basis of overturing moment l 1
and shear force calculations in the GIP [17]. I sheeb qy SUPPLEMENT -
CALCNO M- Dsc_ Md l REVISIOND'* I*D3 BY M M. 6L- AklL Y _ gggg2 )2 bh3 l CHECKED M-
_DATEh/O]
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SIR-92-063, Rev. 0 5-1 l
I INTEGRITY l ASSOCIATESINC
1 1
l
6.0 REFERENCES
l l
- 1. " Design Calculations for Primary Plant Make-Up Tank", Brown-Minneapolis Tank and Fabricating Co., January 1975, SO23-407-3-97-0. l 2.
" Quality Class III, IV Specification for Atmospheric Storage Tanks
& 3",
for the San Onofre Nuclear Generating Station, Units 2 !
i SO23-407-3, February 22, 1974, including Addendum No. 1 1 dated May 30, 1974, Addendum No. 2 dated December 16, 1974, l Addendum No. 3 dated April 16, 1975, Addendum No. 4 dated October 13, 1975, Addendum No. 5 dated March 11, 1976, Addendum No. 6 dated March 3, 1977, and Addendum No. 7 dated July 16, 1981. l'
- 3. Tank Drawing, SO23-407-3-61-2, Rev. 3, 1975. Meeh T[
-\
- 4. Tank Drawing, SO23-407-3-62-3, Rev. 2, 1975.
SUPP W M --
- 5. Tank Drawing, SO23-407-3-63-3, Rev. 3, 1975. CALC NO M 4%- O @ l
- 6. Tank Drawing, SO23-407-3-64-1,'Rev. 1, 1975.! REV!SIONI #
- D7 '
i sy N- M- frL-4 k sLV DATE2h g l
- 7. Tank Drawing, SO23-407-3-65-1, Rev. O, 1975.f 0HEOKED N _DATb
- 8. Tank Drawing, SO23-407-3-66-1, Rev. O, 1975.
- 9. Tank Drawing, SO23-407-3-67-1, Rev. 1, 1975.
- 10. Anchor Bolt Schedule, Drawing No. 20009, Rev. 2, 1976.
- 11. Auxiliary Building Plan, Draw'ing No. 25000, Rev. 17, 1983.
- 12. Auxiliary Building Plan, Drawing No. 25170, Rev. 10, 1978.
- 13. SONGS 2 & 3 DBE Horizontal Response Spectra, SO23-SK-S-689, Rev. O, 1973. Also in SCE Calc. C-281-1, Rev. 1, " SONGS-2/3 Seismic Structural Response Sepctra."
O, 1973. Also in SCE Calc. C-281-1, Rev. 1, " SONGS-2/3 Seismic Structural Response Sepctra."
- 15. SONGS 2 & 3 OBE Horizontal Response Spectra, SO23-SK-S-713, Rev. O, 1973. Also in SCE Calc. C-281-1, Rev. 1, " SONGS-2/3 Seismic Structural Response Sepctra."
O, 1973. Also in SCE Calc. C-281-1, Rev. 1, " SONGS-2/3 Seismic Structural Response Sepctra."
- 17. " Generic Implementation Procedure (GIP) for Seismic Verification of Nuclear Plant Equipment", Rev. 2, Corrected 2/14/1992, SQUG.
SIR-92-063, Rev. 0 6-1 INTEGRITY ASSOCIATESINC
4 18.
ASME Code Case N-284, " Metal' Containment Shell Buckling Design Methods", Reaffirmed July 30, 1989.
19.
ASME Boiler and Pressure Vessel Code, Edition, Section III, 1989 l
20.
M. A. Haroun, " Vibration Studies and Tests of Liquid Storage Tanks", Earthquake 11, pages Engineering and Structural Dynamics, Vol.
179-206, 1983.
I 21.
National Board Inspection Code, ANSI-NB-23, Revision 7, 1989.
- 22. E. H. Baker, L. Kovalevsky, and F. L. Rish, Analysis of Shells, McGraw Hill Book Company, 1972.Structural 23.
E. H. Baker, et al, Shell Analysis Manual, NASA CR-912,1967.
24.
{
ANSI /AWWA D100-84, AWWA Standard for Welded Steel Tanks for Water Storage, American Water Works Association, 1985.
25.
EPRI NP-5228-SL, Revision 1, " Seismic Verification of Nuclear Plant Equipment Anchorage, Vol 4: Guidelines on Tanks and Heat Exchangers", June, 1991.
26.
" Manual of Steel Construction", American Institute of Steel 4
Construction, Inc., 9th Edition, 1970.
- 27. E. H. Gaylord and C. N. Gaylord, " Structural Engineering Handbook", 2nd Edition, McGraw-Hill Book Co., 1979. l l
t
~
SUPPLBENT g u-LSC-2.@
l nvL lD}N43 f y y. u.E t-nuac t ggg707lff
- 7. f , DME #!"
S rt T %
ll!
SIR-92-063, Rev. 0 6-2 q INTEGRETY ASSOCUGEINC
l ghegh q} ,
SUPPLEMENT - l CALC NO M -*
- 80 I #" I DM/ #17 REVISION 7.O NOMENCLATURE BYU El-O'M DATE2h o/93 )
7.1 From Reference 17: CHECKED b' DATE Y2V575 A, -
Cross-sectional area of embedded anchor bolt [in.2) 1 a -
Width of chair top plate parallel to shell I (see Figure 4) Un.] ]
b -
Depth of chair top plate perpendicular to shell (see Figure 4) [in.]
c -
Thickness of chair top plate (see Figure 4) [in.]
c' -
Coefficient of tank wall thicknesses and lengths under stress [dimensionless]
d -
Diameter of anchor bolt [in.]
E, -
Elastic modulus of tank shell material [ psi]
E, -
Elastic modulus of anchor bolt material [ psi]
e -
Eccentricity of anchor bolt with respect to shell outside surface (see Figure 4) (in.] '
F -
Frequency (Hz)
F, -
Allowable tensile stress of bolt [ psi]
Ff -
Frequency of fluid-structure interaction mode [Hz] ,
F, -
Reduced allowable tensile stress of bolt [ psi)
F, -
Sloshing mode frequency [Hz) f -
Distance from outside edge of chair top plate to edge of hole (see Figure 4) (in.]
f Minimum specified yield strength of shell, chair, saddle, or base plate material (psi]
G -
Acceleration of gravity [386.4 in/sect) g - Distance between vertical p!ates of chair (see Figure 4) Ein 3 H -
Height of fluid at the maximee level to which the tank will be filled (see Figure 1)
[in] l i
SIR-92-063, Rev. 0 7-1 1 INTEGENT ASSOCIATESINC 1
Shteeb ] c3 '
I j SUPPLEMENT ~
j -
CALC NO N-DSC F o
{ REVISION V' ""4 \*\'19 2 By N M E L-Ak It.X y2Jac/93
- H' -
Height of tank shell (see Figure 1) [iD*]
~
E
- j. h -
Height of chair (see Figure 4) [in.]
h, -
Effective length of anchor bolt being stretched (usually from top of chair to embedded anchor plate) (see Figure 1) [in.]
h, -
Height of shell compression zone at base of tank (usually height of chair) (see Figure 1) [in.]
h, -
Height of freeboard above fluid surface at the maximum level to which the tank will be filled (see Figure 1) [in.] j h, -
51osh height of fluid in tank [in.]
h,' -
Slosh height of fluid for a ZPA of Ig applied at tank base [in.]
j -
Thickness of chair vertical plate (see Figure 4) [in.]
k -
Width of chair vertical plate (see Figure 4). Use average width for tapered plates [in.].
M -
Overturning moment at base of tank [in-lbf]
M' -
Base overturning moment coefficient [dimensionless]
M, -
Overturning moment capacity of tank [in-lbf]
M' ,- Base overturning moment capacity coefficient [dimensionless]
N -
Number of anchor bolts [dimensionless]
P, -
Fluid pressure at base of tank for elephant-foot buckling of tank shell [ psi)
P,' -
Pressure coefficient for elephant-foot buckling [dimensionless]
P, -
Fluid pressure at base of tank for diamond-shape buckling of tank shell [ psi]
P,' -
Pressure coefficient for diamond-shape buckling [dimensionless]
l l
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l SIR-92-063, Rev. 0 7-2 f i
ASSOCIATESINC !
1 P, -
Allowable tensile load of anchor bolt [lbf]
- Q -
Shear load at base c' tank [lbf]
Q' -
Base shear load coefficient [dimensionless) ;
I Q, -
Base shear load capacity of tank [lbf]
R -
)
Nominal radius of tank [in.] (see Figure 1) 4 r -
Least radius of gyration cf vertical stiffener plate cross-i
. sectional area about a centroidal axis (in.]
53 -
R Coefficient of tank radius to shell thickness
[dimensionless) 400 t,-
Sa -
Spectral acceleration of ground or floor [g]
Sa r -
Spectral acceleration (4% damping) of the ground or floor on which the tank is mounted at the frequency of the fluid-structure interaction mode (F,) [g]
Sa, -
Spectral acceleration (1/2% damping) of the ground or floor on which (F,) [g]the tank is mounted at the frequency of the sloshing mode i
t,, -
Thickness of the tank shell deraged over the linear height of the tank shell (H') [in.]
I t -
b Thickness of bottom or base plate of tank (see Figure 4) (in,]
t,f -
Effective thickness of tank shell based on the mean of the average thickness (t,,) and the minimum thickness (t,,,) [in.}
t, ,, -
Minimum shell thickness anywhere along the height of the tank shell (H'), usually at the top of the tank (in.] !
t, -
I Minimum shell height thickness of the tank shell in the lowest.10% of the (H') [in.]
Cheeb qq SUPPLEMENT ~
CALC NO M - D SC- Wo REVG ON W' AIN- 10 / S / 9 3 BYA/#1.E&4k/ DATEE/2#/b CHECKED - 'S-
_DATE Y SIR-92-063, Rev. 0 7-3 INTEGMTY ASSOCIMEINC
j .
i i
Gltech / Og SM2MW ~~ {
g gM - D SC- Mo '
RM#' *
- 3DM/9#
BYd#'"-O'W DATE O !D CHECKED b' DATE /5S j t, -
Thickness of leg of weld (in.]
j t' -
Equivalent shell thickness having the same cross-sectional area as the anchor bolts [in..]
i V, -
Average shear wave velocity of soil for tanks founded at grade j
I
[ft/sec]
- W -
Weight of fluid contained in tank [lbf]
i Weight of tank without fluid [lbf]
j W, -
! W, '
Average shear load on weld connecting anchor bolt chair to tank l shell per unit length of weld (i.e., total shear load on chair 1 j
divided by total length of chair /shell weld) [1bf/in. of weld] !
I -
Tank shell stress reduction factor [dimensionless]
IPA -
Zero period acceleration [g]
8 -
Percentage damping [%)
1 -
Buckling coefficient [1 - 0.73 (1 - ed )] [dimensionless]
1, -
Weight density of fluid in tank [lbf/in3 ]
A7 -
Increase factor for internal pressure ;
a -
Stress at a point [ psi) i a, -
Stress at which shell buckles [ psi) '
a, -
Stress at which shell buckles in elephant-foot pattern [ psi) og -
Stress at which shell buckles in diamond-shape pattern [ psi) !
a, -
Yield strength of tank shell material (psi)
)
( -
Buckling coefficient [(I/16)(R/t,)u2] [dimensionless) 1
)
l l
1 l
1 SIR-92-063, Rev. 0 7-4 ASSOCIATEINC
l N eb lof SUPPUNENT- - !
CALC NO M - DSC- 2.pe
~
7.2 From Reference 18: i REVIStONA~~ ' nwt ioftfgi BYP' M- G L- A t<ILX y CHECKED b 5' DATE
,- f N.
! I L
i= 4,6, or && corresponding to meridicsal 1 I
direction or stress component, circem-j ferential direction or stress compor.ent, ;
and in-plane shear stress component, re-spectively.
i= 1 or 2 corresponding to & to & above 1
where I corresponds to the larger value and 2 corresponds to the smaller value. !
j=I., S. G corresponding to local buckling l (bucklmg of shell plate between stifre-ners or boundaries), stringer buckling (buckhng between rings of the shell plate and attached meridional stiffeners, and i
general instability (overall collapse), re-spectively.
4= cross-sectional area of stiffener (no ef-fective she!! included), sq in.
C,= elastic buckling coefficients.
=oyR
\
Et
- C,, C,3= elastic buckling coefficients in hoop di-rection for cylinders under uniform ex- !
1 l
l l
l i
l l
SIR-92-063, Rev. 0 7-5 l
ASSOCUGEINC
ternal pressure, cr. = 0 and e. =
0.5cr, respectively. .
n= number of waves into which shell will E= modulus of elasticity of the material at buckle in the circumferential direction.
R = shell radius, in.
Design Temperature. psi.
ES= Factor of safety. R,= radius to centroida! axis of the combined G= E stifener and efective midth of shell, in.
2(1 + p) R i . R.= efective stress radius for toroidal and !
ellipsoidal shells in the 6 and & direc-1,= mornent of inertia of stiEener in the i tions. respectively,in.
direction, about its centroidal axis, in.'
Jr,= moment of inertia of stifener plus ef. t= shell thickness, in. ,
fective width ofshell/sabout centroidal t., t , t., " A. . A, ,
axis of comb.tned section, in the i direc-t, r t.I, m t 0.5 (t, + t,) '
tion, in. l
=
/,/ , I,/
- ,= distance from centerline of shell to cen-i I' A A'#'2A,
+ t,y
- 12 troid ofstifener (positive when stiseners are on outside), in. 1 J,= torsional constant of stiffener, in.'
cy= capacity reduction factors to account for L= overall length of cylinder, in. the diference between eWM theory and predicted instability stresser for fab.
L,= length of cylinder between bnwha4 or ricated shells (% = c,c).
lines of support with suf!icient stiffness l to act as bulkheads, in. Lines of support A. A= %" P rRasticity rR reduction factor.
which act as bulkheads include end stif-feners , a cir-T' 5 i A,= the lowest multiples of the prebuckling cumferentialline on an unstisened head i
at one-third the depth of the head from stress states cr, and cry which cause the head tangent line, a circumferential linear bifurcation buckling.
= Poisson's ratio.
line at point of embedment in or an- l chorage to a concrete foundation, and cr,= calculated membrane stress components i the cylinder to head junction when the due to applied loads, psi.
cruj= theoretical clastic instability stresses, head is designed in accordance with this psi.
Case for stiffened heads. ~
cra= amplined stress components to be used I,=one half of the sum of the distances 4, on either side of an end stiffener,in. for clastic buckling stress evaluation, psi.
I,= distance in i direction between lines of
=cr,. ES/c, support, in. A line of support includes crp= amplified stress components to be used any intermediate size stiffening ring which satisfies the requirements of this for inelastic buckling stress evaluations, psi.
Case in addition to the lines of support =cr/t),
included in the defmition for 4,. ,
a,,j, cry = theoretical clastic instability stresses in lj=one-half of the sum of the distances I, the hoop direction for cylinders under on either side of an intermediate size stisener, in. external pressure, cr, = 0 and cr. .=
0.5 cr,, respectively, psi.
/,=efective width of shell acting with the cr,= tabulated yield stress of material at De-4 stiffener in the i direction, in.'
sign Temperature, psi.
"1.56 @ unless otherwise noted.
M,= l/ g g7 ggg
- "// M 8
M= smaller of M. and N, SUPPuiMEN m= number of half waves into which shell N NO g_psc_g,go will buckle in the meridional direction. - RIMSION #
gy u.M.s L- A m L y DME*/##/?J CHECKED I #' ' DME SIR-92-063, Rev. 0 7-6 ASSOCIATESINC
1 s hee 103 SUPPLEMENT -
MLC NO "' DSC- MO l gyggny W l n'^C t0H/9 3 8.0 SEISMIC EVALUATION OF EXISTING TANKS BY
- M
- M W DATE 4 CHECKED 5- DATE W11 8.1 General Design Information on Existing Tanks Design rules contained in ND-3800, " Design of Atmospheric Storage !
Tanks", of Section III of the ASME Code (19) were used to requalify the PPMSTs. The input parameters are listed in Section 4.0 of this ,
report. A schematic of the PPMST with key dimensions is illustrated in Figure 1.
8.2 Weight calculations 4
(a) Roof (W,,)
0 = Sin = 24. 6243* (see Figure 1) 6 Af = 2x[RjSin@ d@ = 189,576 incha (R,= Roof Radius =48 ')
0 , i I
i W, = p,A ft, = 0 . 2 8 3
- 18 9 , 57 6
- 0 . 2 5 = 13 , 413 Lbf
~
where 4 is the angle measured from the top of the roof, !
A is the total area of the roof plate, f p, is the weight density of steel, and t e is the roof thickness. l (b) Tank (W,)
, 0.187 5
- 24 0. 7 5 +0. 2 5 *71. 6 2 5 + 0. 312 5 *9 5. 6 25
= 0.227 8 inch j We = p ,2 x R c H 't ,y , = 0.283 *2n *240 *4 08*0.2278 = 39,664 Lbf where R, is the radius of the tank, H' is the height of the cylindrical part of the tank, and t,, is the average plate thickness of the tank wall.
(c) Product (W p)
Wp = yfxR*H = 0. 0361 *x *24 0 *3 84 = 2,508,481 Lbf 2
SIR-92-063, Rev. 0 8-1 INTEGRITY ASSOCIATESINC
1
}
where yf is the weight density of the content of the tank, and H=384 inches [2] is the maximum fluid level of the tank.
8.3 Seismic Evaluation of the Existing Tank Design d
Effects due to both the OBE and DBE need to be addressed. Design procedures provided by the Generic Implementation Procedure (GIP)
[17] for the DBE will be used to perform the earthquake evaluation of the PPMST. Terminology used in the following evaluation steps I
are all according to the GIP [17].
[ Step 1] Input Data From Design Input specified in Section 4.0 of this report, R = 240 inches H' = 408 inches tg= 0.1875 inches t, = 0. 3125 inches oy = 29,000 psi (SA-240, Type 304 at 120 *F [19])
h, = 12. 7 5 inches .
6 E, = 2 8. 03 x 10 psi (Table I-6.0, Austenitic, 120 F [19])
V, = average shear wave velocity The maximum operating temperature of 120*F [2] was used as the metal temperature of the tanks. The soil shear wave velocity is intended for evaluating soil structure interaction (SSI). However, the PPMSTs are inside a i building on a thick concrete foundation. Therefore, V, will not be considered further (see Section 3.0).
i SM T- / 0 Y yf =
0.0361 Lbf/in3 _
H = 384 inches [1,2] CALC NO
~*-NO !
!W MON # /
h, = 34.15 inches (see Figure 1) #*
N = 36 BY #' M'####"## $# M
- /#3 CHECKED 5- DATE 9 SIR-92-063, Rev. 0 8-2 INTEGRITY ASSOCIATESINC i
i l
d = 1.5 inches (10] i l
hb= 40.75 inches (10]
Eb= 29.28 x 10' psi (Table I-6.0, Carbon Steel, 110*F) l The maximum environment temperature of 110*F was used as the i l
bolt temperature.
i
[ Step 2j Parameters H/R = 384/240 = 1.6 l t,/R = 0. 3125/24 0 = 0. 0013 1
t*v = 0. 3125 *95. 625 +0.408 25 *71. 625 +0.187 5 *24 0.7 5 = 0. 227 8 inches .
t,f =
- *= 0 . 227 8 + 0.187 5 2 2 = 0. 2077 inches gheh /g [
t,f/R = 0.2077/240 = 0.000865 l l xd2 '
n*1.52 N ~
Ad= =
= 1 N 1 inch 2 4 4 CALCNO M - D S C -- 7 M '
REVISION WI W m)S/qs t, 3Fd 36*1.7671429 28
., 2xRE, 2n *240 *28.03 0.044 inches BYN N-Elr4k/LV DM/2/20/9
- vHECKED_ M DATEY2I41 c'= = 0.044*12.75 .l t,h3 = 0 . 0 4 41 0.3125*40.75 l
W = ER 2ffyf = z *24 0 2*3 04 *0. 03 61 = 2,50 8,4 81 Lbf I l
The applicable ranges of parameters specified in Table !
7-1 of the GIP [17] are satisfied, except for the t,f/R l ratio, which falls below the 0.001 to 0.01 applicable I range. However, it is -judged, based on the trend from 0.01 to 0.001, to be conservative to use the curves for
, tf/R=0.001 for the present evaluation.
[ Step 3] Tank Frequency From Table 7-3 of the GIP (17] for R = 240" and H/R = 1.6, F, = 7. 58 Hz SIR-92-063, Rev. 0 8-3 DITEGRITY ASSOCIATESINC
l Sheek lD 6 suPPLEuerr -
CALC NO M -O s C- M' d) ,
F (s, f) = 7.58*(28.03/30)0 5 = 7.33 Hz f
R N ON #' " WSM !
Period = 1/F, = 0.136 seconds BFNdW DATE $
CHECKED- ~8* DATEWD;
[ Step 4) Spectra Acceleration From the SONGS 2 & 3 seismic loading spectra (see Figures 2 and 3), it is found that, at 4% damping for DBE and 2%
damping for OBE, S , = 1.15 g (DBE)
S,, = 0. 75 g (OBE)
Thus, the DBE evaluation will be bounding, because the DBE load is 1.53 times (1.15/0.75 per [18]) the OBE load, but the OBE buckling factor-of-safety is only 1.49 times (2/1.34 per (18]) the DBE factor-of-safety.
[ Step 5] Base Shear Load From Figure 7-3 of the GIP [17), corresponding to H/R=1.6 and t,,/R=0.001, Q'=0.71 Q = Q' W S,, = 0. 71*2,508,481*1.15 = 2,048,175 Lbf
[ Step 6] Base Overturning Moment From Figure 7-4 of the GIP [17], at H/R = 1.6, M' = 0.345 M = M ' W H S,, = 0. 3 4 5
- 2 , 508, 4 81* 3 8 4
- 1.15 = 3 8 2 ,172 , 0 97 in-Lbf
[ Step 7] Bolt Tensile Capacity L = 27.5 inches [11]
D = 1.5 inches [11]
From Table C.3-1 of the GIP [17],
P = 50. 4 * (1. 5/1. 375) 2 = 59.98 kips V, = 25. 2 5* (1. 5/1. 375) 2 = 30. 05 kips
-l Sein = 17.375*(1.5/1.375) = 19 inches Lain =
- 13. 75 f. (1. 5/1. 375 ) = 15 inches E,in = 12.120*(1.5/1.375) = 13.25 inches 4
SIR-92-063, Rev. 0 8-4 INTEGRITY ASSOCIATESINC
Shee6 jo 9 SUPPLEMENT -
- CALC NO M-DSC-? ? O S= = 42.4 inches > S ein 36 REVISIONV# ""/3/5/97[
BY "'M' El ~ A k Il-Y yyg -}2c/93 2
R , = Radius of Bolt Circle = 243 inches CHECKED I d ' DATE 'N93 E = 22'6"-20'3"= 27" inches > E,in [12] '
I' > 1 %1n per [11], f', = 4000 psi > 3500 psi P,g t = P = 59.98 kips (No reduction factor is required for f[=4,000 psi per [11] and Assumption (2) in Section 3.0 of this report)
V,t t = V ,= 30.05 kips P o = P,tt = 59,980 lbf Fb= Po/Ab = 59,980/1.7671 = 33,943 psi Since, in the GIP [17), the base shear is assumed to be taken by the friction force between the tank bottom and the foundation [25], the bolts are under pure tension.
Thus, there is no need to check the shear-tension interaction limits.
l
[ Step 8] Top Plate (see Figure 4)
( O . 37 5 g-0 . 22 d) Pu fc3
, _( 0.375*2.5-0.22*1.5)*59,980 0.9375*0.8752
= 5 0,7 6 5 psi o>f =y 35,680 psi (SA-36 material at 110'F [19]
Thus, the design of the top plate of the anchor chair is not adequate, and F, = F3 (b) o
= 23,857 psi SIR-92-063, Rev. 0 8-5 INTEGRITY ASSOCIATESINC
1 l
(Step 9) Tank Shell Stress SUPPt.EMENT ~
cal.C NON-OEC-280 1
0.177 a ts Revlss0NP'I W MN/93 yy, 8Y P'"'EAk f nAf'l 7/9.7, K C, CHECKED 7'd
, 1 DAT[hl/N3 0.177*6.5*0.25 g 0.25 V240*0.3125 0.3125) ,1 97, 7Og
= 0.979 l
l l
l
,Pe[u 1.32r ,0.031) 1.43aha C ,2 R C,
+ (4 ah a) t/3 % l
, 59,980*2.6875 g 1.32*0.979
. 0.031 0.31252 1. 4 3 *6. 5 *12.7 5a )
8 240*0.3125 + (4 6. 5 *12.75 ) t/3 v240*0.3125 ;
= 64,647 psi -
I 1
l 1
1 1
a>f y ;
1 F, = F b (f y/ c ) = 33,943* (29,000/64,647) = 15,227 psi j (Step 10) Vertical Stiffener Plate j
k = (I .5+1.25)/2 t = 'l -Sf76 inches
' 3. 2C5 g ,7 g j 0.S l l
95 , 95
=15.90 i
Vf/1000 y 35,680 h 1,000 '
l
- SIR-92-063, Rev. 0 8-6 INC
SUPPLEMENT -
CALCNO M-D SC- O 20 REVISION # I "* I#/#/f 7
& 95 gy H.M. EL- A MIL Y gg33;2/2c/<yy
$ Ji/1000 y
OHECKED 5' DATE 7*YO 0.04(h-c) = 0.04*(12.75-0.875) = 0.475 inches j > 0.04 (h-c)
INI'/Of
}
' " ,77 Psi < 21,000 psi 2*3.375*0.5 The vertical stiffener plate design is adequate.
(Step 11] Chair-to-Tank Weld (see Figure 4) 1 e W" = P ( a+2h) 2,( ah+0. 6 67 h2 ) 2 1 2.6875
=59,980*$ ( 6 . 5 +2 *12.7 5 ) 2, ( 6. 5 *12.7 5 +0. 667 *12.7 5 2):
= 2,055 L2f/ inch i
30600b = 30600* 0.25 = 5 4 0 9 > W, p 6 1
Therefore, the design of the chair-to-tank weld is i adequate.
l
[ Step 12] Elephant Foot Buckling Pressure From Figure 7-7 of the GIP (17] , at S,, = 1.15g and H/R .= 1. 6, P', = 2. 8 3 6 l P, = P', y f R = 2. 836 *0. 0361*240 = 24. 57 psi The above P, value can also be derived by Eq. (2-20) of Reference 25.
SIR-92-063, Rev. 0 8-7 ENTEGBITY ASSOCIATESINC
i SUPPL.EMENT_ -
CA!.C NO M - D SC- 2, eo
[ Step 13] Elephant Foot Buckling Stress REVISIONF I W 10/r/fy ~
S3 = = 240
=1.92 kEW' 2 400c, 400*0.3125 ! _DATE 3 CHECKED _ b 8' P,R
_ DATEb
, 0 . 6 E, 1 1 y M
R/ t, of C,) 2) g. 1,12 +Sz '8 8) +1 l [ 8 +o /36000 g 1
, 0.6*28.03*10 8 24.57*240 1 240/0.3125 [y_(29000*0.3125)2][1_ 1.12 +1. 9 21 5 ) [ 1.92+1 )
= 8,66 8 psi
[ Step 14] Diamond-Shape Buckling Pressure From Figure 7-9 of the GIP [17), corresponding to H/R=1.6 and Sg=1.15, P'd = 2.063 Pd"P d Tt R = 2. 063 *0.0361*240 = 17. 87 psi similarly, the P valtte d can also.be obtained with Eq (2-
- 20) of [25].
[ Step 15] Diamond-Shape Buckling Stress 0.3125 y = 1 - 0.73 (1-e-4) = 1 - 0. 73 (1-e-1.732) , o ,399 From Figure 7-11 of the GIP [17),
Ay = 0.15 og = (0.6y+6y) E' j
=
(0. 6 *0. 399 +0.15) 28.03*10
= 14,212 psi SIR-92-063, Rev. 0 8-8 INTEGRITY ASSOCIKfESINC
1 i
l
[ Step 16] Allowable Buckling Stress !
1 o, = 0.72 [ Min (o p,, opd) ] = 0.72*8,668 = 6,241 psi I 6II T ll1
[ Step 17] Bending Moment Capacity SUPPLEMENT -
NNo M-Dsc- z-gO The weak link is in ductile failure. gj m ppg i
6,241 BY# "~ # DATENO 12.75
( "S F,) (b) h3 = ( 15,227 ) ( 40.75 ) =0.13 CHECKED b ' DATE V2-[5 3 l
l From Figure 7-12 of the GIP [17], corresponding to c'=0.0458, M'ap = 0.1 5
Therefore, M, = M'a, (2Fb ) (R2 t,) (h/h,) I 2
= 0.1*2 *15,227 *24 0 *0. 3125* (4 0. 75/12. 75) I
= 175,200,071 in-Lbf 1
) [ Step 18] Check Buckling Moment .
M>M ap
, Therefore, the tank is an outlier per the GIP [17].
l
) [ Step 19] Shear Load Capacity Qg, = 0.55 (1-0.21Sg) W ;
= 0.55*(1-0.21*1.15)*2,508,481 i
= 1,046,476 lbf I
[ Step 20] Check Shear Load Q > Qup Therefore, the tank is an outlier per the GIP [17].
[ Step 21] Slosh Height i SIR-92-063, Rev. 0 8-9 sTa w ninnt i DITEGRITY l ASSOCIATEINC l
C NCC h ll &
1 SUPPLEMENT ~
1.84G ~OSC-f.,.
2n) R tanh ( 1. 84H)
R CALC NO yi n mg., to}s/q3
, 1 1.84*386.4 BY N ' # "' ' N 2x) 240 tanh(l'84*384) 240 CHECKED NS- DATE 3'
= 0. 27 32 Hz '
a Sloshing Period = 1/0.2732 = 3.66 seconds S , = 1. 5 g at 0.5% damping per Figure 2 h, = 0. 8 3 7 R S , = 0. 8 3 7 *2 4 0 *1. 5 = 3 01. 3 2 inches i
[ Step 22] check Sloshing Height h, > hf (= 34.15 inches)
Therefore, the tank is an outlier per the GIP [17).
l t
=
1 I
SIR-92-063, Rev. 0 8-10 M
INTEGRITY ASSOCIATESINC
sh<d ll b summen -
aup-osc- veo monr i nu WNM3 9.0 Evaluation of Modified Tanks SY NW- EL-Ak/LY DATE*/2'N3, CHECKED N* DATEW1 b 9.1 Proposed Modification to the cylindrical Tank -
i The seismic evaluation presented in Section 3.3 of this report j indicates that the PPMSTs in SONGS-7;&3 do not meet the GIP [17]
seismic requirements. As shown in Steps 18, 20, and 22 of Section l
8.3, the existing PPMST design does not provide enough resistance in bending buckling, shear failure, and water sloshing. As I illustrated in Figure 5, it is proposed that (1) the existing PPMST l
l be reinforced with thirty-six equally spaced vertical stringers of j f either the same material as the shell (SA-240, Type 304) or SA-36 I l carbon steel, (2) a circumferential ring (SA-240, Type 304 or SA-
- 36) be added to cap the tops of the vertical stringers, (3) thirty-i l four additional anchor bolts (A-307 or equivalent) of 1 inches i
{ or greater in diameter be added, and (4) the existing anchor chairs
! be removed and replaced with a ring-type chair around the '
1 circumference of the tank.
- It is recommended that the same 1
i material, SA-36, be used for the top plate and stiffener plates of the ring-type anchor chair, and the top plate thickness be increased from the existing 0.875 inches to at least 1.125 inches.
I It is also recommended that the thickness of the stiffener plates of the chair be increased from the existing 1/2 inch to 3/4 inches.
l The stringers should be 1.375 inches thick, 5 inches wide, and 58
{ inches high. To accommodate for the size of concrete drilling l tools, it is recommended that the additional new bolts be placed at j 3.6875 inches radially from the tank shell outer surface, which is j 1 inch farther out radially than the existing bolts. The design j for the welds between the tank shell and the chair top-plate, the chair top-plate and the vertical stiffener plates, and the stiffener plate to tank bottom should be the same as the existing welds. The details of other components and associated welding are j shown in Figure 5. In addition, it is also recommended,per Section i 10.4 that a pad plate of the dimensions shown in Table 10-1 be
}
SIR-92-063, Rev. 0 9-1 DITEGRITY j ASSOCIATESINC i
1 added to the man-hole penetration to meet the ASME Code ND-3332.2 requirements I (see Section 10.4 of this report for details).
t 9.2 Seismic Evaluation of the Reinforced Tank Except for Steps 14 ard 15, which are not directly applicable to tanks with reinforcement stringers, the evaluation procedures provided tanks.
by the GIP (17] will be used to evaluate the reinforced The reinforcement stringers were smeared into an equivalent shell thickness and the evaluation of Steps 14 and 15 of the GIP was performed on the smeared tank shell.
- [ Step 1) Input Data The cross-sectional area of the stringers (6.875 inches 2) has to be considered and smeared I into an equivalent shell thickness. The effective increase in shell thickness is 0.1639 inches (- **1} =,0.1639) from a tension stress point of i
4
(
view 35 or 0.1676 inches from a bending stress point of view
- ** 5 *1. 37 5 [24 2. 5
- Sin (5'+10**l) ) :
(
n*2403 = 0.1676 ) .
Conservatively, smaller smeared thickness of 0.1194, corresponding to 1 stringer size of 5"x1", is used in the analysis.
From the Design Input specified in Section 4.0 of this report, l R = 240 inches j H' = 408 inches N7 // Y i
tm = 0.1875 inches SUPPLEMEIN ~
t, = 0.3125 inches N 900 " M~ #
' t , = Adjusted Tank Shell Thickness N j
= (0.3125+0.1639) = 0.4764 inches gy* W-M- c t -/}% Lkmg*l
-- /'7/41 oy = 29,000 psi '
i SIR-92-063, Rev. 0 9-2 DITEGBITY AW AWC W
h, = 12.75 inches l E, = 2 8. 03 x 106 psi V, = average shear wave velocity of soil (will not be used) yf = 0.0361 Lbf/in 3 l H = 384 inches h, = 34.15 inches (see Figure 1)
N = 70 d = 1.5 inches (existing bolts) d = 1.875 inches (new bolts)
I hb = 40.75 inches Eb= 29.28 x 10 6psi (also assumed for new anchor bolts) 2 (Step 2] Parameters H/R = 384/240 = 1.6 t,/R = 0.4764/240 = 0.0020 g O . 312 5 *9 5 . 6 2 5 +0. 2 5 *71. 6 2 5 +0.187 5 42 4 0. 7 5 +0.119 4 *7 2 =0. 24 8 8 lach 408 t,, = = 0. 2 4 8 8 +0.187 5 . = 0. 2182 inches t,f/R = 0.2182/240 = 0.00091 $ H 7~ / / I_
A'= * = x*1.52 1.7671 inch 2 3 SUPPLEMENT -
4 4
y M-DSC-7,PO x*1.8752 -
REVISIM U A"=
b = 2 . 7 612 .ina (new boles) 4 BY N M' E~ ' DATE 2/2e/o u CHECKED I- DATE 2MT 36A[ + 34A3 = 2.250 in2 Ab" g t' = b = 0*2.250*29.28 = 0.109 inches 2xRE, 2x *24 0 *2 8. 03 c' = " = 0.109*12.75
= 0.1091 c,h3 0.3125*40.75 SIR-92-063, Rev. O 9-3 INTEGRITY ASSOCIATESINC
I i
i 2
W = nR HYf = x *2402 *3 84 *0. 0361 = 2,508,4 81 Lbf 4
The applicable ranges of parameters specified in Table 7-1 of the GIP [17] are satisfied, except for the t,,/R
! ratio, which falls below the 0.001 to 0.01 applicable range. However, it is conservative to use the curves for t,,/R=0.001 for the present evaluation.
l
- [ Step 3] Tank Frequency From Table 7-3 of the GIP [17], for R=240" and H/R = 1.6, i F, = 7. 58 Hz F, (s , f) = 7.58*(28.03/30)o.5 = 7.33 Hz Period = 1/F, = 0.136 seconds i
i The additional stringers will likely increase the tank stiffness and thus its natural frequency. But, using the lower frequency of the existing tank will result.in a j
higher spectrum acceleration and, thus, a higher and more conservative overturning moment and shear load.
- [ Step 4] Spectra Acceleration From the SONGS 2 & 3 seismic loading spectra (see Figures 2 and 3), it is found that, at 4% damping, 6 W Ub S,, = 1.15 g (DBE) .
i SUPPf.EMENT- -
S,, = 0.75 g (OBE)
CALC NO M-Osc-28@
(Step 5] Base Shear Load REVISION l # "l$2 BYN'"'81'4M'l V 2 MTE ./20/93
) From Figure 7-3 of the GIP [17], CHECKED bS DATEN1"5 i
Q'=0.71 Q = Q' W S,, = 0. 71*2,508,4 81*1.15 = 2,04 8,175 Lbf I
[ Step 6] Overturning Moment and Shear at Different Levels From Attachment A of this report:
s SIR-92-063, Rev. 0 9-4 M
BfTEGENT ASSOCIATESINC
Sheeb l
~
SUPPUNENT CA1.C NO M -D SC- 2.fc) ; M = W H S,, h 0 .119 -0. 4 82 H 2+0. 49 8 (2) 2 EC M I WW H gy N t4-EL- AlctLY 1p.f3 CHECKED b NhV'S3 Q = W S,, (0.7048 - 0.87 )
)
where y is the vertical distance from the bottom of the tank as illustrated in Figure 1. Thus, the bending moments and shear at levels A, A', B, and C (Figure 1) are as follows: Level y y/H M Q (in) (in-Lb f) (Lbf) A 0.000 0.000 382,172,097* 2,048,175* A'# 72.000 0.1875 237,927,613 1,562,599 B 95.625 0.249 191,414,070 1,408,191 l C 167.250 0.436 65,682,921 938,929 Set to previous value for consistency. Percentage of the difference is negligible (<0.01%)
# A' is at the end of the vertical stringers.
[ Step 7] Bolt Tensile capacity 1 L = 27.5 inches (same as the Section 8.3 value) j D = 1.5 inches (existing bolts) ] D = 1.875 inches (new bolts) { From Table C.3-1 of the GIP [17], P", = 50. 4 * (1. 875/1. 375) 2 = 93. 72 kips (new bolts) P', = 5 0. 4 * (1. 5/1. 375) 2 = 59. 9 8 kips (existing bolts) 3 6 P"'" + 3 4 P""" P= = 7 6 . 3 6 8 kips
- V", = 25.25* (1. 875/1. 375) 2 = 4 6. 95 kips (new bolts)
V', = 25. 25* (1. 5/1. 375) 2 = 30.05 kips (existing bolts) V , = Average Nominal Shear Strength of the Bolts
=
" = 3 8 . 259 kips SIR-92-063, Rev. O 9-5 INTEGBITY 1
ASSOCIATESINC
1 l S,, n = 17.375*[(1.875+1.5)/2]/1.375 = 21 inches hin = 13.75*[(1.875+1.5)/2]/1.375 = 17 inches E,,n = 12.125*[(1.875+1.5)/2]/1.375 = 15 inches S= "C = 2n *243.5 = 21. 2 inches > S,,n (72 is used for the spacing of most bolts. The total number of bolts is only 70.) ) E = 22'6"-20'4"= 26" inches > E,,n [12] l l L > bin f', = 4,000 psi > 3,500 psi P,gg = P, = 7 6. 3 68 kips Vatt = V, = 3 8. 2 59 kips P, = P,g g = 76,368 Lbf Fb= P/A b= 76,368/2.25 = 33,941 psi For new expansion anchor bolts, capabilities must equal the values shown above. [ Step 8] Top Plate (see Figures 4 and 5) 5N !! summENT - ( 0. 37 5g-0. 2 2 d) P, CALC NO M OSC- Mo ny yI r)me.10/sjq) fc* \ g
, (O.375*2.5-0.22*1.5)*76,368 ByN M EL- M /W DATE 2/2c/93
, 0.9375*1.1252
= 39,100 psi I CHECKED DATh/O l o>f =y 35,680 psi (SA-36 material at 1107)
F, = Fb ( ) = 33,491* (3 5,6 80/39,100) = 30,562 psi [ Step 9] Tank Shell Stress For the ring-type chair, the equivalent dimension for "a" is 20.94 inches ( 2 *x *240 ) , SIR-92-063, Rev. 0 9-6 INTEGRITY ASSOCIATESINC
l 1 l l tb= 0.25 inches [3] 1 { S d T. (l9 0.177acy en, SUPPLEMENT ~ I g T, CALC NOP - D SC- 2,g o -
, 1 lR5VISIONYI nw- w/s/n 0.25 0.177 *20. 94 *0. 25 ( 0 3125 ) 2q fByN.M.et-p7xfty \
)
V240*0.3125 . l DATE2/coffy-l
= 0.936 j
' HECEL N ~DATEIA'/Sh - _l 1.322 Pe( u t,2 1.43aha . 4 0.031) (f g,) 3f3 , R C, l
,_76368*2.6875[ 1.32*0.936 . 0.031 0.31252 2 ) l
- 1. 43 *2 0. 9 4 *12.7 5 + (4 *2 0. 94 *12.7 5 ) 1/3 V240*0.3125 240*0.3125 2
= 36,77 0 psi (at existing bolts) l
( l l { Pe u 1.322
,, g ,0.031) I t ,2 1.43aha %
+ (4 ah 2) 1/3 R C,
,76368*3.6875( 1.32*0.936 . 0.031 0.31252 2 )
3 *2 0. 9 4 *12. 7 5 + (4
- 2 0. 9 4 2*12. 7 5 ) 1/3 V240=0.3125
- 1. 4 240*0.3125 '
= 50,452 psi (at new bolts) 1 Both o are calculated conshrvatively based on the original shell I l
thickness in lieu of the smeared shell thickness. l o > f y =29,000 psi Fr = Pb (f y/c) = 33,941* (29,000/50,64 6) = 19,509 psi [ Step 10] Vertical Stiffener Plate (see Figure 4) k, (5. 5 +1.25) /2 =4.5 j 0.75 SIR-92-063, Rev. 0 9-7 ! INTEGRITY ASSOCIATESINC ,
c.? -r. 1 'v 0 95 , 95 SUPPLEMENT -
=15.90 .
/t/1000 y 35,680 ;
CALC NO M-OSC- % Fo I h 1,000 ; I P.EVISION Y' * /U gyW-M.EL- Akilfy /20)q)l2 uCHECKED N' .DANJ/O , 95 4<
] }t/1000 y
4
- 0. 04 (h-c) = 0.04*(12.75-1.125) = 0.465 inches j > 0. 04 (h-c) j 2" *3 3*h * .7 5 =15,085 psi < 21,000 psi e
Thus, the vertical stiffener plate design is adequate. [ Step 11] Chair-to-Tank Weld 4 1' 1 e y" = p% ( a+2h ) 2+ ( ah+0.667h2)2 1 2.68M 4 ^
=7 G ,3 6 8 *% ( 20. 94 +2 *12.75 ) ,4 2 0. 94 *12.7 5 +0. 6 67 *12.7 5 2)2
= 1,733 LJffin (at existing bolCS) y* = p 1 e 9 ( a+2h)2+ ( ah+0.667h2)2 1 3.6875
=7 6,3 6 8 *$ ( 20.94 +2 *12.75 ) 2+ (20. 94 *12.7 5 +0. 667 *12.7 5 2):
= 1,807 I.,0ffin (at new bolts) 30,600b = 30,600
- 0.25 = 5,4 09 Lbf/in > W.
N N Thus, the chair-to-tank weld design is adequate.
/
SIR-92-063, Rev. 0 9-8 INTEGRITY ASSOCIATESINC
_ _. ~ . _ _ _ q (Step 12) Elephant Foot Buckling Pressure From Figure 7-7 of the GIP (17), at Sg = 1.15g and H/R = 1.6, P', = 2. 8 (calculated per Eq. (2-20) of [25]) P, = P', V f R = 2. 8 *0. 0361*24 0 = 24. 26 psi Similarly, the elephant foot buckling pressure for higher elevations of the tank can be calculated by subtracting the hydrostatic head from the above pressure: Level y y/H P, (in) (esi) A O.000 0.000 24.26 G M "T, i L / A' 72.000 0.1875 21.66 ' B 95.625 0.249 20.81 ~
' SUPPLEMENT C 167.250 0.436 18.22 CALC NO M-DSC- M o REVISION # "# /92
[ Step 13] Elephant Foot Buckling Stress BYM E-M/'V iMTE2/2a/97 S1 = R , 240
=1.26 EN N' N b 4 0 0 t,, 400*0.4764 l
.i 0 . 6 E, P,R 1 g", 2 y R/ C,, _ c yt s.) 2] [1 1.12 +S**5 2
) [ 8 +c S +1/36,000 i
,0.6*28.03*10 8 24.26*240 1 240/0.4764 g_(29000*0.4764)2) g_ 1.12 +1. 261.5 ) [ 1.26+1 )
= 15,191 psi i
i 4 The adjusted shell thickness of 0.4764 inches is used in the above calculations. Similarly, the elephant-foot buckling stresses at higher elevations are as follows: l a l SIR-92-063, Rev. 0 9-9 INTEGMTY ASSOCIATESINC
5 4 Level y s t, S, o. p J (in) fin) (nsi) A O.000 0.4764 1.26 15,191(a) f 4' 72.000 0.3125 1.92 9,944 (b) B 95.625 0.2500 2.40 j 6,885(b) C 167.250 0.1875 3.20 3,543(b) } ! (a) smeared thickness was used (b) ! actual shell thickness were used , i [ Step 14) Diamond-Shape Buckling Pressure { From Figure 7-9 of the GIP (17), corresponding to H/R=1.6 and S.,=1.15, P'd = 2.063 4 Pd"Md Yr R = 2. 063 *0. 0361*240 = 17. 87 psi j Similarly, the diamond-shape buckling pressure at higher i elevations are as follows: i
- Level y y/H Pd i
fini (esi) i < A 0.000 0.000 i 17.87 A' 72.000 0.1875 i 15.27 B 95.625 0.249 14.42 1 C 167.250 0.436 11.83 i I (Step 15] Diamond-Shape Buckling Stress ! The GIP procedure along with the equivalent thick t, was used fora the evaluation of fluid level A, while Code Case N-284 was j used for evaluating higher elevations.
., g , g
$= = 1. 4 0 m-g gg di- O S C L80 Y = 1-0.73 (1-e-4) = 0.449 REWWOff /
Prom Figure 7-11 of the GIP [17], SYdG M EL-4kVOgigs/24/b AY = 0.12 CIECKED Nd' 04FE"/"/C3 o,, = (0.6y + Ay) s R/ = 21,680 psi (Level A) SIR-92-063, Rev. 0 9-10
.. . _ . - ~.- - . _ _ - . . . .. .-
This number is less than the 35,110 psi solution obtained according to code Case N-284 (See Attachment B) . From Attachment B, o g is 13,548 psi at Level B and 12,328 at Level C. 1 i i (Step 16) Allowable Buckling Stress e, = 0.72 [ Min (cy, og)] = 0.72*15,191 = 10,938 psi I similarly, the allowable buckling stresses at higher elevations are as follows: Level y y/H o, (ini (esi) A 0.000 0.000 10,938 A' 72.000 0.1875 7,160 ' B 95.625 0.249 4,957 C 167.250 0.436 2,551 S ft T. 12, 3 (Step 17) Buckling Bending Moment capacity g g M - D Sc- 2. r o The weak link is in ductile failure. m 8' / *4 IWf7 10,938 12.75 (.F,S) (b) h3 = ( 19,509 ) ( _40.75 = 0).17 c
~
CH N 7=~/' ' D N/*df3 From Figure 7-12 of the GIP [17), M' , = 0.13 , Therefore, Mw = M', (2F,) (R2 t,,) (hgh,) 2
= 0.13 *2 *19,509*24 0 *0. 4 764 * (4 0. 75/12. 75)
= 444,856,583 in-Lbf SIR-92-063, Rev. 0 9-11 BfTEGBITT ASSOCIATESINC
. __ ~ .. . l capacities at higher elevations are simply Ecu> " O *nc *R *2 C and are tabulated as follows Level y y/H Mw (in) (in-Lbf) A 0.000 0.000 444,856,583 A' 72.000 0.1675 404,888,461 q7jp B 95.625 0.249 224,249,397 C 167.250 0 436 86,553,391 ' - CALC NO M-3SC- 2 7o [ Step 18] Check Buckling Moment . RIMSIONYI * "ISI *2 y,g, . M# 'P > 1.17 ' CHECKED DATE NS M where M is the overturing moment calculated in [ Step 6] of this section. Therefore, the modified tank will not buckle in either elephant-foot mode or diamond-shape mode. [ Step 19] Shear Load Capacity It is assumed that the anchor bolts also transfer shear: Q, = 0.55*(1-0.21*Sg) *W + 70*V,gg/2
= 0.55*(1-0.21*1.15)*2,508,481 + 35*38,259
= 2,385,541 lbf The number 35 (=70/2) is used in the above equation because the shear is distributed sinusoidally around the circumference of the tank and the total shear capacity of the bolts is the total number of bolts times bolt capacity V,gt divided by two. Vatt is calculated in [ Step 7] of this section.
SIR-92-063, Rev. 0 9-12 INTEGRITY ASSOCIATESINC
l l I l [ Step 20] Check Shear Load l
> 1.16 i o \
where Q is the shear force calculated in (Step 6] of this l section. Therefore, the modified tank will not fail due to shear. Since part of the shear load is now taken by the bolts, it is necessary to check the shear-tension interaction limits per Figure C.3-2 of the GIP [17) . Both the tensile and shear loads distribute sinusoidally around the circumference of the tank. It is required by the GIP [17] that
# Y
( P,33 ) s 1. 0 ,1f V,33 s 0.3 i ( P,33 ) + 1. 4 3 ( V,33 ) $ 1. 4 3 ,if 1 > V,33
> 0. 3 l i
where P =Po sine , V = Vm cose and 8 is the azimuth angle around the circumference of the tank. For the SONGS-2&3 PPMSTs, p" , 2fM , 2*382,172,097 = 45,497 LBf NR 70*240 0-0.55*(1-0.21S Vm = g) W = 28,620 lbf where the overturing moment M and the shear force Q are calculated in (Step 6] of this section. Therefore, as l illustrated in Figure 14, the bolts satisfy the GIP l , shear-tension interaction limits (see C.3.7 of the GIP) . 5tt T 1 % b' 1 l SUPPLEMENT - CALC NO "~ O" - REV!SIO[ NM BY
- N ~ M N DATE*/*#N3 CHECKED I'b DATE ,O SIR-92-063, Rev. 0 9-13 INTEGRITY ASSOCIATESINC
1 l l S H T, IMo j (Step 21] Slosh Height ' SUPPLEMENT ~ i N NO 4 - 08 C- *80 1 1.84G 1.84N REVISION
' '#N7 F, = g R R gyAi* E- rid DATE b3 !
1 1.84*386.4 2xh 240 tanh(1 84*384) CHECKED N DATE "b ! 240 l
= 0.2732 Hz 1 i
l Sloshing Period = 1/0.2732 = 3.66 seconds l S , = 1. 5 g at 0.5% damping per Figure 2 h, = 0. 8 3 7 R S,, = 0. 8 3 7 *2 4 0*1. 5 = 3 01. 3 2 inches j [ Step 22] Check Sloshing Height h, > h, 1 Therefore, during a DBE event, some of the water in the modified tank might slosh up and exert an additional up-lift pressure on the roof. However, as shown in Section l 10.0 of this report, the roof design as well as the tank-to-roof welds both meet ASME requirements to withstand the additional internal pressure. The shallower than required free board is likely to restrain the sloshing water from its first mode sloshing and reduce the overall overturning moment. The total uplift force due to the sloshing water is 560,144 Lbf, or 8,002 Lbf per bolt, according to the calculation described Section 10.3. As shown in Figure 14, bolts with the additional 8,002 Lbf tensile load will still satisfy the GIP shear-tension interaction limits calculated in Step 20. i SIR-92-063, Rev. 0 9-14 INTEGMTY ASSOCIATESINC
s heet [
~
l g3 SUPPLEMENT ;
/
CALC NO M - D EC -- L80 , 10.0 Qualification to ASME Code Design Rules aEvmou #I '"" e/0Nn] 7/#'/#3 i BY AIA4'!- M fL- AY'EDATE CHECKED 7 _ _DATEY1TD In addition to the seismic requirements diset....J 1.. A % im. ;.0, the PPMSTs must also meet all ASME Code requirements. 10.1 Tank Shell Design Per ND-3324.3 (c) , which is referred to by ND-3842, the minimum tank shell thickness should be determined by: PR ! Q* = SE - 0 . 6 P where P is the Design Pressure, R (240 inches) is the inside radius of the tank, S (18,000 psi) is the maximum allowable stress of the tank material at the Design Temperature per code Table I-7.2 , and E (0.85) is the joint efficiency. The joint efficiency is at 0.85 i because the original API standards, API-620 and API-650, required only spot examination of the tank welds. Thus, according to ND-3352 of the ASME Code, the joint efficiency should be 0.85. Since P=0.0361*h psi, where h is the distance in inches from fluid surface as illustrated in Figure 1 minus 12" (ND-3841(a)), the minimum by: calculated tank wall thickness at different levels of the tank can be
, 0.0361*h*240 18,000 *0. 85
. 0. 6 *0. 03 61 *h Thus, at levels A, B', and C (see Figure 1),the following minimum thicknesses are required:
Level h (inch) t,,,(inch) tw(inch) C 216.75 0.123 0.1875 B 288.375 0.1633 0.25 A 384.0 0.218 0.3125 SIR-92-063, Rev. 0 10-1 D8TEGRITY ASSOCNEEINC
Thhefore, existing tank shell thicknesses of the PPMST at SONGS, Units 2 & 3 satisfy the ASME Code minimum wall thickness requirements. 10.2 Bottom Design i l The existing bottom plate thickness of 0.25 inches satisfies the ND-3831 requirement. Since the PPMSTs were built to the standards of API-650, the existing foundation satisfies all the code requirements in ND-3831. The existing tank bottom design also satisfies the requirements on method of construction (ND-3832) but does not satisfy the shell-to-bottom attachment (ND-3833) requirements, as a full penetration weld is required. 10.3 Roof Design Per ASME Section III, ND-3856.2, (i) the radius of curvature of the roof must be within the code specified range, (ii) the roof plate thickness must be within the range specified by the Code, and (iii) the cross-sectional area of the top angle, in square inches must be greater than the Code minimum value calculated by the Code. R = Radius of Curvature of Roof = 48 feet MTIN t = Plate Thickness = 0.25 inches SUPPLEMENT - D = Tank Diameter = 40 Ft CALC NO M - o sc _ >f 0 1.2D 2 R > 0.8D REVISION - " '0 M/U 0.5 inches > t > (R/200) = (48/200) =0. 24 BY " EL- Ak !/ V DATEU2*/93
, DR , 40*48 = 1. 2 8 inch 2 1500 1500 DENh A = cross-sectional area of the top angle
= 2.52- (2.5-5/16) 2 = 1.46 inches 2 [2]
Therefore, all the, requirements specified in ND-3856, "Self-SIR-9 2 -0 63, Rev. 0 10-2 ON DITEGRITT ASSOCIATESINC
~
Supported Dome and Umbrella Roofs", are satisfied. l i In addition, the roof has to withstand the additional internal l pressure caused by the water sloshing (see (step 22) of Section 9.2). The vertical force exerted by the sloshing water would be l 1 the sloshing mass (m, in Attachment A) times the maximum vertical I acceleration (0.77g for DBE per (14] and 0.5g for OBE per (16]). The horizontal force due to the sloshing water would be water density times the volume under the roof and above the vertical i shall times the maximum horizontal acceleration (1.15g for DBE and 0.75g for OBE). FVm = 0.29*2,508,481*0.77 = 560,144 Lbf FV , = 0.29*2,508,481*0.50 = 363,730 Lbf From Figure 1, l the volume between the roof and the vertical shell can be calculated as ( l 2 24.6243' i Volume = nR} Sin'$d$
= x *576 3 * (-0.7 5 Cos$+ 0. 25 Cos3$) l$4.s243' ,
= 4,814,6 37 inches 3 SUPPuiMENT k
calc no P - O sc-zgo F% = 0. 03 61*4,814,637*1.15 = 199,880 Lbf REVISION ##
- 10h/93 j FHg = 0.0361*4,814,637*0.75 = 130,356 Lbf I 7 BY A "~ & O 8 Y D M E ]y277,/p T~ 6 '
{ The total force exerted on the roof is simply CHECKED _DME f) d.. SA;; ef th: horizontal and the vertical forces. Thus, l 1 F = 594,738 Lbf . F = 386,383 Lbf i Stresses at the tank-to-roof weld is the above forces divided by 2xRem , w h e r e t ,37 ,,,= 0 . 1 3 2 6 inches (4]. That is, i
/
SIR-92-063, Rev. 0 10-3 MTEGMTY ASSOCIATESINC
l 1 o$fg = '
= 2,974 psi 2*x*240*0.1326 o$fd = 2*x*240*0.1326 = 1,9 3 2 c.cl Both stresses are much smaller than the allowable values (35,680 psi for DBE and 19,624 for OBE) per ND-3821.5 of the ASME Code.
I The equivalent pressure due to the sloshing water is the total l force divided by xR 2 where R is tank radius (3.29 psi for DBE and I-2.14 psi for OBE) , and the additional membrane stress caused by the pressure is simply 2xRC , where t is roof thickness (=0.25 inches) . Thus, the additional membrane stresses due to the sloshing water ' are -7,580 psi for DBE and 4,931 psi for OBE, which are much smaller I than the code allowable values of 35,680 psi for DBE and 19,624 psi for OBE per ND-3821.5. l Therefore, the existing roof design including the tank-to-roof l junction weld is strong enough to withstand the additional pressure l caused by the sloshing water. I 1 10.4 Reinforcement of Shell Nozzles i . 1 As shown in Figure 6, the reinforcement requirements for the nozzles, including the manhole, per ASME Code ND-3332.2 are 1 d = Nozzle Inside Diameter t, = Minimum Tank Wall Thickness per Section 10.1 ^ Pr l t'" = SE+0 . 4 P 6 tt T. ( *> O I
~~
, tn = nominal nozzle wall thickness SUPPLEMEE l q A ry = ' d t, F CALC NO M-osc- @ F = 1.O REVISION I#
- I##D A = Area Available = A 3 +g BY P "-"
- M DATE D
; A 3 = d (t-t,) CHECKED N /- DATE YIf">
SIR-92-063, Rev. 0 10-4 INTEGRITY ASSOCIATESINC
Cb<cb /3) SUPPLEMENT - 1 gg_M-Osc '2-g o I y;y,g ' I *L Iols/'t3 A2 = d *tn * ( tn -t,n) !U A>A fSY N " NY# DATE req ICHECKED l b- DATE D where all the quantities in the abvv. volvulaLiva are I according to those provided in ND-3335.1 of the ASME Code. The above reinforcement requirements for the PPMSTs were I checked and is summarized in Table 10-1. As shown in Table 10-1, all nozzles except for the 24-inch manhole satisfy the ASME Code reinforcement requirements. It is recommended that, as illustrated in the last row of Table 10-1 and the figure below Table 10-1, a 1/4 inch thick annular pad plate be welded to the tank shell around the man hole. The recommended width of the annular pad plate is 6 inches or wider. 10.5 Code Stress Limits of Tank Shells Per ND-3821.5, stresses in the PPMSTs under various loading l conditions must satisfy different stress limits. Per Eq (2.13) of l [25], the maximum equivalent pressure' at different elevations can be calculated as follows: Desian Condition l Level y P choop* Callow ** (in) (usii (esi) (nsi) A 0.000 13.86 10,644 17,840 l A' 72.000 11.26 8,648 17,840 B 95.625 10.41 9,994 17,840 C 167.250 7.82 10,010 17,840 0 3,,, = , where R=240 inches is tank radius, and t is tank shell thickness given by [3]. S=17,840 psi is the allowable general membrane stress for Design Condition loading at the design temperature of SIR-92-063, Rev. 0 10-5 INTEGRITY ASSOCIATESINC
1 5heeb /3b : SUPPUNENT l cal.C NO M-Dsc 2 8 O l l REVISION '#l'IU l l 180*F per (19) . gyN M.rt-4 kit.y DATE */**/fd CHECKED b~ DATE
!M ggg i Level y P, og,p
- o,22,,* *
(in) (e s i') (esi) (esi) A 0.000 20.84 16,005 19,624 A' 72.000 18.24 14,008 19,624 B 95.625 17.39 16,694 19,624 l C 167.250 14.80 18,944 19,624 l
- P,R o3 ,= ,
where R and t are radius and thickness l of the vessel, respectively.
** 1.1S=19,624 psi is the allowable membrane plus bending stress for Service Level B loading at the maximum operating temperature of 120*F.
EHE Level y P, 0 3,p
- o,22,,* *
(in) (usi) (esii (esi) A 0.000 24.57 18,870 35,680 A' 72.000 21.97 16,873 35,680 B 95.625 21.12 20,361 35,680 C 167.250 18.53 23,718 35,680 P,R
- o3 ,,, = , where R and t are radius and thickness of the vessel, respectively.
** 2S=35,680 psi is the allowable membrane plus bending stress for Service Level D loading at the maximum operating temperature of 120 F.
SIR-92-063, Rev. 0 10-6 INTEGUTY ASSOCIATESINC
1 Therefore, the modified tank satisfies all the ASME code stress } lim'it requirements. t 1 1 10.6 Strength of Bolts e The bolts have been shown to be adequate to withstand the DBE l loading in Step 7 of the GIP (17] evaluation in Section 9.2. For OBE loading, i M, = 0. 3 4 5 W H S,, = 0. 3 45 *2,508,481*3 84 *0. 75 ) = 249,242,672 in-Lbf f i V, = 0. 704 8 W S,, = 0. 704 8 *2,508,4 81* 0. 75 = 1,325,983 Lbf i i j The above two equations are identical to those for the overturing { moment M and shear force Q at fluid level y=0 in Attacheent A of this
- report. Thus, the maximum bolt tensile stress o,, , due to the overturning bending moment is l
l g*'", F, 2N oar , 2 *249,242,672 = 13'187 psi A s NRAs 70*240*2.25 In the above equation, the maximum bolt force F, is calculated based on Eq. (16) in page 23-7 of (27). The above bolt tensile stress is less than the allowable value of 20,000 psi specified by the AISC (26). The shear force is assumed to be taken by the frction force between the tank bottom and the concrete as well as the bolts. The maximum shear stress in the bolts is
~
SLFPLBWlf m sg M-Osc-2_60 5/tT, /33
) n n polc/gy gyN-N.EL- A k#t.Y hang7/27/9;
, CHECK E NI- W4fE NN) .
SIR-92-063, Rev. O 10-7 DrTEGRrFY ASSOCIATESINC
I l l ~
\
l
, V ,a- O . 55 (1-0. 21Sg) W N A3 /2
, 1,325,983-0.55*(1-0.21*0.75)*2,508,481 70*2.25/2
= 2,07 8 psi The second term in the numerator of the above equation is i.he friction force between the tank bottom and the concrete por the GIP (17] and the factor od 1/2 in the denominator is to account for the ;
sinusoidal shear stress distribution. The bolt shear stress is I less than the allowable value of 10,000 psi specified by the AISC l (26). I To check the tension / shear interaction limits, the following linear 1 curve is checked
- l SUPPLEMElff l CALCNO M -D 5 c. 2. f 6 5HT(3h Ce
, s g3 mf ' * @ng 0 all %all gyN-M- GL-hkiLf g 2f2 9 93/
CHECKED 'd' 3 DATE Since ce=o,m e sine and T. = T m Cose, where 6 is the azimuth angle around the circumference of the tank, the above linear shear-tension interaction limits are satisfied. 10.7 Code Stress Limits of Ring-Type Anchor chair As shown in Step 8 and Step 10 in Section 9.2, the maximum stress in the top plate and stiffener plates of the ring-type anchor chair are, respectively, 39,100 psi and 15,085 psi under the DBE loading, which are less than the allowable value of 42,816 psi (= 2.4S = 2.4
- 17,840 at 120 F per [19]) for the Service Level D loading.
Similarly, under OBE, the pulling force at the anchor bolts due to the overturning moment is simply 23,671 Lbf ( c e ,,,xA3=c e ,,,x*A3 =13,187 psi *2.25 inches2) . With the same equation used in Step 8 of Section SIR-92-063, Rev. 0 10-8 DITEGRITY ASSOCIATESINC
l
<ttT.135' SUPPLEMENT '
9.2, CALC NO M ~D'C- S8 o l l REVtSlON Wl " ~ l*lSI13 g , (0. 37 5 g-0. 22 d) P BYN M-EL-AktLY g2)1o)q fC* CHECKED I g b/n
, (0.375*2.5-0.22*1.5)*29,671 0.9375*1.052
= 17 a 439 psi This stress is less than the allowable value of 29,436 psi (= 1.65S
= 1.65*17,840 at the maximum operating temperature of 120 F) per ASME Code ND-3821.5.
l I } SIR-92-063, Rev. 0 10-9 M INTEGBITY ASSOCUU'ESINC
Table 10-1 Reinforcement Requirement of Tank Nozzles Table 10-1 Reinforcement Requirements of Tank Penetrations Nonle 10 d tn y P tr trn A1 A2 A Areq A>Areq (inches) Onches) (inches) (psi) (inches) (inches) in*2 in*2 in*2 in *2 3 3-A 24.000 0.438 27.500 12.87 0.202 0.0105 2.65 0.93 3.59 4.85 No 3-C 3.826 0.337 9.000 13.54 0.212 0.0020 0.38 0.56 0.95 0.81 Yes 4-C 2.323 0.276 5.375 13.67 0.215 0.0013 0.23 0.38 0.61 C.50 Yes 4-E 1.939 0.218 6.000 13.65 0.214 0.0011 0.19 0.24 0.43 0.42 Yes 4-F 1.939 0.218 5.750 13.65 0.214 0.0011 0.19 0.24 0.43 0.42 Yes 4-G 3.826 0.337 5.87C 13.65 0.214 0.0020 0.38 0.56 0.94 0.82 Yes 3-A
- 24.000 0.438 27.500 12.87 0.202 0.0105 2.65 3.93 6.59 4.85 Yes
- See the recomrnended modification below.
S M T.13 G SUPPLEMENT ~ l CALC NO M -E - Mo l REVLSIOfI lo/5/fy l l- c. 3 s 2 5" N
.SY 'M'"L'Aki1 Y m *-l2 C/93
-*' & Yn CHECKED- I'd' -DATE b/ O:
4 0 938" i : o [ / N/
. . I B
'\ /
v \ /
\ __,/
% /
\ %_
/
SIR-92-063, Rev. 0 10-10 INTEGMTY ASSOCIATEINC
i 6ttT.137 summam - ceno M- Osc-2gp 11.0 Reconciliation with 1989 Edition ASME Code N# #/5/95 y N.M. el.- A kiL Y gjnjy 11.1 Material CHECIWD fd- DATE Y"k'2 This section discusses ASME Code ND-2000 versus API-650, Section 2.- These two codes are very similar in the material requirements except that the ASME ND-2000 calls for CMTR's. Since the PPMSTs were built with ASME materials (except for the anchor bolt chairs, which will be replaced with new anchor bolt chairs of an ASME material) and all the CMTR's are still ' recoverable, the ND-2000 requirements on materials can be considered satisfied. 11.2 Design This section discusses the differences between ASME ND-3000 and API-650, Section
- 3. As discussed in Chapter 2 of this report, except for tank shell buckling and water sloshing height, the existing PPMS tank design meets all ND-3000 requirements. A tank design modification is described in Chapter 2 of this report, and it is shown in Chapter 4 that the modified PPMS tank meets the shell buckling requirement. It is also shown in Chapter 10 of this report that although water might slosh against the roof, the existing roof design is adequate to withstand the additional internal pressure caused by sloshing.
11.3 Fabrication and Installe. tion This section discusses the differences between ASME ND-4000 and API-650, Sections 4 and 5. The two codes are quite compatible on fabrication and installation. One major difference is, the roundness requirements specified in ND-4220. According to a roundness measurement recently performed by SCE, all PPMSTs at un
' SONGS .2&3. are in' full compliance with W-4220.
NME 7/t. 3p 3 SIR-92-063, Rev. 0 11-1 INTEGRITY ASSOCIATESINC
i s bee (~ /37 8UPPLEMO ! gg M-Osc-ado gy JY l ' 10l$(43 l
' g. u. e/-A ki ly ggg7/27/h 11.4 Examination i cHecs3D T*f'
- DME i .
\
) ;
( i and API-650 Standard.This section discusses radiography , Subsection the differenc! NB-5000 I which is API-650 consistent requires that the tanks be inspected by spot with ASME ND-5000 for welds with joint i i efficiencyTherefore Appendix A. o,f 0.85, except for some differences as explaine! the PPMS tanks should be examined per NO-5000. { j This examination given has in Appendix E. been pe,rformed for T-056; results are docume i 11.5 Testing i The testing requirements specified in ASME, ND-6000 and API-650, Section 5.0 are very similar. !. Therefore, the requirements on [, testing tank. the tanks can be viewed to be satisfied for the existing j However, after the recommended reinforcement of the tanks, i the testing procedures provided by,ASME ND-6000 must be followed i before the tank is certified and used again. i I 4 11.6 overpressure Protection i ! j ASME Code ND-7000 discusses rules and requirements for overpressure r j protection, while the API-650 Code does not have any requirements in this area. Since the PPMST's j are designed and operated at atmospheric pressure, i ASME Code. no overpressure protection is required per The existing 1" vent (3-D in (3]) and 6" vent (4-H in (3) are adequate for maintaining the tanks at atmospheric pressure. } Therefore, the PPMST's are in full compliance with ASME Code in ' l this area. { l I i l {
'11.7 Weldir4 i
4 ! i According to.Section 7.0 of the API ~-650 Code, all welding must be done according to ASME Code Section IX. Therefore, the PPMST's are > l in full compliance with the ASME Code requirements in this area It 'is worth noting that, although the welding procedure and . i implementation satisfy the ASME Code requirements, the design of the welds may not, as pointed out in Section 10.2. SIR-92-063, Rev. 0 11-2 NC
11.8 Stamping 1 l Rules on stamping per ASME Code, ND-8000 and API-650, Section 8 are 1 obviously not the same. It is recommended that SCE requalify its tanks as ASME Section III, Class 3 tanks by implementing the { 1 procedures specified in Appendix B of NBIC (21]. 1 l i 2 1 S M T. I3@ ;
/ ! SUPPLEMENT ~~ l , CALC NO M DK- M o l i gm WI
- 10) Slo *? ;
gy N.M- EL- AWi! Y y /2c))3 2 CHECKED F6. DATE Y '3/b, 1 I l l a l l 1 l 1 l l l , 1 l d i 4 l SIR-92-063, Rev. O 11-3 I INTEGRITY ASSOCIATESINC
i
. l 1
S H T. 190 i SUPPLEMENT CALCNO M .OSC- vpfo REVISION YI l#]3lf 3 BY N' M 'EL~4k I' E DATE#/"/T3 CHECKED NI- DATE 7t?O 1 12.0 Figures l l l l l l i l l l SIR-92-063, Rev. 0 12-1 INTEGRFFY ASSOCIATESINC
C.9 de :
/ O.2 6" y
Freeboard. hg = M.l5 " L3
'I' /\ Roof 62, t r65,
^
1 %
^ v / #
l R = 41' e + e
. y g '_' .
I : 3 - 216,15 " 9 $p i I Tank Shell ---* a 2 W ' I Thickness, t
, Tank Radius "
% a C Lud Re a 190" 11.615
8 level erson " '25"
# o.25" Tank t = g
s, s ,37 Anchor Chair or Ring * ,, Base Plate Concrete Fgundation fsc yj ., 4..v..,.. ,*, .- , t' *
**f * *. ;, =. *. -
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'Nh*#
1 CALC NO M-DSC- 08O gg .i, g 7,ig(,g o_ ggxa x(1-CosB,h 3 4 16 " . f ) REVISION fI nw-wIsfq3 i gy rJ. M. 5L- Akil. Y gggg2 80)ff i
- CHECKED '
DATE N i Figure 1. Songs 2&3 Primary Make-up Tank k 8 SIR-92-063, Rev. 0 12-2 s wrlecarrY i ASSOCUMENC 1
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= ,
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2 s . , 4 ma - l l. i Figure 2(b). Design Basis Earthquake Vertical Acceleration
- Response Spectra at Node 1, Elevation 9'0" of 4
Auxiliary Building [14] 4 4 4 SIR-92-063, Rev. O 12-4
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I > N ;4 W
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, Response Spectra at Node 1, Elevation 9'0" of Auxiliary Building (15]
SIR-92-063, Rev. 0 12-5 a l- 1-ASSOCIATESINC
i 4 limfQUDs:' = = w W 50 3 to *
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SIR-92-063, Rev. 0 12-6 il II: -
, >e1 -
N
l s M. I ' ?' L.
~
; SUPPLEMENT CALCNO M MC- WO REVISION
#' l#NU BY d 'M* E'~A ##'Y M*/*#/93 CHECKED DATE I 79
-4 Anchor Bolt Nut f
a v: ,q
> ~
K-e; e , 4 .....- n a Top Plate -
,_ Fu o j h
.- . 2 u
- stiffener J j *ank Tall h r k
=
Tank Base 4 ..:. .L., - U i bM tb (a) Typical Plan and Outside Views (b) Side View , i l Figure 4. Typical Anchor Bolt Chair I 1 SIR-92-063, Rev. 0 12-7 l STRUCTURAL
; INTEGRITY d ASSOCIATESINC
4 It T. I '+2 SUPPLEMENT - CALC NO M - O s C- 2 80 l REvlsioNK' " I l'M3 gy W M- 2L- Ak!LY g2/20/0; CHECKED IS - DATEU/T3 1 [ II A set fC- WM. I b Iatercittta,it usetJiny #, y it" st;tek, g* syne:ng gf si j" b" V l 240' 1( \ V - A f
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T yi - , i i- f=V { f $"as* 5 I 4 I , 4-' 70 bolt &:rs l l TV ' ' gaf _ ^ r i Figure 5. Reinforcement Design of PPMST SIR-92-063, Rev. 0 12-8 INTEGRFrY ASSOCIATESINC
1 1
- 4 H T. I f f
~
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- d/2 d/2 (ND-3334.1(b)]
~~
1 I i l l l l Figure 6. Reinforcement Requirement of Tank Opening , 1 1 SIR-92-063, Rev. 0 12-9 INTEGRFIT ASSOCIATEEINC i
)
l Stt7.I'f4 4 SUPPLEMENT - ; CALC NO M-DSC- 7 fo ,
?neysgoNY " lo}s/q_7 fBYN.M. EL-AKIL y /ze/G 2
Y I '6 DATEYo/53 l CHECKED l l R 4" _--------------______________H,/H _ I
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=
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l i SUPPLEMENT -
!- I-CALC NO M-0%~*80 ]@I O REVIS!ONO gy N.M.GL-AMILY O/TJ f p .. . . . - . . . . . . . . . . . _ . . . . . .gg3.yW/W.
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1 l 4 + T. IJ~l
~~
SUPPLEMENT d CALC NO M'OSC 'Z 80 gmy y/ M 10/s/q3 } gy ^! M-GL~ AKILY gyq 2/20/93 CHECKED- IS - DATE% YT3
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- 1. /
l '
/ ~3X /
/
/ Ws
. / /
n . . 5 / e
/ , /
.? / / i- / X9 j
/ ~
/
"f' f s i
a
/M mg vwwv---/
- / /
- / /
i l /
/
H3 g l /, l n
/
/
mr I'
- Hf / -
/
i /
/ /
/ . /
.H T / /
YL y / l -
/ /
, / / i
// / //////// / n e- / / / / / / / /
G(t) i. 1 i i i i l Figure 9. Mechanical Model of a Flexible Tank [20]
- SIR-92-063, Rev. 0 12-12 DITEGRFIT j ASSOCIATEINC
_. - . . - - .- . . - - _ . - _ - . . _ - - . -.=._ _ _- . _. .- .
. SUPPLEMENT CALC NO N-DSC-W8o 5/j-7.jf L,
\nsylstoNE' " 10/ S / 1 3 1
gy W.M EL-AkiL Y ggy )20/13
! CHECKED b' .DATEYM/Y5 1
036 h>OS 0 34 3
\
h -R 0 32 1-W 030 ' ;C, Ek - 0 28 2. ba Rt Volid for d Z>30 for simply supporied edges 0.26 Z>50 for clamped edges
\\ $
0 24 w Q22 . 3 0.20 18 0 1,000 2000 3000 4400 R/t Figure 10. Buckling-stress Coefficient C, for Unpressurized Curved Panels subjected to Axial Compression (22] SIR-92-063, Rev. 0 12-13 ASSOCIATEINC
SUPPLEMENT ~ CALC NO M -OSC- MO N IO REVISION #l#/1 gyu H-wL-AlclLY' y /2of93 2 CHECKED ' DATE - Y#2
)
h j 10 i 8 1 6 ] 4 i 2 LO ! 8 I 6 l ti 4 A r
' /
2 ,
/
/
/
.GQ # , ,
6 ! 4 2 . j OU 2 4 68 2 4 68 2 4 68 2 4 68 8 OOt 0.10 ID 10' 10 k . _ . . _ . i Figure 11. Increase in Axial-compressive Buckling-stress Coefficient for Curved Panels Due to Internal Pressure [22] SIR-92-063, Rev. 0 12-14 DITEGRITY ASSOCIATESINC
l SUPPLEMENT i CALC NO M DSc_ Mo !5.4 If y / AK 10} S/ 4 3 l REvlSION BYW .M.EL--hkJLY gg3gWOl
. CHECKED DATE 1.0 I llIll l
~ ' ~
8 -. 1 N-g '7 e 3 1
$ .6 \
- I 2-5 \, ...
R g .4, -- - - Y .3 N . w_._ _
.2 --_-. .. . .. _.... . __ ... .. _
\ '
.i _ _
_. . -. N __ _ _ __ O , .l. 2 3 4 56789 2 3 4 56789 2 3 4 56789 O, O C' R /t. I l l l l Figure 12. Correlation Factors for Unstiffened Unpressurized Circular Cylinders Subjected to Axial Compression [22] SIR-92-063, Rev. 0 12-15 INTEGRETY ASSOCIATESINC
SM T- l W i .
?
' - I SUPPLEMENT '
CALC NO M-USC- , RMIOW !
$ YI gy W.M.GL-AKILf gg3yG /30/fj[
iCHECKED i DATE!9bi ' 10 4 2 >700 lO g 6 - -' 4 .. - _
<3 2 .
Olog
/
6 /- 4 s
/ _
2 -.-- 0 01 ! 2 4 68 2 4 68 2 4 60 0 01 0 00 1.0 0 I 1 1 e I Figure 13. Increase in Axial-compressive Buckling-stress Coefficient for cylinders Internal Pressure [22] d SIR-92-063, Rev. O 12-16 INTEGRITY ASSOCIATESINC
SUPPLEMENT - CALC NO ?~ OSC~ 780 b!rT.156-REVISIONYI "* 10)$/97 ] SY ^^ M Kl-4k/L7 DATEIN#/13l CHECKED E 5' DATE% 5h, 1.2 1.0 -n'- - , PPMST Bolts N ,\ - - Failure in Bolts
,\
Failure in Concrete 0.8 - s,
\ 's, with uplifting force s N 's '
"" O.6 -without uplifting force '
g
- \ 's s
\ 's 0.4 - \ 's
\ N
\ 's
. r 0.2 - \ \ s
\ ',
\ ',
\ ',
0.0 i i , i i i , 3 i i t 0.0 0.2 0.4 0.6 0.8 1.0 ' 1.2 V/Vn Figure 14. Shear-Tension Interaction Limits of Bolts in the Modified PPMSTs (17] SIR-92-063, Rev. 0 12-17 INTEGRITY ASSOCIATESINC
2- . ._ . -.. . -.- ~.s.-. .- ...-n.. ,.m.. .-a -ss.. .~ .m .. .a. -.~,..---,.n - - .. - . - _ . - - - - - - - _ _ . - - - - _ _ _ - - - t
'u '
l. i Attachment A i
- j i-overturning Moments and Shears at Various Liquid Levels i
The overturning moment and shear calculated per the GIP [17] are the maximum values at the bottom of the tank. The analysis method developed by Haroun (20] was used to compute overturning moments and shears at higher elevations of the tank. H/R = 384/240 = 1.6
- h=t g = 0.2077 inches (see step 2 of section 8.3) h/R = 0.2077/240 = 0.000865 i
SFT 150 i From the referenced paper,
~
1 SUPPLEMENT y H-DSC-200 g: , 1.84g tanh 1.84H # / DW /7/5/ f.J _ I
- 1. 4*386.4 1.84*384 BY "' M j
=
240 2.946 (rad /sec) 2 240 g ML DMh i t i } T, = 2x = 3.66 seconds l e, = 1.716 rad /sec, ) *s 1 3 j In addition, the following quantities can be obtained from Figures j 7 and 8, which are extracted from Haroun's paper (20): i o fR = 0.09 i i f 3 SIR-92-063, Rev. O A-1 M j DITEGRITY ASSOCIATPS INC
Nf
- = 0. 6 8 m
,-- 4WT. l[S I ~
SUPPLEMENT . I = o ,71 CALC NO-M-DSC- tJo ] REVISIOWI A# l*]$l93 ' lBYW M-EL-Akfl_f 1/20/q m
-m! = 0. 29 jCHECKED I 6- d/23/si Hg
- = 0.47 H ?
H
- HI = 0 . 414 H
-H! = 0.69
- Thus, g', 0.09 E H ) p,
" 0.09 28.03*10'*386.4 384 h 0.283
= 45.77 rad /sec
)
l Tf= 2xU = 0.137 seconds t SIR-92-063, Rev. O A-2 i M1 n m aarry ; ASSOCIATESINC l
, 4 PT. / fT l SUPPLEMENT ~
CALC NO M-DSC- tfo l
' REVISION '0/8/M l From the DBE spectrum shown in Figure 2 (a): 'gy N-M- EL-Ak/4 / g@o/p3 :
S,, = 1.15 g CHECKED T-C DN/647 S,, = 0 . 7 5 g = 0 . 6 5 S,, (set to achieve the GIP [17] moment) dm = 1 g = 0.87 S,, From the model shown in Figure 9, it can be shown that, at a distance y from the tank bottom, the overturning moment and shear are: W N = / [m,(H,-y) S,,) 2 + [mf (H f -y) S,f] 2 +([m,(H,-y)f -mf (H -y) ] dj
= H m S,f 0.119 - 0.482 , + 0.498 ( )2 The above equation is the same as the first equation in page 205 of
[20] by Haroun except that the moment arms H,, H, and H, are f ; ajusted to reflect higher fluid levels. I Similarly, V = / (m,S,,) 2 + (mfS,f) 2 + [ (m,-m ) e ]2 -m dm f m
= (0.7 04 8-0. 87 ) m S,f i
l This equation is simply the last equation in page 203 of [20] less the product of the fluid mass between the bottom and the level and ; the acceration. SIR-92-063, Rev. O A-3 INTEGRITY ASSOCIATESINC .
Attachment 8 i ! 4 Diamond-Shape Buckling Stress Limits 1 1 ! l i ' B.1 Perform Stress Analysis (Step 1 of CC N-284) )l 0 4 = axial stress j , = y, + y s trT. / G O 2xRC KR 3 t - f.: mm H - DSC - tM mM/ M IO)G/93 ce = Hoop Stress = " BY "'"'E'* * 'A DME? h t
- c j m- ec . ,,,wd i
l sy = Shear Stress = i 1 j Where Pd is the pressure calculated in Step 14 of Section
- 9.2.
f B.2 Determine Stress Components og (Step 2 of CC N-284) l 1 q i (a) Level A (see Figure 1 for definition)
, , 39664 , 382,172,097
- 2n*240*0.3125 = 6,843 psi (compression) f x*2402
- 0.3125 oo 0 3125 - = 13,724 Psi (tension) i I
'M " 2x*240*0 3125 * ,
Psi (shear) where 39,'664 Lbe is the weight of the tank W: calculated in Section i 8.1 of this report, 382,172,097 in-Lbf is the overturing moment M j calculated in (Step 6) of Section 9.2 of this report, 2,048,175 is the shear force Q calculated in (Step 6) of Section 9.2 of this l SIR-92-063, Rev. O B-1 i DETEGMTY ' ASSOCWESINC !
report, and 17.87 psi is the diamond shape buckling pressure calculated in (Step 13] of Section 9.2 of this report. i (b) Level B (see Figure 1 for definition) 39664 191,639,921
,+.,
2n*240*0.25
= 4,342 psi (compression)
+ n *2402 *0.25 o, = 14.42*240 = 13,843 psi (tension) og= 2 *20*025" ' * * "" where definitions of the numbers in the above equations, namely i 39,664, 191,639,921, 1,408,191, and 14.42, are similar to those for Level A. (c) Level C (see Figure 1 for definition) 39664 , 65,682,921
,* , = 2,077 psi (compression) 2 x *24 0
- 0.187 5 n *2402 *0.187 5 o, = U *4
= 15,142 psi (tension)
O.1875 04e " 2x *240 *0 187 5 Psi @ ead l where definitions of the numbers in the above equations, namely 39,664, 65,682,921, 940,067, and 11.83, are similar to those for Level A. 4ttT,/d/
~
SLP PL B W if B.3 Factor of Safety (Step 3 of CC N-284) CALClO M- n %-M O FS = 1.34 for DBE g ; ome.go/gj4 3 FS = 2.0 for OBE M v yggn, g. a.no m /2t/c 7 g f- d - summ /W/S3 B.4 Capacity Reduction Factors (Step 4 of CC N-284) (a) Level A 14 = 72 inches SIR-92-063, Rev. O B-2 DITEGRITY ASSOCIATESINC
le = 2n36*240 ,41,gg jgg3,, .. g p77, f g, p
~
i'SUFFLEMENT - N, = 7 2 /V24 0 0 . 3125 = 8. 31 hW NO M -DSC-. MC .
]f Ne = 41. 89 /V24 0
- 0 . 3125 = 4 . 84 REVISIO# 10/5/f3 M = Min ( N,, N e) = 4 . 8 4 8Y MOW DATE*/U I.
i O.826 a,3 = = 0. M1 ! g, , , aet = 0 . 8 1,e c j
= 41 89 *0.3125 = 6.54 inch 2 240 i
a,eg = 1. 323-0. 218Logie CR = 1. 323 -0 . 218 Log 1, 0 3125
= 0.694 Assume that the cross sectional area of the stringer is greater than or equal to 5 inch 2, i
= 5 I = 1,e t = 0.765 6.54 a,a = 0.7 2 asa = 0 . 8 4
a,e, = 1. 3 2 3 - 0 . 218 Logia (R/ c) = 0.694 (b) Level B 14 = 408 inches le = 2n *240 = 1,508 inches N, = 408/V240 *0.25 = 52.7 He = 150 8 //24 0
- 0. 25 = 19 5 M = Min ( N,, Ne ) = 5 2 . 7 c,3 = ata = 0. 2 07 cet = age = 0.8 SIR-92-063, Rev. O B-3 INTEGMTY ASSOCW'ESINC
a,ez = 1. 3 2 3 -0. 218 Logia = 1. 323-0.218Logzo
- 0.25 (c) Level C 14 = 408 inches le = 2x *240 = 1,508 inches . . - M T' I N _.
~~
CJ77LEMENT 14 = 408/V240 *0.187 5 = 6 0. 8 ; C ALC NO M- DSC-- vg O !
!sEvisl08 ' " #M3 !
H, = 150 8 /y24 0
- 0 .187 5 = 225 2 l3y v.M.EL-4k/L7 g /2o/9yl
!HECKED O E #- DAM'/b!
i I M = Min ( M,, N, ) = 6 0. 8 a43 = a4c = 0. 207 cet " 8ea = 0. 8 apt = 1. 323-0.218Logio = 1. 323 -0 . 218 Log 1a 0 .187 5
- i It is worth noting that the roundness requirements on the tank shell, ND-4220 of the ASME Code are implicit in the calculations of all the above reduction factors. Since the PPMST's were built originally according to API-620 and API-650 rules which did not have such roundness requirements, checks on roundness of the tanks per ASME, Section III, ND-4220 might be necessary to -j ustify accepting evaluation results by Code Case N-284.
B.5 Plasticity Reduction Factors (Step 5 of CC N-284) Since DBE loading is a Level D service loading, the factor of safety FS is 1.34 per the Code Case N-284. C+ FS .6843*1.34 = 0. 31 < 0. 55 o f 30,000 T14"1 SIR-92-063, Rev. O B-4 INTEGBrrY ASSOCIATESINC
l SUPfUMENT CALCNO N Dsc 24o g7ffy 8e M , 10646 *1.34 = 0. 4 8 < 0.67 REWION-# NU C 30*000 y y v.M. El- A r nsN y /23/q3
-1 CHECKED 'E' - N'l*N*-
11e = 1 B.6 Calculate Amplified Stresses (Step 6 of CC N-284) (a) Level A 0 4, = 0, , = 6 84 3
- 1. 4 = 28,528 psi (in compression) 321 ces = De s = 13724 *0.8 1. 34 = 22,988 psi (in tension) ec Tee , = T ,e = 4,346
- 0 b94 8,393 psi (in shear) a (b) Level B 4
0,, = 0, ,
= 4342
- O b07 = 28,108 psi (in compression) c,=ce e
a et
= 13 84 3
- 1. 3 4 = 23,187 psi (in tension) l 0.8 ;
I T,e, = T,e , = 3,735
- 1
- 3 7,437 psi (in shear) 73 l I
1 (c) Level C l 4 0,, = c, , = 2077
- 0.207
= 13,445 psi (in compression) c e , = 0, m et
= 1514 2
- 1
- 3 4 = 25,363 psi (in tension) 0.8 i
Tp, = Ty , = 3,325
- 1. 3 4 = 6,897 psi (in shear) l I i
t 1 i SIR-92-063, Rev. O B-5 1 INTEGRITY ASSOCIATEIhC
( 6M /Q WLEMENT _ _ _ . . , _ , B.7 Plasticity Effects (Step 7 of CC N-284) . 2A!.C .NO M- OSC# 'IO _ o,, = o,,/q , = o,, .?.EVIS!O# IDIS /'7.R c# e =ces/no = ce , i3YN.M. tirlr5) MIL {' g 2/2.0/f). e
- HECKED I' I' DATE /
0+ep " o,e, B.8 Determine Evaluation Approach (Step 8 of CC N-284) Article-1700, By Formula, of Code Case N-284 will be used to evaluate the reinforced PPMST. It is worth noting that the stresses calculated in Step 13 of this section are the maximum axial stress at a certain liquid level of the tank. Stresses at a higher elevations and other azimuth angles around the circumference are lower than the maximum values. However, the maximum stresses calculated in Step 13 are used conservatively for the evaluation in lieu of the average stresses within a meridional distance of flE permitted by Article-1711 of , the code case. B.9 Determine Allowable (Step 9 oh'CC N-284) 04,3 = ( C, +A C,) o p ,3 = (Cp +ACg ) AC, , AC, are included to adjust for internal pressure. It is specifically stated in Article-1500 of the Code case that "The influence of internal pressure on a shell structure may reduce the initial imperfections and therefore higher values of capacity reduction factors may be acceptable." Similarly, the latest AWWA Standard for Welded Steel Tanks for Water Storage [24] also allows the SIR-92-063, Rev. O B-6 INTEGMTY ASSOCIATESINC
i j .- i 4
- adjustment for internal pressure.
l (a) Level A GP T Hofo
~
= SUPPLEMEfff C, 3.62 +0.02534 wo y _ggc_,gg
! = 3.62 g,n g.i*2.49 2 REVISION # # "* I#I'*/93 j 2.49:
, BY u- M . E L - A 's "_ DATE7/22/#f' CHECKED 70 DAt[!M i
i
- A C, = A C*b = 0 . 3 5
- 0
- 74 = 1. 02 C, 0.255
} Cp = [4. 82 (1+0. 0239#3 )1/2+3.62 ( ) 2]
= 3 2.49, [4. 82 (1+0. 0239 *2. 49 )1/2+3.62 ( 21. 72 54 ) )
= 0.962 1
\ , 1 i ' In the above equations, the coefficients C, and A C, are i 4 elastic buckling coefficient and buckling coefficient i increment due to internal preissure defined by Baker, et j f al [22,23), and are calculated as follows 4 ! b= 2xR =41. 9 inches 1 36 j a/b = 72/41.9 = 1.7 > 0.5 i j Z=M /1 p =2 240 *0. 41 9 3125 /1 -0 . 32 = 2 2 , 3 RC 2E (.E} 2 = 17 87 240 *
= 0.376 l
C 28.03x20 5 ( 0.3125): .i From Figures 10 and 11, which are extracted from Figures 10-2 and 10-3 of Baker, et al, [22),
; C. 0. m
)
l l A C, = 0. 35 l< i,.* SIR-92-063, Rev. O B-7 1 l a MTEGRITY ASSOCIATESINC 4
~
1 It should be noted that the buckling coefficient c, given by Baker, l
)
et al (22,23) is corresponding to a 90 i I percentile failure of the actual test data while the 4 N-284 buckling coefficient C, is corresponding to a much higher theoretical buckling strength. The compound coefficient C,ag=0.125 is corresponding to the lower bound of test data and is certainly lower than the 90% failure coefficient t (0.255). A C, is the buckling coefficient increment due to internal pressure defined by Baker, et al (22,23). 5 og= (0.74+1.02)*28.3*10 *0.3125/240 = 64,235 psi o,,, = 80, 86 0 psi (see Appendix C for details) I o 8 pe = 0.9 62 *2 8. 03 *10
- 0. 3125/24 0 = 3 5.110 psi psi 1 Therefore, 8+, <
0+.r. Ces < 04es U+e, < GM4 The reinforced PPMST will not buckle due to the DBE loads at level A. S M'T. l b 7 (b) Level B ~ SUPPLEMENT C, = 0 . 6 0 5 CALC NO M- E -2 @ g .GV i 1"^* 10/S/G A C, = A C, = 0.164 0 605
# 3g = 0.70 gyv.n.ct.4 ktur g7/27/q 0.746 m ' F-4 ' '
IWWE IID' C p = @ = 0.103 A C, = 03 *0.27 = 0.361 (from Figures 10-4 and 10-6 of (22)) SIR-92-063, Rev. O B-8 INTEGBITY
. AssoCIATESINC
In the above equations, the coefficients C, and A C, are calculated per Baker, et al, [22,33], as follows l l b = 2xR = 1,508 inches 4 N /5 _ R/t = 240/0.25 = 960 JUPPLEMENT
~
0.23 CALC NO M-OSC * ' C* = = 0.139 V3 (1-0.32) (from Figure 12) j35VISIO[ IO O 2 lgyN-M EL- AkILY g l20/9]j 2( E
)2 . 14.42 240 28.03x10 ( 0.25 ) 2 = 0.474 fCHECKED_$6. DATE IS l ;
A c, = 0.16 (from Figure 13) Again, the buckling coefficient C, given by Baker, et a1 [12,13] is corresponding to a 90 percentile failure of the actual test data while the N-284 buc kling coefficientC, is corresponding to a much higher theoretical buckling strength. The compound coefficient C,a,3=0.125 is corresponding to the lower bound of test data and is certainly lower than the 90% failure coefficient (0.139) . The A C, factor is used to adjust for benefits due to internal pressure. 04 ,3 = (0.605+0.70) *28.14 *10'*0.25/240 = 38,620 psi op,3 = (0.103 +0. 361) *2 8. 03 *10'* 0. 25/24 0 = 13. 54 8 psi Therefore, j l 0 4s NU teL \ l 0 $0s IU $6eL l The reinforced PPMST will not buckle due to the DBE loads l 4 SIR-92-063, Rev. O B-9 ) l DITEGBITY ! ASSOCIATESINC l l
at level B. 6HT IS9 I
! SUPPLEMENT _ - _
(c) Level C 1 CALC NO C, = 0 . 6 0 5 ! REVISION # A C, = A C, C4
= 0.18
- 0 6 0 5 " U ' 8 0 BY^'
- L~
IM DATE N3! 0.121 ! CHECKEDb- dad 3f I 0.746 = 0.096 Cp= V60.8 ACp= 0.096 *0.35 = 0.467 (from Figures 10-4 and 10-6 of [22]) In the above equations, the coefficients C, and A C, are calculated per Baker, et al, [12,13), as follows, b = 2xR = 1,508 inches e R/t = 240/0.1875 = 1280 0.20 C, = = 0.121 (from Figure 12)
/3 (1-0.3 2) 11.83 240 2E (.E) 2 = = 0. 691 C 28.03x10 5(0.1875)
AC, = 0.18 (from Figure 13) Again, the buckling coefficient C, given by Baker, et al [12,13] is corresponding to a 90 percentile failure of the actual test data while the N-284 buckling coefficientC4 is corresponding to a much higher theoretical buckling strength. The compound coefficient C,ag=0.125 is corresponding to the lower bound of test data and is certainly lower than the 90% failure coefficient (0.139) . The A C, factor is used to adjust for benefits due to internal pressure. SIR-92-063, Rev. O B-10 INTEGRITY ASSOCIATESINC
c 4 ,r. = (0. 6 05 +0. 9 0) *2 8. 03 *10' *0.1875/24 0 = 33,4 04 psi 0 4e,:, = (0. 09 6 +0. 467 ) *2 8. 03 *10'*0.187 5/24 0 = 12. 3 2 8 psi Therefore, 0,< 4 %.s
% es < % eet The reinforced PPMST will not buckle due to the DBE loads at level C.
5,M T, 17 0 i
~~
' SUPPLEMENT CALC NO "'OZ~ 8----
RE':;SION Y #l
;y W.M- nE L- AkIL Y DATE Y.YW 79ECKED '
D AT E '@O l l e 1
; i SIR-92-063, Rev. O B-11 INTEGRITY ASSOCIATESINC
Attachment C Calculation of Stringer Buckling Stress Equations contained in Article-1712.2.2 of ASME Code Case N-284
- were used to compute stringer buckling stress. A copy of the Code
{ I case page is included in the next page l'or reference. After many
- iterations, it was found that the minimum stringer buckling stress i
og = 80,860 rsa i i } occur at m=1 and n=16. Computer outputs for the cases of (m,n)= (1,16), (1,15), (1,17), (2,15) , and (2,16) are attached. i i > l 4
- , SftT.l'Il' 1
i ~ SUPPLEMENT
- i. CALC NO M-E .2. @
g m y / D"e-10/S/93 , BY " '"' k~O ' ' Y DMY'Y3 l CHECKED T' S '- DM "
^
A i
- I i
i SIR-92-063, Rev. O C-1 1 DETEGRITY 1 ASSOCIATESINC
CASE (centinued)
! CASES OF ASME BOILER AND PRESSI!RE VESSEL CODE
-1712.2.2 Cylindrical Shells - Stringer Stiff. where ened or Ring and Stringer StfEened The theoretical clastic buckling stresses for both d" " #*
- 6" stringer buckling and general instability are given by 1
the equations which follow. Stringer buchg is defined an = E, as the buckling between rings of the stringer and at- 2 + G,, (.*. 4* #):
. I tached plate and general instability is defined as the me -
me. ' buchg mode in which the rings and attached plate + #* '+ deform radially. """ E,#*, K 2C,
+#"T' i The elastic buckling stress is denoted crg where iis P " f V(nt, i]
the stress direction andfis the buckling mode;f = S for stringer buckling and] = G for general instability. # 4 The stringer buckling stress is determined by letting A := (E., + G.,) *b N the cylinder length equal the ring spacing,j L = /., [ a3 + c, 2 and the general instability stress by lettingjL = L,. R The values of m and n to use in the following equa- 1 i[. tions are those which minimi" o g where m 2 1 and me I 7 n > 2. The following values are to be used for I. and Au" 3 L- + C+ y ' ' 3 I 7When /,. < t. or /,, < I,, set p = 0. '
,[ ) Et 9
}l Axial Compression E, =
E.= 1 F' \ *I + f,b 1 y-h l Et . EA, p 1 e., = e. E, = 3-
, t- G., = Gt f ,, la
- e. r e, 1 . e. 2 O
[ q /,, = /, if /, $; 1.288tQ Et' I., El. . EA. . ! h j /,,=1.9tQ(1- ifI, > !.288tQ 12(1 p ) 5 T t, I l M
- Q N N' D,=
Et3
- e. El,
- + Z4,:2 t 12 (1 - -)
1 M z) a wter. - /. $o D 0 uj 2: 9
- c. E g= E E D.,= 6 (1 p,) + 6 b+b+b+b I, I.
S ;o;i! @ 9($ .
@u %c.o 2 -
ri
- t. /,
u = c- u c,, W. c, , M,:, l f, 1 For stringer buckling: (b) External Pressure f = I A, = /, = J, = 0, t, = t. 4 = /, Stringer Buckling y = S) For general instability:
/,. = 8t but not greater than I.
l J = G, Q = Ls f , f, See -1521(a)(1) for c.o and the equation below for cry When I,, < I,, the values for cr.,j must be . A, = I, = J, = 0, t, = t. 4 = /. determined by iteration since the effective width is a function of the buckling stress. General Instability y = G)
"*<t "
^" (A::Au-AuA22AuAn-A% 22-A% I-u / +(\ AnAAaAu-AnAuf
/, = 1.56 di but not greater than /.
mw
'I~ __ f,,= f,Q = La SIR-92-063, Rev. O C-2 INTEGRITY ASSOCIATESINC
~
l } I m= 1 Sig$ej= 80860.38 3 ! n= 16 Q= 29.36504 alpha $G= 0.402 sq(E/Sy)=30.56686 Sig-y= 30000 1.288tQ= 11.81942 t= 0.3125 R= 240 E= 28030000 Nu= 0.3 G= 10780769 . L$= 408 LQ= 167.6 Lj= 167.6 I Le$= 408 LeQ= 17.03931 z$= 2.8125 zQ= 1 A$= 6.875 AQ= 0 ! I$= 10.417 IQ= 0 J$= 20.834 JQ= 0 t$= 0.353520 tQ= 0.3125 tSQ= 0.333010 ES= 2128409. EQ= 9625686. E$Q= 2887706. G$Q= 3711504. D$= 10845225 DQ= 78334.03 DSQ= 1447543. C$= 3233808. CQ= 0 } A11= 17243.41 , A22= 44084.90 A33= 172.2593 A12= 3608.590 A23= 2673.801 A13= 246.8350 gT ? ~7 } JUFPLEMEhT - - ,
- CALC NO
~N ~ ,
- nEVISION f / AM 10/ S / 93 '
d; -> h igy u M EL-rN</LV DATE ! N' ' Q*O DAT l CHECKED l l SIR-92-063, Rev. O C-3 INTEGRITY ASSOCIATESINC l
i n= 1 Sig$ej= n= 81040.48 15 Q= 29.33239 alpha $G= 0.402 sq(E/Sy)=30.56686 Sig-y= 30000 1.288tQ= 11.80628 i t= 0.3125 R= 240 E= 28030000 Nu= 0.3 G= 10780769 L$= 408 LQ= 167.6 Lj= Le$= 408 167.6 LeQ= 17.02081 z$= 2.8125 zQ= 1 A$= 6.875 AQ= 0 I$= 10.417 IQ= 0 J$= 20.834 JQ= 0 tS= 0.353520 tQ= 0.3125 j ES= 2127346. tSQ= 0.333010 EQ= 9625686. l ESQ= 2887706. G$Q= 3711132. j D$= 10845216 DQ= 78334.03 ) D$Q= 1447537. ' l l C$= 3233808. CQ= 0 A11= 15244.07 A22= 38904.28 A33= 171.6335 l A12= 3383.053 A23= 2506.689 i A13= 246.8350 4
$r T. : '? d
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. SUPPLEMENT i
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4 , i 1 SIR-92-063, Rev. O C-4 INTEGRITY ASSOCIATESINC
m= 1 Sig$ej= 82231.83 n= 17 Q= 29.11913 Glpha$G= 0.402 sq(E/Sy)=30.56686 Sig-y= 30000 1.288tQ= 11.72045 t= 0.3125 R= 240 E= 28030000 Nu= 0.3 G= 10780769 L$= 408 LQ= 167.6 Lj = 167.6 Le$= 408 LeQ= 16.89991 z$= 2.8125 zQ= 1 A$= 6.875 AQ= 0 IS= 10.417 IQ= 0 J$= 20.834 JQ= 0 t$= 0.353520 tQ= 0.3125 t$Q= 0.333010 ES= 2120403. EQ= 9625686. ESQ= 2887706. GSQ= 3708702. D$= 10845160 DQ= 78334.03 DSQ= 1447497. C$= 3233808. CQ= 0 A11= 19352.92 A22= 49598.63 A33= 172.9752 A12= 3834.127 A23= 2840.914 A13= 246.8350 s wT l 74-
, j
~
;SUPP!.EMENT lCA1.C NO ~#~
j 3 REVISIO i nru Iofr/93 i
)g y n. n a L- h W L Y W Y l; CHECKED - DE i 4
i 5 4 2 SIR-92-063, Rev. O C-5 INTEGRITT ASSOCIATESINC
n= 2 Sig$ej= n= 95424.60 16 Q= 27.03138 alpha $G= 0.402 sq(E/Sy)=30.56686 Sig-y= 30000 1.288tQ= 10.88013 t= 0.3125 R= E= 240 28030000 Nu= 0.3 L$= G= 10780769 408 LQ= 167.6 Le$= 408 Lj = 167.6 z$= LeQ= 15.71417 2.8125 zQ= 1 AS= 6.875 AQ= 0 I$= 10.417 IQ= 0 J$= 20.834 JQ= 0 t$= 0.353520 tQ= 0.3125 ES= 2052303. t$Q= 0.333010 EQ= 9625686. ESQ= 2887706. G$Q= 3684866. D$= 10844606 DQ= 78334.03 D$Q= 1447109. C$= 3233808. CQ= 0 A11= 19261.57 A22= 47959.68 A33= 199.1200 A12= 7217.180 A23= 2673.801 A13= 621.4589
$ 6 T.1 %
I 3UPPLEMENT
;CRCNO M -Ds C- MC I 1,EVIS10ftfy/
- r. nM4 10/G/93: .
'l3y v. M - arc-Ak i' / DATE E CHECKED -
DAW ! l l l l l l SIR-92-063, Rev. O C-6 DITEGRITY ASSOCUUEINC
l I m= 2 Sig$ej= 95930.68 n= 15 Q= 26.95999 alpha $G= 0.402 sq(E/Sy)=30.56686 Sig-y= 30000 1.288tQ= 10.85139 l i t= 0.3125 R= 240 E= 28030000 Nu= 0.3 G= 10780769 L$= 408 LQ= 167.6 Lj= 167.6 i Le$= 408 LeQ= 15.67355 z$= 2.8125 zQ= 1 A$= 6.875 AQ= 0 l I$= 10.417 IQ= 0 J$= 20.834 JQ= 0 t$= 0.353520 tQ= 0.3125 tSQ= 0.333010 l ES= 2049970. EQ= 9625686. ! ESQ= 2887706.- GSQ= 3684050. ) D$= 10844587 DQ= 78334.03 I D$Q= 1447096. C$= 3233808. CQ= 0 l A11= 17271.92 A22= 42778.04 A33= 197.6732 A12= 6766.106 A23= 2506.689 A13= 621.4589 i set T i 7 7_
~~
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1 Attachment 0 Examination Reconciliation with the ASME Code 4 i Examination of tank shell weldin the 1989 ASME Code, Section III,g by spot radiography is acceptable by both Edition. Subsection NO, and API Standard 650, 5th. Table 1 gives a comparison between the requirements of the Standard differences. showing the areas of agreement between n them and examination and the acceptability criteria for crowns . !
- \
Table 1
- Comparison Between API-650 ASME Code API-650 I ASME Section ND Cracks
- Unacceptable.
i Unacceptable. l !
<2/3T 0.K. 1 i <2/3T 0.K. i
'/4" Max. i 3/4" Max.
i Indications { i
<1/4" 0.K.
' <1/4" 0.K.
SUPPLMK Combined length of gg a - orc. 2%0 several inclusions y / nme g)ygy <T in 6T length. Same. j gy 9 u Et.- Akf LY ghe j m E6- DME,/YN7 Rounded indications are not i a factor in the acceptability ! of welds not required to be i \' ST1 T l'18 fully radiographed. ! 1 j First 10 ft, Frequency of Vertical First 50 ft, Spot 100 ft increments Joint 50 ft increments. i Radiography (25% at intersections).
- 3 j Horizontal First 10 ft, 200 ft 1
Joint increments. AP-650 g Crowns
<1/16
- in the area 3/32" Max. I where. spot radiography is planned.
Undercut No requirement. 1/32" Max. D-1
- - - .- - _ = _ - _ - . . . _ _ _ _ . - . _ . - _ - __ _
- NES&L DEPARTMENT CALCULATION SHEET = "," L o. ,A E ,,
1 CCN C NVERSION l Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN - , I ] subject See Title Sheet Sheet No. 17 h a j REV ORIGINATOR DATE IRE DATE REV ORIGINATOR' DATE IRE DATE
- O NA81L M. EL-AKILY 7/27/1993 JUN GAOR /[ 7/27/1993 j
i
/ v - 67. -/)ki Q 1815/ 9 3 74 '%f 3 f
i i 1 i i i J l 3 i j J
- APPENDIX - B l
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! CONTR0t. NO. os9 31 CERTIFICATE OF AUTHENTICITV l CONTINLATION . i i This is to certify that the microphotographic images appearing in this microform are direct and facsimile 1 j reproduct ons of the original records of the Southern California Edison Company and were microfilmed I in the regular course of business. The microfilming has been performed according to established routine Company Policy for systems utilizatior: and/or maintenance and preservation of records through the I storage of such microforms in protected locations. THE DOCUMENTS CONTAINED ON THIS MICROFORM ARE ORIGINAL RECORDS OF: r f[8 Southern California Edison l 1 b l For the MATERIAL & ADMINISTRATIVE SERVICES - CDM/ SONGS Department I
- Sun Ckufzu maclant Generatirq eaHm Dggign chim1mHmm l 1 l s <
This microform file is a complete record of the transaction herein recorded. The documents are arranged on this microform in the following manner: I O sv moach ia 'oe><ioa aaa work Order seaueace O Order of Payroll Location Number O ^inhabeticai order by- O crievaace rii. Number se9ueace
@ Numerical order by. Design Cal.Mo. Oo>ieorder O Order of Customer Service Store Number OOther j l
The hardcopy documents used to create this microform have been authorized for destruction after verification of correctness and acceptability of the microfilming. It is further certified that on the date specified below, the micrographic images appearing on this microform were made at a reduction ratio of 29 :1 under my direction and control. The above information is deemed necessary in compliance Licensees - issued March 14,1972. This order has subse. with the Federal Power Commission Order No. 450. Regu. quently been approved by the Public Utilities Commission lations to govem the Preservation of Public Utilities and of the State of Califomia on October 29,1974. IO-/T-93
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NES&L DEPARTMENT CALCULATION SHEET " * " ' DAEUM CCN NO PAGE OF ccN eonveRs:cN: Project or DCP/MMP 7 k D " Od7 D1 $ h Calc No. H - Df C - DC ccNNo CCN-- Subject (te Tlk b M-u/\ Sheet No. NO REV ORIGINATOR DATE 5tE DATE REV CRIGNATOR DATE 9RE DATE 8 ) O E .Std "/h1 f-6 W/e > > l U EL-hlC-l d N f) 'T(., ffy j A Q vicx cPEck mAv Mo +W W t. w'/.' i o c v ap MG s5 r.' o w. - t o a f. t.- 5 n w rJ E S % ,
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1 1 NES&L DEPARTMENT CALCULATION SHEET " " " '
'ACUM CCN No PAGE or ccN cCNVERS:ON:
Project or DCP/MMP 1 k 3 ?") Y2.07 5 H Calc No, M- 05c- M ecN No CCN.- Subject S /-< T ' k k b Sheet No. _ /h .l REV ORIGINATOR DATE RE DATE REV ORIGNATOR DATE IRE DATE
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NES&L DEPARTMENT CALCULATION SHEET " " " ' DAEUM CCN NO PAC.: OF CCN CONVERSIOtt Project ohiMP 2d 3 -6 M 2 o/- SM Calc No. M - MC - IhU CCN NO CCN-- 1 Subject PO W9 C 4 Gi 4fT W Attfr W S" ? d A ' L 'I~T- N (L Fob /W ES Sheet No. l 'I ~, l Rev oRomAToR DATE RE DATE MEV ORcNATOR DATE RE DATE g [c\ $ [<((h/ 12/,/,2 f< . Yuj$) [ l l u eAuu Y loh)v f t. . "/cin Ej won t. 3)u,
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^ALCULATION SHEET pot:ttM CCN No PAGE OF CCN CONVERSON:
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'1MP ~2 4 3 -[a ~74-2. . O 7- S(4 Calc No bll
- f ' 2h0 ccNNo CCN-Subject _ g1' d V Ct4NT M A'Z F O# 57 MG C %E #4c et710 5
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Sheet No. IN 3 REV URClNATOR DATE WIE DATE REV ORIGINATOR DATE ME DATE g-fc S. 0 31) *bl9 2. %. % 0 g h I us-nut )cisH3 n. '% Q ceec m r-s s q , 33 ' . 13,7ao] % y t . e v. r A e c W o c w-u_ t.y N
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NES&L DEPARTMENT CALCULATION SHEET "
- !MCN,o. ,A. ,,
CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - subject See Title Sheet sheet No. /h REY ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL-AXILY 7/27/1993 JUNCAOR[I.- 7/27/1993 ( H ' EG-f kILX 10h/9J f-G . 'ffFi APPENDIX - C ANSYS AND ME101LS INPUT FILES SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::r n No. ,Ax c, CCN CONVERSION Project or DCP/M4P SONGS 2 Calc No. M-DSC-280 CCN No. CCN - Subject See Title Sheet Sheet No. / REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUNGAOR((,, 7/27/1993 l n.ee-Av-tuv lofs/13 Fr. . t'/ds 4 List of ANSYS Input Files File Name Description Sheet
- PPMS1 Tank model with concentrated force of JQf, 1,000,000 lb applied near the top of the shell.
PPMS4 Tank model with forces applied at each shell 20( node. Each force is 1,000 lb in magnitude. i l SCE 26-426 NEW 4,90 l 1
1 NES&L DEPARTMENT
- CALCULATION SHEET
- ::n No. ,Au o, CCN CCNVER$10N Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN -
subject See Title Sheet Sheet No, /N REV CRIGlWATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NASIL M. EL AKILY 7/27/1993 JUN CAOR f [,. 7/27/1993 { H -EL-Okt LY >}]l 9] 7-6 , Hgn
/ PREP 7
/ TITLE, PRIMARY PLANT MAKE-UP TANK C*** FILE NAME: PPMSI.
C*** C*** FORCE APPLIED NEAR THE TOP C*** KAN,0 C*** C*** ELEMENT TYPE: ELASTIC SHELL ET,1,63 ET,2,8 C*** C*** MATERIAL PROPERTIES EX,1,28.3E6 ** TANK SHELL (TYPE 304 SS) NUXY,1,0.3 EX,2,30.0E9 NUXY,2,0.3 C*** C*** REAL CONSTANTS R,1,0.25
- BOTTOM R,2,0.3125
- FIRST TIER R,3,0.25
- SECOND TIER R,4,0.1875
- THIRD TIER R,5,0.25
- ROOF R,6,1.0
- SP0KES C***
C*** GE0 METRY RT=240.0
- TANK RADIUS H1=95.625
- HEIGHT TO TOP 0F FIRST TIER H2=167.25 HEIGHT TO TOP OF SECOND TIER HT=408.0
- TANK HEIGHT RBL=243.0-
- BOLT CIRCLE RADIUS RBT=246.0
- OUTSIDE RADIUS OF THE BOTTOM RR=576.0 ROOF RADIUS Al=SQRT(RR*RR-RT*RT)
A2=HT-Al
- CENTER OF COORDINATE SYSTEM 11 A3=A2+576.0 C***
C*** N0DE DEFINITION N,1,1.0
- CENTER OF THE TANK N,7,RT
- TANK RADIUS FILL,1,7
- N,9,RT,H1 FILL,7,9 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :=n . ,,, ,, Project or DCP/M4P SONGS 2 Calc No. CCN CONVEPSION
, H-DSC-280 CCN No. CCN -
Subject See Title Sheet
< Sheet No. / f)
REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL AKILY 7/27/1993 JUNGAOR$G. 7/27/1993 i H ' E L.-fac-tL Y l0}Sl43 7g, 1 i% % N,11,RT,H2 4 FILL,9,11 N,17,RT,HT FILL,11,17 C*** N,23,1.0,A3 \
- N,9000,0.,A2 l i
NGEN,2,1,9000,,,1.0 NGEN,2,1,9001,,,,1.0 CS,11,1,9000,9001,9002 , ) CSYS,11 FILL,17,23 C*** CSYS,0 j N,24,RBL 1 N,25,RBT C*** N,9003,0.,0.,0. N,9004,1.0,,-1.0 CS,12,1,9003,7,9004 CSYS,12 NGEN,72,25,1,25,,,5.0 NDEL,9000,9004 i C*** CSYS,0 N,1801,,367.875
- C***
C*** ELEMENT DEFINITION MAT,1 TYPE,1 l REAL,1
- BOTTOM E,1,2,27,26 EGEN,6,1,1 i E,7,24,49,32 E,24,25,50,49 EGEN,71,25,1,8 E,1776,1777,2,1 EGEN,6,1,569 E,1782,1799,24,7 E,1799,1800,25,24 C*** ,
REAL,2
- FIRST TIER E,7,8,33,32 EGEN,71,25,577 SCE 26426 NEW 4/90
CALCELYT5^dEdHEET ="" L . ,A. ,, CCN CONVERSION Preject or DCP/M4P SONGS 2 Cale No. M-DSC-280 CCN NO. CCN - sibject See Titie Sheet Sneet No. /N[ REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE < 0 NA81L M. EL AKILY 7/27/1993 7/27/1993 JUNCAOR[4-i M-EL-OcI L V l'M}93 7G, '%f 5 i E,1782,7,8,1783 i EGEN,2,1,577,648 C*** REAL,3
- SECOND TIER E,9,34,35,10 ;
~ EGEN,71,25,721 ! E,1784,9,10,1785 EGEN,2,1,721,792 ; C*** \ t REAL,4
- THIRD TIER I E,11,36,37,12
- EGEN,71,25,865 E,1786,11,12,1787
- EGEN,6,1,865,936 1 C*** l l REAL,5
- ROOF E,17,42,43,18 l l
EGEN,71,25,1297 I E,1792,17,18,1793 ) EGEN,6,1,1297,1368 C*** MAT,2 l TYPE,2 ; REAL,6
- SP0KES E,1801,16 E,1801,41 E,1801,66 E,1801,91 E,1801,116 E,1801,141 E,1801,166 E,1801,191 E,1801,216 E,1801,241 E,1801,266 ,
E,1801,291 ! E,1801,316 E,1801,341 E,1801,366 E,1801,391 ) E,1801,416 E,1801,441 E,1801,466 E,1801,491 1 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =L. , A. ,, CCN CONVERSION Preject or DCP/MP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN - subject See Title Sheet Sheet No. Ihh 1 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA81L M. EL AXILY 7/27/1993 JUNGAOR'J-(p- 7/27/1993 l N-EL-A4lGY 10/S}9) F&. Iff,y E,1801,516 E,1801,541 E,1801,566 E,1801,591 E,1801,616 E,1801,641 E,1801,666 E,1801,691 E,1801,716 E,1801,741 E,1801,766 E,1801,791 E,1801,816 E,1801,841 E,1801,866 E,1801,891 l E,1801,916 l E,1801,941 i E,1801,966 i E,1801,991 E,1801,1016 j E,1801,1041 E,1801,1066 j E,1801,1091 E,1801,1116 E,1801,1141 E,1801,1166 E,1801,1191 l E,1801,1216 E,1801,1241 E,1801,1266 E,1801,1291 E,1801,1316 E,1801,1341 E,1801,1366 E,1801,1391 E,1801,1416 E,1801,1441 E,1801,146f3 E,1801,1491 E,1801,1516 E,1801,1541 E,1801,1566 E,1801,1591 SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET n n ,.. ,A, ,, CCN CONVERSION Project or DCP/MP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN - Subject See Title Sheet 4 00 Sheet No. REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE 1RE DATE O NABIL M. EL-AKILY 7/27/1993 JUNGAORy[,, 7/27/1993 i N - EL.-l} el L-Y I0]sl99 gc , 175f,3 E,1801,1616 E,1801,1641 E,1801,1666 E,1801,1691 E,1801,1716
- E,1801,1741 E,1801,1766 E,1801,1791 C***
C*** LOADING AND B0UNDARY CONDITIONS WSORT,ALL NSEL,,24,1799,25
- FIXED N0 DES ALONG THE BOLT CIRCLE D ALL,ALL
- NALL
- C***
ITER,-10000,10000,1 F,1801,FX,1000000.0
- FORCE APPLIED AT THE CENTER C***
i AFWRITE FINISH
/ INPUT,27 FINISH SCE 26-426 NEW 4/90
)
CALCd" NT5d EdHEET = = t .o . ,, ,, Project or DCP/MMP CCN CONVERSION ; SONGS 2 Calc No. M-DSC-280 CCN No. CCN - 1 subject See Title Sheet Sheet No. 101 1 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE 1RE DATE { o mn m. u-uny mmm auwcAoR5t. mme l N-et-h tticy itsl93 gc. '#/sfa ; l l l
/ PREP 7
/ TITLE, PRIMARY PLANT MAKE-UP TANK C*** FILE NAME: PPMS4 C*** !
, C*** UNIFORMLY DISTRIBUTED FORCE AB0VE BOTTOM
- C***
KAN,0 C*** I C*** ELEMENT TYPE: ELASTIC SHELL : ET,1,63 ' ET,2,8 C*** C*** MATERIAL PROPERTIES EX,1,28.3E6
- TANK SHELL (TYPE 304 SS)
NUXY,1,0.3
- C***
C*** REAL CONSTANTS i R,1,0.25,0.25,0.25,0.25,30000.0
- BOTTOM l R,2,0.3125
- FIRST TIER R,3,0.25
- SECOND TIER R,4,0.1875
- THIRD TIER R,5,0.25
- ROOF C***
C*** GE0 METRY l RT=240.0
- TANK RADIUS H1=95.625
- HEIGHT TO TOP 0F FIRST TIER j H2=167.25
- HEIGHT TO TOP OF SECOND TIER ;
HT=408.0
- TANK HEIGHT RBL=243.0
- BOLT CIRCLE RADIUS RBT=246.0
- OUTSIDE RADIUS OF THE BOTTOM RR=576.0
- ROOF RADIUS Al=SQRT(RR*RR-RT*RT)
A2=HT-Al
- CENTER OF COORDINATE SYSTEM 11 A3=A2+576.0 C***
C*** N0DE DEFINITION N,1,1.0
- CENTER OF THE TANK i
N,7,RT
- TANK RADIUS FILL,1,7
- N,9,RT,H1 l FILL,7,9 N,11,RT,H2 FILL,9,11 N,17,RT,HT SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =&. , , , o, CCM CONVERSION Project or DCP/>MP SONGS 2 Calc No. M-OSC-280 CCN NO CCN - subject See Title Sheet sheet No. MY REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NABIL M. EL AKILY 7/27/1993 JUN GAOR % . 7/27/1993
- I N-EL-/}idU( IO]S/93 $g , Y{/g3 l
i FILL,11,17
- C***
N,23,1.0,A3 N,9000,0.,A2 NGEN,2,1,9000,,,1.0 NGEN,2,1,9001,,,,1.0 CS,11,1,9000,9001,9002 CSYS,11 FILL,17,23 C*** CSYS,0 N,24,R8L N,25,RBT C*** N,9003,0.,0.,0. N,9004,1.0,,-1.0 CS,12,1,9003,7,9004 CSYS,12 NGEN,72,25,1,25,,,5.0 NDEL,9000,9004 C*** CSYS,0 C*** C*** ELEMENT DEFINITION MAT,1 l TYPE.1 REAL,1
- BOTTOM I E,1,2,27,26 EGEN,6,1,1 E,7,24,49,32 E,24,25,50,49 EGEN,71,25,1,8 E,1776,1777,2,1 EGEN,6,1,569 E,1782,1799,24,7 E,1799,1800,25,24 C***
REAL,2
- FIRST TIER E,7,8,33,32 l
EGEN,71,25,577 I E,1782,7,8,1783 l EGEN,2,1,577,648 i C*** i REAL,3
- SECOND TIER l
( l SCE 254M NEW 4/90 i
NES&L DEPARTMENT CALCULATION SHEET = " n No. ,Aet o, CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 cCN No. CCN - subject See Title Sheet Sheet No. M) REV CRIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O NA8IL M. EL AXILY 7/27/1993 JUN GAOR [f, 7/27/1993
/ v -EL-A Ki LV l8/5/93 Tc. /%[9g i
E,9,34,35,10 EGEN,71,25,721 E,1784,9,10,1785 EGEN,2,1,721,792 C*** REAL,4
- THIRD TIER E,11,36,37,12 EGEN,71,25,865 E,1786,11,12,1787 EGEN,6,1,865,936 C***
REAL,5
- ROOF E,17,42,43,18 EGEN,71,25,1297 E,1792,17,18,1793 EGEN,6,1,1297,1368 C***
C*** LOADING AND B0UNDARY CONDITIONS WSORT,ALL NSEL,,24,1799,25
- FIXE 0 N0 DES ALONG THE BOLT CIRCLE D,ALL,ALL
- NALL C***
ITER,-10000,10000,1 NSEL,Y,2.0,500.0 F,ALL,FX,1000.0
- FORCE APPLIED NALL C*** ,
AFWRITE FINISH
/ INPUT,27 FINISH CCE 26-426 NEW 4/90
' NES&L DEPARTMENT CALCULATION SHEET :r,"oicN,c. ,A. ,, Project or DCP/M4P SONGS 2 Calc No. CCM CONVERSION M-DSC-280 ccN No. CCN - Subject See Title Sheet i Sheet No. bD REV ORIGINATOR DATE IRE
. DATE REV ORIGINATOR DATE IRE DATE O NABIL M.'EL AKILY 7/27/1993 JUNGAOR'y6, 7/27/1993
/ IJ -EL-@ k t G Y 10}S}f] F.f , l'/{l$ ',
l l l l l l l APPENDIX - D REFERENCE DOCUMENTS SCE 26-426 NEW 4/90
Primary Plant Makeup Storage Tank (PPMST) Nozzles NOZZLE SIZE QUANTITY ELEVATION DESCRIPTIONSIREMARKS A 3" 1 10'-7" CCW Safety Related Makeup Pumps Suction B 1" 1 16'-0" CCW Safety Related Makeup Pumps Miniflow Back to the PPMST _7 F t 2h" 1 31'-0" Existing Fill Line for the PPMST (Relocated) H G 2" 1 31 *-0" Existing PPMST Pumps Recirc to the PPMST (Relocated) H 4"
- =
_ g u 1 31'-0" Existing Suction Line for the PPMST Pumps (Relocated) - t g'" ,< J 4" 1 9'-9 saire" Existing PPMST Oveiflow Line K 3"
&E 1 8 '-5" Existing PPMST Drain Line L
N&:= 2" 2 9 '-6" Existing Level Transmitter Taps t 42 *.0" M. 2" 1 9 '-8" Existing PPMST Pumps Recirc to the PPMST (to be capped) N 28" 1 9'-7 srire" Existing Fill Line for the PPMST Pumps (to be capped) P 4" 1 9'-6 ssire" Existing Suction Line for the PPMST Pumps (to be capped) f}fT. Vo r surrumm _ , , _
* ' V > ' ' "
CALCNO NOTE: All elevations are pipe centerline elevations. N' *"% ggy,g,nn
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NES&L DEPARTMENT CALCULATION SHEET = n N No. ... ,, Project or DCP/MP 2 & 3 - 6742.07 SM cale No. M-1203-476-2A CCA CONVER$10N CCM No. CCN - subject SE'E- TITLE SHEET sheet no. REV ORIGINATOR DATE 1RE DATE REY ORIGINATOR l DATE IRE DATE 0 P. DE ALDAY 02 23 93 { 2/gg i 1 I 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS (CONT'D) EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE (*) REMARK DATA POINT MOMENT (FT-LBS) (LBS & FT-LBS) Tank - T056 Fx = 0/ - Nozzle A Fy = + 58 /
/2/ Fz = 0/ COPY iGR YOUR WT01 Mx = - 67 / }gyggy,i}DH i
)
My = 0/ Mz = -130 / I THEM01 Fx = -755 / - Fy = + 12 / Fz = -287 / Mx = + 10 / My = -237 / Mz = - 38 / SEIS01 Fx = Seismic 86 / - Fy = 28 / loads are Fz = 37 / +/- Mx = 45 / My = 47 /' Mz = 115 / TOTAL LOADS: Fx = +172 / - See note
-927 / (1)
WT01+THRM01+(2xSEIO1) Fy = +126 / M-a AY 0/
),,h Fz = + 74 / SUPfG MB R
-361 / my WOS C - 2 ?O
/\ <X Mx = + 33 /
-157 / REVISION ys om e,gj3 j9, My = + 94 / gy g -
-331 /
Mz = +100 / N N E
-398 /
Notes : (1) Tank Rev. O nozzle loads are evaluated in calculation M-DSC-269 SCE 26-426 NEW 4/90
3 NES&L DEPARTMENT CALCULATION SHEET g i: n No. ,A, ,, Project or DCP/MMP _ 2 & 3 - 6742.07 SM Calc No. CCN CONVERSION M-1203-478-2A Ccn No. ccN - subject SEE TITLE SHEET REV Sheet No. .3b ORIGINATCR DATE IRE CATE REV CRIGINATOR DATE O IRE DATE tao VAN NCUTEN 12 09 92
*h l'h,g 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS (Cont'd.)
EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE DATA POINT / REMARK LDCASE MOMENT (FT-LBS) (LBS&FT-LBSgS ..T, ! Tank -T056 FX = + Nozzle B 3 / ,1'-kNb FY = - 15 / g[GJ$ !
/ 2A / FZ = + 2 / VTW c; I
! l g , 5 SUPPLDIENT I MZ = - 2 / CALC NC O'W~U #
THRM1 FX = + 3 / - REVISIOfl # "'" " FY = - 3 / ~ FZ = + BY DAIE 3 / MX = + 2 / CHECKED
~
DATE MY = + 5 / MZ = + 12 / SEIS1 FX = 30 / FY = 7 / Seismic FZ = loads are 25 / MX = +/- 2 / MY = 60 / MZ = 6 1 TOTAL LOADS: WT.'.+THRM1+2 SEIS1 FX = + 66 / SAM Loads 66 _ are N df FY = + 32 / negligible
= - 32 FZ = + 55 / See note
=-55
, MX = + 6 / (1)
=- 6 MY = +130 /
= -130
$ I, MZ = + 22 /
= - 22 ;
Notes : (1) Tank M-DSC-269 nozzle Rev.0loads are evaluated in calculation SCE 26426 NEW 4/90'
NES&L DEPARTMENT SUPPLEMENT *A* CALCULATION SHEET l : n n ,. ,,x 23 C, y, CCN CCNV[R$1CN Project or DCP/MMP 2 & 3 - 6742.07 SM Calc No. S-1415-22 :CN No. CCN - subject SEE TITLE SHEET Sheet No. A - 26 REV ORIGINATOR DATE IRE CATE REV CRIGihATOR DATE IRE l DATE O S.8tsWAS 12 23 92 7vy M.Jo-fg-i i 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK . l DATA POINT / MOMENT (FT-LBS) (LBS & FT-LBS) LDCASE Tank -T056 FA = + 3 - Nozzle Q'F FB = - 67 o N
/ 5/ h., FC = - 1 kg\hg\bggh.$g L iO l WT1 "dM-
- MA = + 1 \W 60 E CALCFD iv\ - 0 5'^ - 2 ?*
THRM1 FA = - 62 - y' REVISI M "" 10l5/*J FB = + 43 FC = - 9 8Y u er ---- MA = + 6 MB = + 12 CHECKED ME-MC = - 79 ; SEIS1 FA = 36 - Seismic FB = 152 loads are l FC = 44 +/- MA = 32 MB = 46 MC = 189 TOTAL LOADS: FA = + 131 / _ WT1+THRM1+2SEIS1 - 131 See note Yb FB = + 371 / (1)
= - 371 FC = + 98 /
= - 98
- MA = + 71 /
,,g C = - 71 L
MB = + 105 /
= - 105 2 % MC = + 517 / i 0- = - 517 %
Notes :' (1) Tank nozzle loads are evaluated in calgulation j M-DSC-269 Rev.0 SCE 26 426 NEW 4/90 i
NES&L DEPARTMENT SUPPLEMENT *A* CALCULATION SHEET ;;r,"o m . ,Aem ,, o CCM CONVER$10N Project or DCP/MMP 2 & 3 - 6742.07 SM Calc No. 844 CCM No. CCN - Subject SEE TITLE SHEET Sheet No. A 2h REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE CATE 0 s.stswAs 01 04 93 h / f -f3 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK DATA POINT / MOMENT (FT-LBS) (LBS & FT-LBS) LDCASE Tank -T056 FA = + 6 - Y
~
Nozzle G FB = - 84 QS YOA
/5/ FC = + 2 YJ WT1 MA = - 2 \\\N% %\(5M i.O ' i g MB = - 4 MC = - 85 SUPFLEMEPE- l THRM1 FA = - 28 ,
W M M-N< - f 80 l FB = + 11 REWif0N Er / W Whjey l FC = - 1 MA = + 1 BY n n' - I i MB = + 2 CHECKED -- Ds n~ ~
]
MC = - 62 SEIS1 FA = 50 - Seismic FB = 502 loads are FC = 62 +/- MA = 34 MB = 85-MC = 587 TOTAL LOADS: FA = + 106 / _ WT1+THRM1+2SEIS1- - 122 See note Y,b FB == + 931 / (1) L -1088 FC == + 126 /
- 123 o
MA = + 67 / 10 g if, = - 70 MB = + 168 /
= - 174 2 N MC = +1089 /
g
= -1321 Notes : (1) Tank nozzle loads are evaluated in calculation M-DSC-269 Rev.0 SCE 26 426 NEW 4/9o
NES&L DEPARTMENT SUPPLEMENT *A* CALCULATION SHEET ::,N/de. ,m m, u Project or DCP/ HHP 2 & 3 - 6742.07 SM Calc Ho. S-1415-06 CCN CONVER$!04 CCN No. CCN - Subject' SEE TITLE SHEET sheet No. _A b l REV CRIGINATOR DATE IRE DATE REV CRIGINATOR DATE l IRE CATE O TAO VAN NCUYEN 12-17 92 [h y - f f.21.(/ I 8.6 I EQUIPMENT NOZZLE LOADS EVALUATIONS l l EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK DATA POINT / MOMENT (FT-LBS) LDCASE (LBS & FT-LBS) Tank -T056 FA = 13 - Nozzle H FB = - 137
/ 3C1 / FC = 19 D-
~
WT1 MA = - 17
. , , l Yo '
MB = - 46 SUPP24ENT-MC = - 180 Calc Im M- OSC - I 7/O '
'THRM1 FA = - 68 FB =
REVISION -
#l#1 8
FC = + 14 BY- DJ TE -- 1 MA = - 14 CHECGD
~
MB = - 33 DA FE ~~ MC = - 208 SEIS1 FA = 116 - Seismic FB = 258 loads are l FC = 119 MA = +/- 42 MB = 181 MC = 512 TOTAL LOADS: FA = + 245 / WT1+THRM1+2SEIS1 - 287 See note g hY FB == + 387 / (1)
- 653
,FC = + 271 /
(
= - 219 MA = + 67 /
g.,- y = - 115 ; MB= = + 316 / g 2"q - 441 MC= n + 844 / i h -1412 i Notes : , (1) Tank nozzle loads are evaluated in calc,u_1._ation i M-DSC-269 Rev.0 ' l SCE 26-426 NEW 4/90
1. NES&L DEPARTMENT supplement w CALCULATION SHEET ::: n ,..c-2 ,A. ,, CCN CONVERSION Project or DCP/M4P 2&3 - 6742.07 SM Calc No. S-1415-37 CcN No. subject See Title Sheet Sheet No. A-REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE fo\ u vEna rana 2 11-95 Q z/nt'73 /\
/\ /\
8.6 Equipment Nozzle Loads Evaluation : gp1IDE gBRMhD , Equipment Force (Lbs) I.D. Moment (Ft-lbs) Remark
/ Data Point M T.1) 3
/ Loadcase l Tank T-056 Fa = - 6 Ma = - 1 ,,
and T-055 Fb = - 564 Mb = + 0 CALC NO M- V 5' 4f' Nozzle J Fc = + 0 Mc = - 356 REVISION d' Y8Ild?
/ D.P. Al ~
)
/ Dead Weight BY DATE ;
~
Fa = - 1 Ma = + 0 CHECKED D4rg ~ Thermal Fb = + 0 Mb = - 1 ' Fc = + 0 Mc = + 4 l Fa = 1 Ma = 35 SAM loads l I SAM (DBE) Fb = 103 Mb = 4 are +/- Fc = 5 Mc = 71 Fa = 87 Ma = 166 Seismic (DBE) Fb = 610 Mb = 102 Seismic loads FC = 90 Mc = 385 are +/- Total Design Fa = + 81 Load - 93 i Fb = + 54 l T l Eb
- 1183 l Fc = + 90 l
- 90 See Note (1) '
Ma = + 169 Fc 7 170 g o y Mb = + 102 2 - 103 k Mc = + 39
- 748 Note : 1) Nozzle loads are qualified by calc. M-DSC-269 Rev. O SCE 26 426 NEW 4/90
f . NES&L DEPARTMENT Supplemsnt 'A' CALCULATION SHEET g r n No. c-1 ,A , ,, I CCN CONVER$10N Project or DCP/MMP 2&3 - 6742.07 SM Calc No. S-1415-56 CCN No. Subject See Title Sheet Sheet No. A-DATE IRE DATE REV ORIGINATOR DATE !RE DATE REV ORIGINATOR [0k L! FENG YANG 2-19-93 2./9- D [k
/\ /\ ^
aur r -. CALCI' h^~O$_~N# 8.6 Equipment Nozzle M ads Evaluation : RE\t [ ' 15/'13
~ -- ~
BY . --_ DATE
~
~- ___ JATE Equipment I.D. Force (Lbs) ~-'
/ Data Point Moment (Ft-lbs) Remark l
/ Loadcase iMN Fx = + 0 Tank T-056 and Fy = - 188 *yy': %150N T-05y Fz = + 0 155 g.ylDN ,
l Nozzle K Mx = + 287
/ D.P. 5 My = + 0 i l
/ Dead Weight Mz = - 287 Fx = 182 Fy = 146 Seismic (OBE) Fz = 182 Seismic loads l Mx = 244 are +/- l My = 512 Mz = 244 1 Total Design Fx = + 182 Load - 182 Dead weight + Fy = + 0 2(Seismic) - 334 FZ = + 182 U -
182 Mx = + 531 See Note (1) 0 My = + 512 Z
/\ X 512 Mz = + o 531 Note : 1) Nozzle loads are qualified by calc. M-DSC-269 Rev. O l
l SCE 26-426 NEW 4/90
t NES&L DEPARTMENT
- CALCULATION SHEET =
- % ,0. -
,A,E ,,
- Project or DCP/B04P _2 & 3 - 6742.07 SM CCM CONVERSION cale No. _ M-1203-476-3A CCn no. ccN -
i subjet SEE TITLE SHEET sh t u.. REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 0 P. DE ALDAY 02-23 93 h Ig., - 1 i 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS (CONT'D) 4 ' EQUIPMENT I.D./ FORCE (LBS) DATA POINT ALLOWABLE (*) REMARK MOMENT (FT-LBS) (LBS & FT-LBS) Tank - T055 Fx = 0/ Nozzle A Fy = + 58 / 1 q j
/2/ Fz = 0/ {,Di$IggjgSB WT01 Mx = - 67 / g(M6k@$ Sn'I[
M +130 SUPPtmABIT l i THRM01 Fx = +755 / - CALC No ' ' ' ' ~ " " ~ - 2 N i Fy = + 12 / REVISIOW-g f ne ' * '<" ? i Fz = -287 / BY ~ Mx = + 10 / DATI -- My = +237 / CHECKE) DATI Mz = + 38 / . SEIS01 Fx = 86 / - Seismic ' Fy = 28 / loads are Fz = 37 / +/- Mx = 45 / ' My = 47 / Mz = 115 / TOTAL LOADS: Fx = +927 / - See note
-172 / (1) 4WT01+THRM01+(2xSEIO1) Y Fy = +126 /
% M "
0/ j 2 Fz = + 74 / h -361 / h I X My = +331 / 15 _3 n g - 94 / pfe, MZ = +398 / a
-100 /
Notes : (1) Tank Rev. Onozzle loads are evaluated in calculation M-DSC-269 i SCE 26-426 NEW 4/90 i t
NES&L DEPARTMENT CALCULATION SHEET =:% No. j ,,, ,, i Project or DCP/MMP 2 & 3 - 6742.07 SM Calc No. CCN CONVER$lCN ' M-1203-478-3A CCN No. CCN - subject SEE TITLE SHEET sheet No. 37 REV ORIGINATOR DATE IRE DATE REV CRIGINATOR DATE IRE CATE 0 TAC VAN NGUYEN 12 15-92 h ll[gg ' 1 ll 8.6 ggp1 ygg 10BR ! EQUIPMENT NOZZLE LOADS EVALUATIONS (Cont'd.) {}((0RIdbON EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK DATA POINT / MOMENT (FT-LBS) LDCASE (LBS & FT-LBS) Tank -T055 FX = - 2 - Nozzle B FY = - 15 g WT . 9.4 5
/ 2A / FZ = + 2 WT1 MX = - 2 SUPP!JNENT
+ CALCPO M - 05c - Iffo THRM1 FX = - 3 -
FY = - 3 BY --' tMQ E [ 3 2 CHECKED DME~ MY = - 5 MZ = - 12 SEIS1 FX = 27 FY = 7 Seismic FZ = loads are 24 MX = 2
+/-
MY = 59 MZ = 6 TOTAL LOADS: FX = + 59 / WT1+THRM1+2SEIS1 SAM Laads 59
;y FY = + 32 /-
are
. negligible
= - 32 4
FZ = + 53 / See note
= - 53 MX = + 6/ (1)
=- 6 X
MY = +128 /
= -128 3
MZ = + 22 /
= - 22 Notes :
(1) Tank nozzle loads are evaluated in calculation M-DSC-269 Rev.O i SCE 26-426 NEW 4/90
1 NES&L DEPARTMENT
- SH T. D-l$
CALCULATION SHEET i::;%,. ,,, ,, Project or DCP/MMP . 2 & 3 - 6742.07 SH CCN CCNYERSION i cale No. _ H-1203-482-AA CCa No. ccN - subject SEE TITLE SHEET aEV calc 1NAfoe
$heet No. 31.
DATE laE DATE aEV OtictMAfee j o s. siswAs DATE IRE l 12 18 92 h (thg3 DATE NOTE : THIS NOZZLE IS NO LONGER USED AND IS CAPPED. LOADS ) 8.6 INCLUDED HERE ARE FOR INFORMATION ONLY.
- EQUIPMENT NOZZLE LOADS EVALUATIONS (CONT'D)
EQUIPMENT I.D./ FORCE (LBS) j DATA POINT ALLOWABLE (*) REMARK i ' . MOMENT (FT-LBS) (LBS & FT-LBS) Tank - T055 Fa = - 2 - Nozzle C, Fb = + 64 ' ggg i /455/ Fc = - 7 S j WT01 Ma = - MM Mb = - 22 2
%j @i"'
Mc = - 7 6 StPPLBENT m THRM01 , y M-Osc -2go < Fa = + 17 - RE,asUii N N/n Fb = + 5 f Fc = - 1 2 U i Ma = + 2 M- ~-- Mb = - 13 CHECKED- - nATEl _~ Mc = - 63 SEIS01 Fa = 71 Fb = 211 Seismic Fc = 108 loads are Ma = 19 +/-
! Mb = 233 Mc = 410 TOTAL LOADS: Fa = +157
-157 See note WT01+THRM01+2SEIO1 Fb = +491 (1) g -491 Fc = +225 I
-225
.x 4 Ma = + 40
" - 40 Mb = +501
-501 g Mc = +959 1
-959 Notes : (1) i TankOnozzle loads are evaluated in calculation M-DSC-269 Rev. !
i c i SCa 38 438 NEW 4/30 ! l 1 i
l 1 NES&L DEPARTMENT SUPPLEMENT "A" l CALCULATION SHEET ::::= .A c, , CCN CONVER$!CN Project or DCP/MMP 2 & 3 - 6742.07 SM cale No. S-1415-04 CCs so. ccN - subject SEE TITLE SHEET Sheet No. A l'I REV CRIGINATOR DATE IRE DATE REV CRIGINATOR OATE 1RE ' DATE l o S.81$WAs 12 29 92 ygg l_Q _q 3, t 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK DATA POINT / MOMENT (FT-LBS) (LBS & FT-LBS) LDCASE Tank -T05$5 FA = - 1 -
%h -
/ 5 FC 2 -c" E iMT.lt$
WT1 MA = + 1 h : MB " - 5 SUPPLEMENT ! MC = + 40 t, _ n er _ gg ll UAbu nu " '- - ' THRM1 FA = - FB = - 60 29 REVEION M'*
~
h LTE FC = + 1 BY O CHECKED [{ 1 LTE - M'C = + 42 l SEIS1 FA = 85 - Seismic FB = 255 loads are FC = 73 +/- MA = 23 MB = 132 MC = 557 TOTAL LOADS: FA = + 231 / - WT1+THRM1+2SEIS1 - 231 See note o i,b FB = + 554 / (1) b = - 554 M , FC = + 149 /
@O =- 149 6 / 48 2'I" MB = + 269 / "
=- 269
'A MC = +1196 / "*. .
'l
= -1196 Notes : (1) Tank nozzle loads are evaluated in' calculation M-DSC-269 Rev.0 SCE 26-426 NEW 4/90
l l NES&L DEPARTMENT SUPPLEMENT *A* l CALCULATION SHEET ;;;: = 0. ,Ax C, CCN C0hytR$1CN Prtject or DCP/ HHP 2 & 3 - 6742.07 SM Calc No. 807 CCN ho. CCN - Subj ct SEE TITLE SHEET Sheet No. A- I REV CRIGINATCR DATE !RE DATE Riv l CAIGINATOR DATE IRE DATE 0 TA0 VAN NGUYEN 12 28 92 [fh ff.g.f; 1 I l l 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS l EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE .
~ REMARK l DATA POINT / MOMENT (FT-LBS) (LBS & FT-LBS)
LDCASE I Tank -T055 FA = 0 - pg ' Nozzle # Q FB = + 24 9,j FC = + Ng j@6NY. T M'f t h,
/ 3C1 / WT1 1 INgeS '
7lt yf 42. MA = + 1 MB = - 2 SUPPLEMENT i
- MC = + 9 , , , _ _
- nw M- Osc. - i g f.
1 l THRM1 FA = - 19 - gg M/""-l '#M/f7 ) l FB = - 40 BY DAT .
=
FC = + 4 MA = + 4 CHECKl!D " DATlE 13 : MB = - ~ MC = - 56 SEIS1 (OBE) FA = 43 - Seismic FB = 91 loads are i FC = 81 +/- MA = 9 ) MB = 192 MC = 205 . TOTAL LOADS: FA = + 86 / _ l WT1+THRM1+2SEIS1 - 105 See note ' C, t y g FB = + 206 / (1) g =
- 198 i ,
s
**'9 FC = + 167 / ;
j
= - 161 !
A MA = + 23 /
=- 17 ;
,f MB = + 382 /
= - 399 Q MC = + 419
= - 457 '.
Notes : (1) Tank nozzle loads are evaluated in. calculation M-DSC-269 Rev.0 SCE 2&426 NEW 4/90
NES&L DEPARTMENT SUPPLEMENT "A* CALCULATION SHEET ::::ry:,. ,A m n G, y Prsject or DCP/ HHP 2 & 3 - 6742.07 SM Calc No. S-1415-07 CCN CCNVER$10N Ccx No, ccn - subject SEE TITLE SHEET Sheet No. AM REV CRIGINATOR DATE IRg DATE REV CRIGINATOR DATE !RE DATE o tao vAu uGuvEn 12 19 92 ($ s2 2L-72 1 8.6 EQUIPMENT NOZZLE LOADS EVALUATIONS EQUIPMENT I.D./ FORCE (LBS) ALLOWABLE REMARK DATA POINT / MOMENT (FT-LBS) (LBS & FT-LBS) l LDCASE Tank -T055 FA = + 19 -
,.w _
Nozzle M FB = + 181 ...0 Y& *
/ 3C1 / WT1 FC = - 13 ~[. , . '"g,\6$ ggt -,Ao MA = - 14 i ,, . u ' " - - -
MB = + 50 MC = + 362 SUPPLEMENT - THRM1 FA = - 35 CALC NU ,, MO FB = - 24 REVHl10N gg m apj,y FC = - 3 MA = - 6 BY h EE ~ MB = - 3 CHECKED "O LTE __ , MC = 71 . . . SEIS1 (OBE) FA = 136 - Seismic FB = 542 loads are FC = 230 +/- MA = 47 MB = 638 MC = 1606 TOTAL LOADS: FA = + 291 / WT1+THRM1+2SEIS1 - 288 See note M C W6 l FB = +1265 /
= - 927 (1) 1 l
Vs FC = + 447 / A , = - 476 l
=- 1 X
MB = +1326 / 3 = -1229 MC = +3645 / -
= -2850 -
Notes : , (1) Tank nozzle loads are evaluated in calcAlation M-DSC-269 Rev.0 ' l 1 l SCE 26-426 NEW 4/90 l l
I NES8L DEPARTMENT SUPPLEMENT B CALCULATION SHEET *** * ' c- 2. 04EUM CCN NO PAGE OF CCN CONVERSON: Project or DCP/MMP 2d3-6702 O'7SM Cale No. P- 4 50 - /. 2 2, ccNNo CCN-SL)S CALC, Af 0 ;; ll C Subject 5E.6, TITLE SHEGT Sheet No. 8 nry omomAfon cATE stE DATE 1 MEV ORCNATOR SATE WlE DATE h dh dafn % b' V *! O g
/\ /\ 9l
^N SA- M u)-226-HOOC
/\
N' [][{ iC?. '". 13,iGI!.U.5Il0II 5, G f::;/ " S H T*. M P3g *y*M. '.i L OAC 5 ,
-g /
i N #'N I2-
,, , it f CO N r.sg.yA rt v6 i N
' L.4x4xQ C s's) SUPPLEMENT w-r. n i L o ^ o AT' JO'M T - 3 CALC NO M - N ' 2 00 N gj wx Fxf Fe Ge soo" y -- - LoAo AT Joi9 T- 7 CHECKED ' DATE ~ w. Fy = t 3o o
,SA sso o rd FAPP5 C M E '5'0 3 CO O7 0u T Ef2 ouT PuT A
rne m rsEPI A Q_E Acc6PTAGLE Fo e. Ste6S AND Dis ete temF td6LD is A Ls o Ac c F PT A (3 L6 PEE. t4Etro FAPps e u Aty.fi.t. Ca e c.(c S T R.A P ct. t u u 4 '( cmp _t u r r ELL) - 4" f t pE Ablo w AGLE pep. LC D =
- Sid s to A D = 380 FoC LB'EL'A'0 (Fea hg WEtp strzap) Tegn o a t. Ac , 2531 # Fe e. t.EV6l. - A G NTERACTi oaf = 3gp 3so 3 0 o ' - O. p 2557 (l.O &E LEVEL - D Lo A D 0 SED fe) f r5-t Lev s c. A .s AttogAs3ter.
.c= u..a . . .,..
g ,,,,,, ,,, _,
NES&L DEPARTMENT SUPPLEMENT: B CALCULATION SHEET = gg. ,A,, 0, CCN CONVER$10N Project or DCP/>NP 283 - 6742.07 SM Cale No. P-450-1.22 CCN NO. cCN - Sub Cole No. - 110 subje:t SEE TITLE SHEET sheet No. 8 REY ORIGTNufot DATE IRE DATE REY ORIGINATOR DATE !RE DATE O N.PATEL 2 17 93 7f s/. [./7 fj SA.NW-228.H.002 STRESS RESULTS IN ABSOLUTE TERM 5(+/.) LOAD : . . . . . . . . BENDING
. . . .. . . . BENDING
. . . . . . . .WARP
. . . s 1NG TRE s s t s . . . . . . . . . . . . . . . . . . . . . . . . . . . : . . . I N T E RAC T I ON v A tu E S. . .
$MEAR SHEAR SHEAR MEM J01 NAME TYPE AXIAL Y Z NORMAL Y ALLOW. MAXIMUM MAXI M MARGIN Z TOR $10NAL FACTOR NORMAL 1 SHEAR FACTOR l 1 FAULTED ACTUAL .C80 10.537 4.640 .000 .456 456 2.495 1.000 .797 .231 1.254 2 ACTUAL .080 .617 .272 .000 .453 .453 2.476 l FAULTED ALLOW 17.594 1.000 .051 .229 4.358 19.140 19.140 19.140 12.760 12.760 12.760 l CVERALL MINIMUM STRESS MARGIN FACTOR = 1.25397
............ 5 F'-) . qav -
SUPPLEMENT CALC NO M ~ Y26d - 2 5 0 UNIT 5: KIPS. INCH,0EGREE5 M ON- M# " 'cl5/43 015 PLACEMENT CHECK RESULTS(GLOBAL) gy_ - -
.................................. OME JOINT DIRECTION ALLCW. ACTUAL CHECKED- - DATE-3 X .C6250 .00159 3 Y .C6250 .01023 3 Z .C6256 .00345 .
I h ,7 UNITS: KIPS INCH.0EGREES JOINTDISPLACEMENT$(GLOBAL) JOINT LOA 0 NAME X OISP Y 015P Z 015P 1 ROT Y ROT Z ROT 2 FAULTED +/- .00186 +/. .01276 +/. .00345 +/. .32427 +/. .04919 +/. .06291 3 FAULTED +/. .00159 +/. .01023 +/. .00345 +/- .32427 +/. .04924 +/. .06291 UNITS: KIPS,!NCH,0EGREES MEMBER END. ACTIONS IN LOCAL C00RolNATE SYSTEM
- ...................r0RCES................... ..................M0KONTS...................
MEMBER JOINT LOAD NAME AXIAL SHIAR Y SHEAR Z TORSIONAL BENDING Y BENDING Z 1 1 FAULTED +/. .300 +/. 1.140 +/. 1,140 +/. .000 +/. 14.480 +/. 14.479 2 FAULTED +/- .300 +/. 1.131 +/. 1.131 /. .000 +/- .849 +/. .B49 2 2 FAULTED +/. .300 +/- .000 +/. .300 +/. .000 +/. 1.200 +/. .000 3 FAULTED +/. .300 +/. .000 +/- .300 +/. .000 +/. .000 +/. .000 UNITS: KIPS,1NCH JEG m L0603 je e.y g gj pg pg 3 g SUPPORT REAGIOhi(GLOBAL) hhfkT h[hNkMI FX FY FZ MX MY M2 1 FAULTEr .f. .300 +/. 1.313 +/. .300 +/. .000 +/. 4.800 +/. 15.677
i ' g,PI 0432 y ( l' O M M s t u n *
- n u n u n x u * *
- n u n * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ,n: *** u u n 3 3 3 x
x n ': 0 N T, S 0NSTRUCT T0N U0?K 0RDEP u n ===u==============\ x QUAL_ _l T Y FIR $T f=====================g x CONSTRUCTICN WOR? GRDER NC 72072078000 x e nnn0? I r, I N A :. x n n ;
'E x
x *- n RESPONSIDLE CRG. - DF2 TECMTEL PRCJECT FCRCES U? x
- PRC ECT CODE N/A
- WCRX TYPF C" x n -
N x ECUIPMENT ID- SA1415MTO55 IPRIORITY- 4 Sun !QA/QC W~TNESS/NCLD REQD~ NX
****n**-*******************HWM***************Hu****************************
QYT. *L'23 c e e c- - < EQUIPMENT FUNCTIONAL DESCRIPTIOi-PPIMARY PL.T MAKE UP STORAGE TX supptamfr
~~
EU M- P SC- 290 QUALITY CLASS 3 fyy.c DESCRIPTION: REVISION p PERFORM SURVEY OF TANK FOR ENGINEERING TO ALLOU UPGRt f" 0F :-ANK TO gygg ----
ROVIDE SCURCE OF MANE -UP WATER TG THE CCU SYSTEM. AL .. nEr,sCKEnENis W g
'ERTORMED ON 011TSIDE OF TANK , WORK SCOPE INCLUDES SUg Otflicipp -T g rg. DE ,
x * * *
- u x x.* x x x**2 x' REQUEST DATA 2 2
- u
- w u *
- x *
- x *.x 2 <
DCP/FCN - 2/3-6742.0T
.fr " - A SU SYSTEM MEA SEIS 2 CCNST. CODE (API
- NO 407-03 ) 650 IST -
N ENVIRN QUAL -- N SECRTY N FP - N HVAC - N t..Ct.,ATION: AREA - RD ROOM 127D ELEY OG7 CCLUMN N/A NPRD "
/
EQUESTING DEPARTMENT - BF2 BECHTEL PROJECT FORCES U2 3.EQUESTOR NAhE GAIKOWSKI, TOM PAX C7202
'EMARKS SCC-PERFORM SURVEY ON T056 FITST
- ax<**K
- x x x * * *
- REQUIREMENTJ: .x*uu**K ****K x**xx LCOAR REQD? - N NO. - N/A PLANT MODE REQD - A' A EDMR REQD? - N NO. - N/A . MOEE RESTRAINT - G UORK AUTH REQD? - N NO, - -N/A EFFECT ON UNIT N WORK AUTM. TYPE - N STARTUP TESTS REQ'D ON THIII CWO? - N ASME CODE WORK? -- N NO. -
N/A SEPARATION CRITERIA? - N CWC TO DISPOSITION NCR? - N NO. - N/A EFFLUENT ENGINEER REQD? - N TEMPORARY MOD.? - N NO. - N/A FIF:E PROT , ADMIN. REQD? - N WELD /I: URN FERMIT REQD? - N NO. - N/A SECURITY REQD? - N R.E.P . REQD? - Y STARTUP/ ENGINEERING REQD? -V CREACUS DREACH? - N FME REQUIRMENTS? N PFC/FCE REQD? N NO. - N/A xx*************I
- SCHEDULING * * * * * * * *
- K K * ***X x
?CHEDULED START DATE - 09/20/?2 TIME - 37:00:00 SCHEDULED COMP DATE 10/23/?2 TIM 7 18:00:00
.i *
- PLANNED UORK UINDOW n
- n * ~ * * *
- EQUIPMENT AVAILABLE UIUDOU * * *
' ROM DATE - 00/00/00 TIME - 00:00:00
- FROM DATE - 00/06/00
'3 DATE - 03/00/00 TIME - 00:M:00
- TO DATE - 00/00/00 COPY FOR YOUR INFORMAT10N i
CUO- ?2092070000 xnH 0 R I 'G r N A !. n n n pagg .. xx****4 *x*x**** SAFETY EVALUATION *a**x*
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xuu2 x2 aa .c L SIGNATURE APPi'0VALS (SEE UORK PLAN FOR CSE REQl!IREMENTS) IIZANT FE REVT.EU: GAIK0WSKI, T. DATE: 7/25/72 SCE NCE REVIEW: G. VECHINSKI DATE- ?/P.5/72 CSE U/D REQUIRED: NC
'.'NITIAL W/D COMP- NCE N/A .. .. DATE (H-7 . L'I. J
- FINAL U/D COMP NCE.......N/A.. . . . . . . . DATE .... . . . . -
nnnnn nn nnnuw n n n n n WORK PLAN n u u nn t CALCiNG d'IN M F u f fMUINGS/ REFERENCES : 4 !/4 BY- - DATE ~
, CONSTRUCTION SAFETY EVALUATION '.CSE). --
A. THERE ARE NO SAFETY RELATED ITEMS BEING MODIFIEl. D ., THERE ARE NO UNIQUE CONSTRUCTION ACTI'.!ITIES. C. PROTECTIVE MEASURES ARE REQUIRED. D. REVIEW AND IMPLEMENT IHE CSE PRECAUTIONS AS FOLLOWS:
- 1. NOTIFY NCE PRIOR TO STARTING WORK.
- 3. ODTAIN THE APPROPRIATE WORK AUTHORIZATION / APPROVAL.
TAILBOARD ALL WORK TO INSURE PERSONNEL FAMILIARIZATION WITH APPLICADLE SAF'ETY, AND HOUSEKEEPING PRECAUTIONS / REQUIREMENTS A. TAILBOARD ALL WORK'TO INSURE PERSONNEL FAMILIARIZATION WITH e APPLICADLE PROCEDURAL AND DESIGN REQUIREMENTS.
- 5. MINIMIZE THE AMOUNT OF TOOLS AND MATERIALS IN THE WORK AREA. -
/, , ALL LADDERS, OTHER THAN SHORT STEP i. ADDERS, ARE REQUIRED TO BE' 7 TIED DOWN TOP AND BOTTOM OR MONITORED WHILE I:EING USED.
PERSONNEL WILL IN NO WAY OPERATE, CI< IN ANY WAY DISTURB ANY WIRES. INSTRUMENT TUDING, OR SWITCHES. ( 3, DO NOT BLOCK VISUAL AND/OR PHYSICAL ACCESS TO EQUIPMENT WHILE UORK ACTIVITIES ARE IN PROGRESS 7 THE NUMBER OF PERSONNEL UILL DE KEPT TO THE MINIMUM PRACTICAL IN THE WORK AREA. WHILE IN OVERHEAD.
- 10. ANY EQUIPMENT THAT CANNOT DE SECURED, WILL DE' REMOVED DEFORE
- .EAVING THE AREA FOR ANY REASON.
ii. ALL WOOD USED MUST BE FIRE RESISTANT. 12 FOLLOW ANY ADDITIONAL PRECAUTIONS AS LISTED IN THE WORK PLAN. . II. TAILDOARD INSTRUC~ IONS: 5 J 300 i
- 1. RW 9 RM A INITIAL BRIEF1NG WIT' ,
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. ATE ./@M.l FOREMAN.(. .
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PERFCRMED DY. ... . _ ... . .... . ... .. DA T E ..3. /2#NS.7. l
.50 2.O VERIFY REP REQUIREMENTS IN PLACE.
PERPORMED BY _ y /vf) . D A TE A?/.).. /9 > 3
ERFORM SUN:VEY OF TANK 055 AS REQUESTED DY NEDO ENGINEERING.
COPY FOR YOUR INFORMATION
':UO- ?2092070000 xun0RIGINALn n x-p p g ,, . ,
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- xxxvx*xxaxx x x ATTACH SURVEY RESULTS O THIS CRO. II PAINT REMOVAL IS REQUIRED FOR LOCATING / ESTABLISHING DENCHMARKS, CrM*ACT HP RIt t TO REMOVA! .
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- 303cD2--
PERFORMED BY _. .. DATE ,1,O / 3, /.C)'?- - ., 5.0 TOUCH UP PAINT AS REQUIRED. N/A IF NOT RECUIRED. ATTACH INSPECTION REPORTS AS REQUIRED. TC55 PERFORMED LY..... Md......
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NCE VERIFIED DY .
- . . DATE /9./ /d/ D
-' 3 *!ERITY UORK COMPLETE AND WORK AREA CLEAN.
s ,. sp2., PERFCRMED BY....x s . s D ATE : N.. ../t.3 M L i' FINAL INSTRUCTIONJ' 1, i REVIEW THE CWO FOR COMPLETION OF REQUIRED SIGNATURET. CRAFT ID NO.'S, ' DATES AND DATA.
- 2. RETURN THE CUO UORK PACKAGE TO THE C00" ~.'NT P..-OR INAL 4
.REVIEU.
FINAL INfTRUCTIONS PERFORMED BY l
. . . . . . . aATE:@./.!h/$ L-x**4 x
- x * * * * * * *
- x PLANNING APPROVALS x x * * * *
- x
- x R X X X DY . DATE TIME WORK PLANNED GAIK0WSKI, TOM 07/25/? 10:46:37 1
UORK PLANNED REVIEW l VECHINSKI. GJ 09/25/92 13:50:10 ! ENGINEERING REVIEW SANLUIS, F 07/25/9? i4:36:5?. Q.A. REVIEW ENSMINGER, MIKE 00/28/?2 07:10:56 ^ E.C. REVIEW ELMORE, J 0?/28/72 OT:16:i1 WORK SCHEDULED GAIK0WSKI, TOM 0?/20/92 07:23:16 4: * *.x * * *
- x.* *
- a a K a PROCEDURE LIST * * * * * * * * *'2 * **X X X i -
PROCEDURE ID. -- IUP-108
- REVISION - 000 TCN - 000 7E~CRIPTION - FIELD CAULKING PAINTING AND SEALANTS 2 - PROCEDURE ID.
'bM N-S0123-XXIX-2.14
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- NES&L DEPARTMENT l
l CALCULATION SHEET = n NO. ,A. ,, ccnc0NytR$10h Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccn No. CCN - T subject see title sheet Sheet No. 135 4 REY - ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE 1RE DATE 0 WSHONG yow [gA/ 7/28/93 J. GAOR Id. 7/28/93 j / u ec-A ty 10/J/92 1 c. /7'r/m 4 i i 1 4 s a l a
- APPENDIX E 1
i i i ESTIMATION OF 95TH PERCENTILE FLAW LENGTH i, BY STATISTICAL ANALYSIS i i 4 1 4 ? l l 1 l i i l l i l I l 1 i SCE 26.426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =n ,0 . . ,, CCN CONVER$!0N Praject or DCP/MMP SONGS 2 Calc No, M-OSC-280 CCN No. CCN - subject see title sheet Sheet No. 13 7 REV CRIGINATOR DATE 1RE DATE REV ORIGINATOR DATE !RE DATE O WSHONG YOW 7/28/93 J. GAOR 1 6. 7/28/93
/ U-6L-4k t L Y P#/f] 7 <. /#/J/C) i
- 1. PURPOSE l Appendix E performs a statistical analysis on the sample welding flaws taken by radiographic films from the Unit 2 Primary Plant Makeup Storage Tank weld seams l during the Cycle 7 refueling outage. The statistical analysis is the first phase of the
- two phase analyses to determine the acceptability of the welding defects for the I
structural integrity of the tank. The statistical analysis determines the 95th percentile defect length which bounds a 95% probability of the total flaw population j on the tank at a 95% confidence level. The calculated 95th percentile defect length ! j will be the basis in the phase two fracture analysis to demonstrate acceptability of ' , the weld defect with a high degree of reliability. Phase two analysis is contained l in Appendix F. ) j 2. RESULTS/ CONCLUSIONS From a total of 283 sample welding flaws ranging from 0.03125 inches to 4.875 inches, it was determined that the 95th percentile defect length is 1.625 inches. That is, there is a 95% chance that the flaw length in the total flaw population on the tank will be less than 1.625 inches at a 95% confidence level. SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ==,. ,A E ,, CCN CONVERSION Project or DCP/MMP SONGS 2 calc No. M-DSC-280 CCN NO. CCN - subject see title sheet Sheet No. O REV ORIGINATOR DATE IRE DATE REV ORIGlWATOR DATE IRE DATE 1 WsHONG yow /g 8/20/93 J. GAOR b/, , 8/23/93 r
- 3. ANALYSIS (1) Samole Data During the Unit 2 Cycle 7 refueling outage, radiographic films were taken showing the welding flaws on the Primary Plant Makeup Storage Tank (MT056). These flaws were apparently the results of poor workmanship in the original construction welding of the tank. Attachments E.1 and E.2 show the film locations, flaw characteristics, and the sizes of flaws as obtained from QC (Reference 3). Based on the examination of the 60 films, produced by spot radiography,283 flaws were identified. Table E.1 lists all these 283 sample flaws in an ascending order of flaw length.
(2) Characteristics of Samole Data Among the 283 sample data, the range of the flaw length is from a minimum of 0.03125 inches to a maximum of 4.875 inches. The sample mean and standard deviation are calculated as n x = I x, /n = 103.06/283 = 0.364 i=1 l s = [ I (x -i x)2 / (n-1) ]u2 = 0.547 i=1 l l SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::r s .o. . ,, CCN CONVERSION Project or DCP/MP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - . subject see title sheet Sheet No. Ub REY ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O 7/28/93 J.GAORff, 7/28/93 W$HONG YOW Q
/ u - c<-w Ly ' M/U P6. /Mfo Figure E.2 shows the probabiftty distribution curve of the sample data, it can be seen that the probability distribution function does not have a normal or near-normal distribution. In fact, the probability distribution of the sample data fails to pass the goodness-of-fit tests for normal distribution, log-normal distribution, and the second-order Erlang distribution functions. Therefore,instead of pursuing an extensive mathematical derivation to establish theoretical confidence intervals, it is necessary to pursue an alternative procedure using the theory of order statistics for a non-parametric testing as discussed in next section.
(3) Non-Parametric Confidence Intervals A. Minimum Sample Size The minimum sample size required to perform a non-parametric test is dependent on the required probability of the population and the level of confidence. According to Reference (1), the minimum sample size to ensure with 95% confidence that 95% of the population will be less than a certain sample flaw length is 93. The sample size of 283 used in this study is much more than the smallest sample size required to produce the specified probability at the level of confidence desired. B. Estimation of Flaw Lenoth for 95/95 Probability and Confidence Level The theory of order statistics with binominal test is used to determine the upper bound of the flaw length which will envelop 95% of the flaw population on the tank SCE 26-426 NEW 4/90
NES&L DEPARTMENT j CALCULATION SHEET =n NC. ,m 0, i CCN CONVER5!0N Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - subject see title sheet Sheet No. 40 l CEV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE j 1 WSHONG YOW 8/20/93 J.GAOR((,, 8/23/93 1 l l l with 95% confidence level. Table E.1 shows the 283 sample observations in the ascending order. 1 l Let ! X, s X2 . . ......s X, s ...s X n i 1
- represent the ordered sample, where X's are the observed flaw lengths and n = )
283. According to Reference (2), the upper bound flaw length X, which has a 95% confidence level for the 95% probability of the total flaw population being less than X,is determined as 1 s = np + w osqrt[np(1-p)] ]
= 283
- 0.95 + 1.645
- sqrt(283*0.95*0.05)
= 274.9 I i
1 where p is the specified probability, and a is the desired confidence level. w, is j the one-tailed 95th percentile of a standardized normal random variable. The value + for w, is available from the standard normal distribution table in any statistical handbook. By rounding s upward to the next higher integer, we obtain s = 275. ! From Table E.1, i X27s = 1.625 inches. Therefore, from the 283 sample observations, we determine with 95% confidenca that 95% of the total flaw popu;ation will have flaw lengths less than 1.625 inches. SCE 26-426 NEW 4/90
l NES&L DEPARTMENT l CALCULATION SHEET ::r n ,. ,A E ,, l CCN CONVER$10N Project or DCP/letP SONGS 2 Calc No. M-OSC-280 CCN No. CCN - subject see title sheet Sheet No. O4I REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O W$HONG YOWg ' 7/28/93 J.GAOR((, 7/28/93 l W ~ Eu-hu-t t.V ' lofs/q) 9 c. to/Qqy 1
- 4. REFERENCES (1) G.M., Hesson, W.C. Cliff, and D.L Stevens, "A Mathematical Model for Assessing the Uncertainties of Instrumentation Measurements for Power and Flow of PWR Reactors," NUREG/CR-3659, PNL-4973,1985. !
l l (2) W.J., Conover, Practical Noncarametric Statistics, John Wiley & Sons, Inc. ' l (3) SA-1415-MT-056, " Summary Reports and NDE Reports" ) l l 1 l l 1 1 SCE 26-426 NEW 4/90
1 CALCU*LAYid^ A"" SHEET := 6. . ,, ,, Project or DCP/MP SONGS 2 Calc No, CCN CONVERSION M-DSC-280 ccN No. CCN - subject see title sheet Sheet No. WL REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE O WSHONG YOWh4f7/28/93 J. CAOR f(, , 7/28/93 l l00f[] pg, M *EL~ t%klLY' lf[f$) l TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 Sample No x x2 1 0.03125 0.00098 2 0.03125 0.00098 3 0.03125 0.00098 4 0.03125 0.00098 5 0.03125 0.00098 6 0.06250 0.00391 7 0.06250 0.00391 8 0.06250 0.00391 9 0.06250 0.00391 l 10 0.06250 0.00391 11 0.06250 0.00391 12 0.06250 0.00391 13 0.06250 0.00391 14 0.06250 0.00391 15 0.06250 0.00391 16 0.06250 0.00391 17 0.06250 0.00391 18 0.06250 0.00391 19 0.06250 0.00391 20 0.06250 0.00391 21 0.06250 0.00391 22 0.06250 0.00391 23 0.06250 0.00391 24 0.06250 0.00391 25 0.06250 0.00391 26 0.06250 0.00391 27 0.06250 0.00391 28 0.09375 0.00879 29 0.09375 0.00879 30 0.09375 0.00879 31 0.09375 0.00879 32 0.09375 0.00879 33 0.09375 0.00879 SCE 26-426 NEW 4/90 l
NES&L DEPARTMENT CALCULATION SHEET :: mo. ,, ,, Project or DCP/MMP SONGS 2 Calc No. M-0SC-280 $$ EcE-subject see title sheet sheet No. W3 REV OR]GINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O WSHONG YOW 7/28/93 J.CA0Rf(,, 7/28/93
/ N-EL-Ak.iU/ /0/f/91 TC . /r/43 TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued)
Sample No x x2 34 0.09375 0.00879 35 0.09375 0.00879 , 36 0.09375 0.00879 37 0.09375 0.00879 38 0.09375 0.00879 39 0.09375 0.00879 40 0.09375 0.00879 41 0.09375 0.00879 42 0.09375 0.00879 43 0.09375 0.00879 44 0.09375 0.00879 45 0.09375 0.00879 46 0.09375 0.00879 47 0.09375 0.00879 48 0.09375 0.00879 49 0.09375 0.00879 50 0.09375 0.00879 I 51 0.09375 0.00879 52 0.09375 0.00879 3 53 0.09375 0.00879 54 0.09375 0.00879 55 0.09375 0.00879 56 0.12500 0.01563 57 0.12500 0.01563 58 0.12500 0.01563 59 0.12500 0.01563 t 60 0.12500 0.01563 61 0.12500 0.01563 62 0.12500 0.01563 63 0.12500 0.01563 64 0.12500 0.01563
; 65 0.12500 0.01563
- 66 0.12500 0.01563 SCE 26 426 NEW 4/90
NES&L DEPARTMENT
- CALCULATION SHEET =L. , , , ,,
CCN CONVERSION Project or DCP/MP SONGS 2 Cale No. M-DSC-280 ccN No. CCN - subject see title sheet Sheet No. NY REV ORIGINATOR CATE IRE DATE REV ORIGINATOR DATE IRE DATE O 7/28/93 J. GAOR ((,. 7/28/93 WSHONG YOW /'LP/ , / v - dL -/M.i t. f lo///g 9, /%f93 i I TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) Sample No x x2 ' 67 0.12500 0.01563 68 0.12500 0.01563 69 0.12500 0.01563 70 0.12500 0.01563 71 0.12500 0.01563 1 72 0.12500 0.01563 l 1 73 0.12500 0.01563 . 74 0.12500 0.01563 1 75 0.12500 0.01563 l i 76 0.12500 0.01563 ' 77 0.12500 0.01563 78 0.12500 0.01563 79 0.12500 0.01563 l 80 0.12500 0.01563 I 81 0.12500 0.01563 . 82 0.12500 0.01563 1
- 83 0.12500 0.01563 '
84 0.12500 0.01563 I 85 0.12500 0.01563 4 86 0.12500 0.01563 i 87 0.12500 0.01563 1 88 0.12500 0.01563 i 89 0.12500 0.01563 90 0.12500 0.01563 91 0.12500 0.01563 92 0.12500 0.01563 93 0.12500 0.01563 94 0.12500 0.01563 l
. 95 0.12500 0.01563 96 0.12500 0.01563 l 3 97 0.12500 0.01563 98 0.12500 0.01563 99 0.12500 0.01563 l
l l SCE 26-426 NEW 4/90 ' i
l NES&L DEPARTMENT l CALCULATION SHEET ;;;,;L. ,A,E ,, Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 cc$ ccE- l subject see title sheet Sheet No. N[ REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE I IRE DATE D W$HONG YOW g4f 7/28/93 J. GAOR k 7/28/93 )
/ u-ec-9%d 10/1) 91 76 '7dn I
TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) Sample No x x2 100 0.12500 0.01563 I 101 0.15625 0.02441 l 102 0.15625 0.02441 ! 103 0.15625 0.02441 ! 104 0.15625 0.02441 105 0.15625 0.02441 l 106 0.15625 0.02441 3 107 0.15625 0.02441 1 108 0.15625 0.02441 109 0.15625 0.02441 110 0.15625 0.02441 i 111 0.15625 0.02441 112 0.15625 0.02441 ! 113 0.15625 0.02441 114 0.18700 0.03497 l 115 0.18750 0.03516 116 0.18750 0.03516 117 0.18750 0.03516 118 0.18750 0.03516 119 0.18750 0.03516 120 0.18750 0.03516 121 0.18750 0.03516 122 0.18750 0.03516 ! 123 0.18750 0.03516 124 0.18750 0.03EiS I 125 0.18750 0.03516 l 126 0.18750 0.03516 l 127 0.18750 0.03516 l 128 0.18750 0.03516 129 0.18750 0.03516 130 0.18750 0.03516 131 0.18750 0.03516 132 0.18750 0.03516 l SCE 26-426 NEW 4/90
)
NFS&L DEPARTMENT
- CALCULATION SHEET = n No. . ,, !
CCN CONVER$10N Preject or DCP/M4P SONGS 2 Calc No. M-DSC-280 { CCN No. CCN - I subject see title sheet Sheet No. Nb REV ORIGINATOR 0 ATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 0 7/28/93 J. GAOR Q , 7/28/93 WUSHONG YOW g y l N-GL-AKILY 10/1/qf y6 "Ygp
~
1 j TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) Sample No x x2 133 0.18750 0.03516
- 134 0.18750 0.03516
- 135 0.18750 0.03516 136 0.18750 0.03516
) 137 0.18750 0.03516 . 138 0.18750 0.03516 l 139 0.18750 0.03516 j 140 0.18750 0.03516 141 0.18750 0.03516 142 0.18750 0.03516 l! 143 0.18750 0.03516 i j 144 0.18750 0.03516 I i 145 0.18750 0.03516 I l 146 0.21875 0.04785 l 147 0.21875 0.04785 1 148 0.21875 0.04785 i 1 l 149 0.21875 0.04785 j i 150 0.21875 0.04785 i i 151 0.21875 0.04785 l ! 152 0.25000 0.06250 j 153 0.25000 0.06250 154 0.25000 0.06250 155 0.25000 0.06250 { 156 0.25000 0.06250 157 0.25000 0.06250 158 0.25000 0.06250 159 0.25000 0.06250 160 0.25000 0.06250 161 0.25000 0.06250 162 0.25000 0.06250
' 63 0.25000 0.06250 164 0.25000 0.06250 165 0.25000 0.06250 SCE 26-426 NEW 4/90 l
l
NES&L DEPARTMENT
' CALCULATION SHEET ;;; n ,.. ,, ,,
Project or DCP/MMP SONGS 2 Calc No. M-OSC-280 cc$k$ccE-subject see title sheet Sheet No. TY7 REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE O WUSHONG YOW g 7/28/93 J.GAORf.6 7/28/93 l 9 - EL- A V-4 LY' lb)Slqf FQ;, /o/sfg; TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) Sample No x x 166 0.25000 0.06250 167 0.25000 0.06250 168 0.25000 0.06250 169 0.25000 0.06250 170 0.25000 0.06250 171 0.25000 0.06250 172 0.25000 0.06250 173 0.25000 0.06250 174 0.25000 0.06250 175 0.25000 0.06250 176 0.25000 0.06250 177 0.25000 0.06250 178 0.25000 0.06250 179 0.25000 0.06250 180 0.25000 0.06250 l 181 0.25000 0.06250 182 0.25000 0.06250 183 0.25000 0.06250 184 0.25000 0.06250 185 0.25000 0.06250 186 0.25000 0.06250 187 0.25000 0.06250 188 0.25000 0.06250 189 0.25000 0.06250 190 0.25000 0.06250 191 0.25000 0.06250 192 0.28125 0.07910 193 0.28125 0.07910 194 0.28125 0.07910 195 0.31200 0.09734 196 0.31250 0.09766 197 0.31250 0.09766 198 0.31250 0.09766 SCE 26-426 NEW 4/90
1 CALCOLN db"dHEET g r n ,0. ,A,E ,, 4 CLN CONVERSION l Project or DCP/MtP SONGS 2 Calc No. H-DSC-280 ccN so. CCN - l l l subject see title sheet Sheet No. TY2 ' ,' REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE l O WSHONG YOW d'y 7/28/93 J. GAOR j_[, , 7/28/93
/ u-eL-AVlL.f l0lS{ff f[, /ffq$
i l 4 TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) l Sample No x x2 { 199 0.31250 0.09766 200 0.31250 0.09766 201 0.31250 0.09766 ) 202 0.31250 0.09766 1 203 0.31250 0.09766 ) 204 0.31250 0.09766 205 0.31250 0.09766 206 0.31250 0.09766
- 207 0.31250 0.09766
- 208 0.31250 0.09766
! 209 0.31250 0.09766 210 0.31250 0.09766 2 211 0.37500 0.14063 212 0.37500 0.14063 l 213 0.37500 0.14063
- 214 0.37500 0.14063 215 0.37500 0.14063 j 216 0.37500 0.14063
- 217 0.37500 0.14063 I
. 218 0.37500 0.14063 l l 219 0.37500 0.14063
- 220 0.37500 0.14063
! 221 0.37500 0.14063 222 0.37500 0.14063
- 223 0.37500 0.14063 224 0.37500 0.14063 225 0.43750 0.19141
- 226 0.43750 0.19141 4 227 0.43750 0.19141 I
228 0.43750 0.19141 229 0.43750 0.19141 j 230 0.46700 0.21809 ! 231 0.50000 0.25000 SCE 26-426 NEW 4/90
- l NES&L DEPARTMENT j CALCULATION SHEET ;;rn , . ,, ,,
CCN CONVERSION Project or DCP/M4P SONGS 2 Calc No. M-DSC-280 cCN No. CCN - subject see title sheet Sheet No. Ni REV OR10lMATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE O WSHONG YOW g 7/28/93 J. GAOR f,4 , 7/28/93 I tr EL-0ktI Y NU5/9) p c, . /W/n TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) I Sample No x x I 232 0.50000 0.25000 j 233 0.50000 0.25000 1 234 0.50000 0.25000 } 235 0.50000 0.25000 l 1 236 0.50000 0.25000 l i 237 0.50000 0.25000 l 238 0.50000 0.25000 4 239 0.50000 0.25000 240 0.50000 0.25000 l l 241 0.50000 0.25000 242 0.50000 0.25000 l 243 0.62500 0.39063 i 244 0.62500 0.39063 ) 245 0.62500 0.39063 246 0.62500 0.39063 247 0.62500 0.39063 ! 248 0.62500 0.39063
- 249 0.62500 0.39063 250 0.68750 0.47266 l 251 0.75000 0.56250
! 252 0.75000 0.56250 253 0.75000 0.56250 254 0.75000 0.56250 '. 255 0.87500 0.76563 256 0.87500 0.76563
- 257 0.87500 0.76563 258 0.87500 0.76563
{' 259 0.87500 0.76563 260 0.93750 0.87891 261 1.00000 1.00000 262 1.00000 1.00000 J 263 1.00000 1.00000 264 1.00000 1.00000 i SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :n No. ,A E o, CCN CONVERSION Project or DCP/letP SONGS 2 Calc No, M-DSC-280 CCN NO. CCN - subject see title sheet sheet'No. TO REV ORIGINATOR DATE !RE DATE REV ORIG!kATOR DATE 1RE DATE 0 WU$HONG YW/pg 7/28/M J. GACR jg. 7/28/M
/
" - E L-A k n Q ' Mis /7) 9g , to/374y TABLE E.1 RADIOGRAPHIC FILM FLAWS FOR MT-056 (continued) ;
Sample No x x l 265 1.00000 1.00000 266 1.00000 1.00000 267 1.03125 1.06348 268 1.09375 1.19629 269 1.12500 1.26563 270 1.12500 1.26563 271 1.18750 1.41016 272 1.25000 1.56250 273 1.25000 1.56250 274 1.37500 1.89063
+ 275 1.62500 2.64063 276 1.87500 3.51563 277 2.12500 4.51563 l 278 2.50000 6.25000 279 2.50000 6.25000 280 2.50000 6.25000 l 281 3.00000 9.00000 l 282 4.37500 19.14063 283 4.87500 23.76563 1
SUM = 103.05975 121.92169 1 l l l l l l l l L SCE 26-426 NEW 4/90 l l
a - r 4 FIGURE E.1 TANK T-056 RADIOGRAPHY MAP co
'o r 1 &
J4 ROW 4 N 3 .$ t' r 'f ,_ y 7 VErfT. T n +# I h 'l f 5 JOINTS
' 40" 40-1o}i so- t 20"+ 40 #t 20"t O HORII.
t* .a ' . -> a.y " *E { EEj6+ 'EE y ,EZ j EE *EE R0W3 uH : 3 x , j; 3 7 venr. AT U t' t ', 1 5 7 JOINTS T
, , #y d , 40" 26 4s ,
, m.
40"
.,,2 to f
92 30 4 m 3 4 3 H O RIZ. oI 9.s 2 ' i A r r R0W2 NO 5 I t
-L ?'
ll 7 VERT 10"
- I g " 3 HO II de *
+ +-
+
54"** 4~60"4 - -
+4 4e 48-F F ROW 1 E9 7 VcRT. %5 Y 1~
y < j 4f 4X l_ 4 ! 4L ' 4s O JOINTS . 45- 40" 25 35' 45" 2d"; 30" g
." 7 HORII. m
> Y\ g f
2 3 4 5 6 7 2 1
'g ,
%)
ACCE P TA BL L s O A Y BASE oom. m ,! $ g ,i l % '3L J w l%
~
5' bl nt
,. %s
FIGURE E.2 PROBABILITY DISTRIBUTION 0.3 . 0.25-- 0.2 c a 5 g 0.15 8 m 0.1 0.05 1 l5 0 ^^^^
^'
^ ^
^ &
o 0:5 i 1.s i 2.s 6 s's
. 4 4.s s ?
FLAW LENGTH, INCHES ll ;l g ' (-t R eie 5I 9 C
NES&L DEPARTMENT i CALCULATION SHEET =:L. ,A E ,, CCM CONVER$10N Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - q subject see title sheet Sheet No. DE) Rev ORIGruATOR DATE 1RE DATE REV ORIGINATOR DATE 1RE DATE WSHONG YOWM/ 7/28/93 O J. GAOR f.(3, 7/28/93 l l N- 5 -Ak t LY 10H/9] J' 6. '/* r/99 \ r 1 l 1 ATTACHMENT E.1 i
- RADIOGRAPHIC FILM RESULTS FOR MT-056 (l) 1 l
1
- l i i i
a 1 i
- l 1
4 k l i b i j SCE 26-426 NEW 4/90
ChLC NO. N' 'O ^ REV' ~ M:]q=^ ' SUPPLEMENT SHT D ORIGINATOP NM DAT*7k8/N lps N- ruywDb T , [224] From: BRUCE HAMMER at SOUTH 2 7/19/93 3:42PM (14'30 bytes: 33 in) Tot WUSHONG YOW at NESL5
Subject:
RESULTS OF RADIOGRAPHS FOR T056
Forwarded ----------------------------------
Frem: JOE TRANER at SOUTH 2 6/25/93 7:42PM (1240 bytes: 33 in) To: RIYAD QASHU at NESL5, JUN GAOR at NESL2, VINCENT BARONE at NESL4, DON STONECIPHER, BRUCE HAMMER, DANNY COLE, GERALD SCHMIDT, SAM DEATON, GREG VECHINSKI at SOUTH, ED MCNEILL at SOUTH cca JOE TRANER
Subject:
RESULTS OF RADIOGRAPHS FOR T056
Message Contents -------------------------------
GENTLEMEN; - THE FOLLOWING ARE THE RESULTS OF THE FIRST 11 LOCATIONS. R2V3 ACCEPTABLE G2-3 REJECT-INSUFICIENT FUSION (I.F.) 2.5" AND 4.875" LENGTH. R4J8 REJECT-SLAG INCLUSIONS (S.I.) .375",.5", .25". I.F. .250" l R2J5 REJECT-UNDERCUT (U) .312" I.F. 3" R4J4 REJECT- I.F. .187" U. .5" ' R2V8 REJECT- I.F. .375" R3V5 REJECT- I.F. 4.375" R3V-l REJECT S.I. .75" ** ! R3J6 ACCEPTABLE G1-2 ACCEPTABLE t&3 ; 1 R1J7 REJECT- S.I. .4 " AGREGATE LENGTH PLEASE CONTACT QCNDE 87817 FOR ANY QUESTIONS. THANK YOU JOE TRANER I I 1 l
NES&L DEPARTMENT CALCULATION SHEET ::: n ,.. ,A , o, CCN CONVERSION Project or DCP/MHP SONGS 2 Calc No. H-DSC-280 ccn no ccN - subject see title sheet , sheet No. M1 REV ORIGINATOR DATE !RE DATE REY ORIGINATOR CATE !RE DATE O W$HONG YOW [dy7/28/93 J. CAOR J.& 7/28/93 I v Gu -tm L 1 lolyq) f4, !%% , ATTACHMENT E.2 RADIOGRAPHIC FILM RESULTS FOR MT-056 (11) i l l 4 i SCE 26 426 NEW 4/90
CA1.C NO. H'o c~ ZY# Q8 lc) Sle v SUPPLEMENT SHT j OfuGINATOR N DAT8 I! ' i
,, 74 w%r/n ;
j [234] Frem: BRUCE HAMMER at SOUTH 2 7/27/93 10:39AM (18761 bytes: i i To: RIYAD QASHU at NESLS, WUSHONG YOW at NESL5 354 in) cc: BRUCE HAMMER, DALE CRANDALL -
Subject:
TANK MT056 RADIOGRAPHIC FII.M REVIEW FOR UPGRADE Rylad, Message Contents ------------------------------- The changes will be in this color. e The reader sheets that have this information on them is being put into the pony mail today. i I Bruce i Ryiad, The only areas that I see that could be correct would be the radiographs identified. which have only undercut or concavity items These two items are surface indications but by the
- Code film. we have to reject based on the abrupt density change on the i radiographic 1y whenbeprepared.
This would four additional film that could be accepted I I I believe If you have that this any is what you questions were please asking to have presented. call. i, Bruce Hammer l
- l a',
- FLAW
SUMMARY
OF REJECTABLE FILM LOCATIONS ON MT 056.* This report only covers the area of rejectable indications. Film Location: Acc/Rej: . , Flav Characterization: Size of Flaw: R1V-i , A R1V-2 R SLAG INCLUSION @ 5/16 x 7/32" INCOMPLETE FUSION 3/16 X'1/16" R1V-3 R UNDERCUT 5/16 x 1/32" SLAG LINE 1/32 x 3/4" SLAG. INCLUSION 3/8 x 3/32" INCOMPLETE FUSION 3/16 x 1/32" R1V-4 R SLAG LINE 1/32 x 5/8" R1V-5 A
*** R1V-6 R INCOMPLETE FUSION 5/16 x 1/32" 1/16 x 3/16"
@ 1/16 x 1/64" 1/32 x 1/8" ADD THIS ONE UNDERCUT 1/32 x 1/4" 3/8 X 1/32 e
1
~
CALC NO. _ ge 79 3 l summant mer m ! omomAw N'1 rus=7/2J/13 T4 ' nA7bN
^
1 i 1
; R1V-7 R UNDERCUT 1/4 x 1/16"
! R1J-1 R UNDERCUT 1/4 x 1/32" 1/2 x 1/16" CONCAVITY (SHARP) 1/4 x 1/32" s 1/4 x 1/32" l
*** R13-2A R INCOMPLETE FUSION I
ADDED THE ALPHA DESIGNATER 3/16" ! h 3/16" i 7/16" i
.3/16" l i
*** R1J-2 R SLAG LINE }
DELETED THE 'A' FROM TF.IS ONE, IT IS THE ONE ABOVE 3/16 x 1/32" l 3/16 x 1/32" ! DELETE THIS INDICATION FROM THE LIST 3/16 x 1/32" l 2,'10 :. 1,'10 " i INCOMPLETE FUSION 1/8 X 1/16 3/32 X 1/16 1 R1J-3 R INCOMPLETE FUSION i 1/8 X 1/32"
- 1/16 X 1/32" !
i h 1/16 X 1/32" , 5/32 X 1/32" ! 1/8 X 1/32" l 1/2 X 1/32" l CONCAVITY (SHARP) 1" X 1/16" j
*** R1J-4 R
- INCOMPLETE FUSION 1/8 X 1/32" t
1/16 X 1/32" i l ADDED WIDTH MEASUREMENT 1/8 x 1/32" i 1 3/16" LengthX 1/16 *--- l 5/32 X 3/32" CRACK h 1/4" Length ', xxxR13-5 R UNDERCUT 1/4 X 1/16" 1/4 X 1/32" NEED TO BE 15/16 X 1/32 CONCAVITY (SHARP) 1/2 X 1/32" 15/16 X 1/32" 4 1/4 X 1/32" R1J-6 R CONCAVITY (SHARP) 1/4" Length 3/8" " " UNDERCUT 5/16 X 1/16" SLAG LINE 1/2 X 1/32"
- Ih 1/8 X 1/32" U
' 1/16 X 1/32" 3/32 X 1/32" INCOMPLETE FUSION 1/8 X 1/32" R1J-7 R INCOMPLETE FUSION 1 X 1/16"
_ , a --L. a -- - - - - = I M N, (4- D6C - 230 Mw n'4 tois/93 suPPLEuert sHT IN oaxunAron W oAw 7hfM3 . me f-4 mv IVlf*7 h 1/8 X 1/16" 3/16 X 1/32" e e a l l l 1 l l
m W, #- DSC - Lie g-- - n" tof s/ 9~2 SUPPUEMENT SHr M
. ORIGINATOR N4 OAW7!##/f3 in. T4 mphh3 G1-3 R INCOMPLETE FUSION 3/16 X 1/32" 1/8 X 1/64" 1/8 X 1/32" CONCAVITY (SHARP) h 1/4 X'1/32" 1 1/8 X 3/32" G1-4 R CONCAVITY (SHARP) 1 1/8 X 1/32" 7/8 X 1/32" 7/8 X 1/16" G1-5 R CRACK 5/32" Length G1-6 R CONCAVITY (SHARP) 5/8 X 1/32" G1-6X A G1-7 A *** R2-V2 R DELETE THIS LINE SLAG LINE 2/0 1/ 0 4 ADD THIS INFO INCOMPLETE FUSION 1/4 X 1/32 ADD THIS ADD THIS 1/8 X 1/64 }
ADD THIS 3/8 X 1/32 1 ADD THIS @3/32X1/32 1/4 X 1/16 ' ADD THIS ADD THIS 1/16 X 1/32 ADD THIS 5/16 X 1/16 ! 3/32 X 1/16 ADD THIS INFO SLAG INCLUSION 5/16 X 1/16 s R2-V4 A R2-V5 R SLAG LINE 20 3/16 X 1/16 1/16 X 1/32 R2-V6 A R2-V7 A i xxx R3-V2 R INCOMPLETE FUSION 20 l 3/32 X 1/16 5/32 X 1/32 1/8 X 1/64 7/32 X 1/64 3/8 X 1/64 29 1/4 X 1/16 3/16 X 1/32 5/32 X 3/32' 1/8 X 1/32 h 1/16 X 1/32 1/8 X 1/16 f 3/32 X 3/32 1 DELETE THIS ONE
?/22 1/15 i CRACK 3/16 3 s
~
CALC NO, - Ibl5 95 summer ., a o ORIGINATOR DAF tar 96- DAN xxxx R3-V6 R CHANGE TO 5/32" INCOMPLETE FUSION 5/23 - R3-V4 R INCOMPLETE FUSION 2 1/2 X 1/8 1/16 X 1/32 5/32 X 3/32 3/32 X 1/32 xxx R3-V3 R INCOMPLETE FUSION 3/16 X 1/32 DELETE THIS ONE 1/? Y 1/22 ADD THIS ONE 1" X 3/32 < CRACK 1/8 R3-V1 R SLAG INCLUSION (IN LINE) 1/8 X 3/32 1/8 X 1/16 3/32 X 1/16 CRACK 3/32, 1/16, 9/32 R3-J7 R INCOMPLETE FUSION 1 1/4 X1/32 3/32 X 1/32
@ 1/8 X 1/32 5/32 X 1/32 R3-J5 R UNDERCUT 1/4 X 1/32 ,
INCOMPLETE FUSION 7/16 X 1/64 , 7/16 X 1/16 l 3/16 X 1/32 !
' 30 1/8 X 1/64 l 3/16 X 1/64 '
3/32 X 1/64 R3-J6 R INCOMPLETE FUSION 29
- 1/4 X 1/32 3 20 3/32 X 1/32 1/8 X 1/32 3/16 X 1/32 3/32 X 1/64 3/16 X 1/64 1/8 X 1/64 I m, w ,nv i R3-J4 R UNDERCUT (ALIGNED) 3 0 1/8 X 1/32 '
INCOMPLETE FUSION 3/16 X 1/16 3/4 X 1/32 3/32 X 1/32 i GOUGE IN BASE MTL (GRIND SCAR) 5/8 X 5/32 m __
cAten. M-Dsc - ass ,*tg w.z
~
Icj:ln" SUPPLEMENT- ggr %d> I
. ONGWATOR N DAT*7/3883 IR'- DATE DN3 ,.'
R3-J3 R UNDERCUT 20 1/4 X 1/32 1 1/4 X 1/32 CRACK
/4, 1/8, 1/32
/8 CONCAVITY (SHARP) 2 1/2 X 1/32 2 1/8 X 1/32 3/4 X 1/32 1/4 X 1/32 INCOMPLETE FUSION 7/16 X 1/64 xxx R3-J2 R INCOMPLETE FUSION DELETE THIS ONE 7/32 X 1/32 DELETE THIS ONE 0/0 X 1/02 0/0 X 1/00 d 1/4 X 1/32 1/8 x 1/16 1/8 x 1/16 ADD THIS ADD THIS' 30 1/8 X 1/32 ADD THIS 5/16 X 1/32 * - -
20 3/16 X 1/32
\
CONCAVITY (SHARP) 1/4 X 1/16 GOUGE IN BASE MTL (GRIND SCAR) h 5/8 X 7/32 R3-J1 R CONCAVITY (SHARP) 3/8 X 1/32 ** SLAG LINE 5/16 X 1/32 ; G2-4 R CONCAVITY (SHARP) 1 5/8 X 1/16 5/8 X 1/16 G2-5 R INADEQUATE PENETRATION 1"
- 3/32 2 0 5/16 ,
xxxx G4-5 R j UNDERCUT (ALIGNED) 5/16 X 1/32 & 3/16 X 1/16 CHANGE ONE OF THE 1/4X1/16 TO 1/4 X 7/16 h 9/16 X 1/16 & 1/8 X 1/32 l ' 1/4 X S/16 & 1/4 X 1/16 & ; j
/16 X 1/32 & 5/32 X 1/32 &
3/16 X 1/32 3Qg CONCAVITY (SHARP) 3/16 X 3/32, 1 7/8 X 1/16,
- , 1 3/8 X 1/16, 1/4 X 1/16, 7/8 X 1/32 J
cal.C NO. bC ~ 2E# RE I SHT , f"oa, sumEMENT ORIGINATOR DAT8 2 IRF DA xxx R4-J1 R INCOMPLETE FUSION h 1/8 X 1/16, 7/32 X 1/32 3/32 X 1/16, 1/16 X 1/16,(go) 3/16 X 1/16, 1/8 X 1/32 CONCAVITY (SHARP) 1/2 X 1/16, 3/8 X 1/16 DELETE THE 1/8X1/16 1/3 X 1/10, 3/32 X 1/16 1/2 X 1/16, 5/16 X 1/16 7/8 X 1/16, 7/8 X 1/16 R4-J2 R UNDERCUT h 3/8 X 3/16 INCOMPLETE FUSION 1/4 X 1/32 CONCAVITY (SHARP) 1 X 1/32, 3/16 X 1/32 ARC STRIKE 7/16 X 1/4 xxxx R4-J4 R UNDERCUT' 3/8 X 1/32 INCOMPLETE FUSION 1/2 X 1/64, 3/4 X 1/64 1/2 X 1/64, 5/32 X 1/16 DELETE THIS LINE CONCAVITY (SHARP) 5/2 2 ! '2 2 SLAG INCLUSIONS h 5/8 X 3/16, 1/8 X 3/32 R4-J6 R UNDERCUT I 1/4 X 1/32, 1/4 X 1/16, ' 1/4 X 1/32, 1/4 X*1/32, j 1/4 X 1/16 INCOMPLETE FUSION 1/4 X 1/32, 5/32 X 1/32, ' 5/16 X 1/32 ' R4JJ7 R GRIND GOUGE [ 5/16 X 3/32 UNDERCUT 1/4 X 1/32 INCOMPLETE FUSION 1/4 X 1/32, 3/32 X 1/32, 3/16 X 1/32 CONCAVITY (SHARP) 1 X 1/32, 5/8 X 1/16, 3/8 X 1/16, 5/16 X 1/16
CALC NO. N'
~
0 REV
\ ct:fo,
~
SUPPLEMENT SHT ORIGINATOR DATE O ire ' DATF ! xxxx R4-V1 R INCOMPLETE FUSION 3/16 X 1/16, 3/32X1/32[W) 3/32 X 1/32, 5/32 X 1/16, 1 3/32 X 1/16, 5/32 X 1/16, 3/32 X 1/32, 1/16 X 1/32, 1/16 X 1/64, 3/32 X 1/32, j 1/8 X 1/64*, 3/8 X 1/16, pto) 9/32 X 1/16, 1/8 X 1/32, 1/8 X 1/16, 3/32 X 1/16, 1/2 X 1/16, 1/8 X 1/64, 5/8 X 1/16 ADD THIS ONE 1/8 X 1/32 O R4-V2 R INCOMPLETE FUSION 1/8 X 1/32, 3/16 X 1/8 (t#s) INADEQUATE PENETRATION 7/32 R4-V3 R INCOMPLETE FUSION 3/16 X 3/16, 1/8 X 3/32, 1/4 X 1/16, 1/16 X 1/32, ( 1/4 X 1/32 R4-V4 R INCOMPLETE FUSION 1/4 X 1/32, 3/32 X 1/32, 3/8 X 1/8, 1/8 X 1/32 (,tg R4-V5 R INCOMPLETE FUSION 1/16 X 1/32, 3/32 X 1/32, 1/16 X 1/32, 1/16 X 1/32 R4-V6 R INCOMPLETE FUSION 5/16 X 1/16, 1/4 X 1/8, 1/16 X 1/32, 1/8 X 1/32, 1/16 X 1/32, 5/32 X 3/32, (t6o) 1/4 X 1/64 R4-V7 R INCOMPLETE FUSION 3/16 X 1/64, 3/32 X 1/16, 1/16 X 1/32, 1/16 X 1/32, ' 9/32 X 1/16, 7/32 X 3/32, 3/16 X 3/32, 7/32 X 3/32 Q I 1 I
. l l
NES&L DEPARTMENT l l< CALCULATION SHEET grn , . ,A. ,, i l CCN CONVER5!0N Project or DCP/MHP SONGS 2 Calc No. M-DSC-280 cCN No. CCN - j subject see title sheet Sheet No. %b REV ORIGINATOR DATE IRE CATE
] REV ORIGINATOR DATE IRE DATE O R. cashu y 7/26/93 JunGaorT[f. 7/28/93 1
i
/ ti .E c-j;k t u y CU/*f] fg /rf()
i J, i i I 1 i APPENDIX F 1 l 1 l i l l i ) 1 i l r i i } i i i k i i i i SCE 26-426 NEW 4/90
1 1 i l NES&L DEPARTMENT CALCULATION SHEET = " n ,.. , A. ,, J CCN CONVERSION 1 Project or DCP/ HHP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - 2 Subject see title sheet Yo d Sheet No.
? REV ORIGINATOR DATE IRE DATE REV CRIGINATOR DATE IRE DATE O R. Qashu k 7/26/93 JunGaor[.y , 7/23/93 i l
1 h h-?'o uY-WI5/97 7-6 'Yr/gs I i 4 TABLE OF CONTENTS i 2 , 1 q l l
} PAGE
- 1. PURPOSE ........................................... 'k b
i 1 1
- 2. RESULTS/ CONCLUSIONS ............................... M> l l j i l I
- 3. ASSUMPTIONS ....................................... h 'i i.
t 4. DESIGN INPUT....................................... 07 0 i i i i m m ' )
- 5. METHODOLOGY ....................................... -t 1 f
I l 6. REFERENCES ........................................ 1~7 0 i i i l I 3 7. NOMENCLATURE ...................................... t)5 I I j 8. CALCULATIONS ...................................... 7"/
-ru ~
ATTACHMENTS TO APPENDIX F........... 78 i SCE 26-426 NEW 4/90 '! I
NES&L DEPARTMENT CALCULATION SHEET ==L. ,,, o, CCN CCNVERSION Project or DCP/MMP . SONGS 2 Calc No. M-DSC-280 CCN No. CCN - Subject see title sheet Sheet No. 7bb REV ORIGINATCR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O R. cashu Q 7/26/93 Jun Gaor k 7/28/93 l U EL-ik I L'l \cplyg Q, ofgp 1.0 PURPOSE / BACKGROUND: During a QA surveillance activities of the primary make up storage tank T-056 modifications, QA identified evidence of poor workmanship in the original construction welding of the tank. The poor workmanship was identified for example; as excessive weld reinforcement (greater than 3/32"), and undercut (greater than 1/32"). QA also reviewed the original 10 radiographs and found two unacceptable. The QA assessment was later confirmed by QC. Additional five radiographs were taken and found unacceptable by QC. It was evident at this point that continuing the radiography will continue to show same type of weld defects, and an evaluation must be developed to address the structural integrity of the tank with the weld defects. In order to address the weld defects, a plan was put to try to characterize statistically a bounding defect with high ! confidence. The number of radiographs wau increased to a total of ! 60, covering basically all of the tank shell weld seams. The results of the radiographs is used to perform a bounding fracture mechanics analysis to demonstrate acceptability of the welds with high reliability. i l The analysis is comprised of two phases. Phase one a statistical SCE 26-426 NEW 4/90
NES&L DEPARTMENT
- CALCULATION SHEET g i: n , . ,A, ,, ;
I CCN CONVERSION j Project or DCP/ HHP SONGS 2 cale No. M-OSC-280 CCN No. CCN - Subject See title sheet Sheet No. M REV CRIGINATOR DATE IRE DATE CRIGINATOR DATE IRE REVl DATE O R. Qashu Q 7/26/93 Jun Gaor 5 L. 7/28/93 l i I n.er-Au-y \ wis/93 p c. 8/rh5 l ; i l l analysis to try to calculate a reliability of at least 95% of a ! I l defect length not to exceed a given length, with 95% confidence , I j level. The bounding defect will be used in phase 2 conservative
- fracture analysis to show that the defect, simulated as a crack i
will be acceptable for the life of the tank. 4 j Phase 1 is addressed in appendix E, and phase 2 is addressed in this appendix. l 1 i i i 4 i SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;;r," L . ,Ax o, CCN CONVERSION Preject or DCP/ HHP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - Subject see title sheet Sheet No. A REY ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 R. Qashu 8/23/93 JunGaorff, 8/23/93 2.0 RESULTS/ CONCLUSIONS: The worst defect reported in appendix E was assumed to exist in the highest stress region of the tank shell, and oriented axially to maximize the stress and the stress intensity. The defect was analyzed by two methods: In the first method the defect was assumed infinitely long and depth equals to half the shell thickness. The analysis showed that the flaw will be stable with a safety factor of 4.4, and the amount of radial crack growth over the life of the tank is within the remaining tank shell thickness. In the second methodology the crack was assumed through wall and 5" long. The results showed that the crack will be stable with a safety factor of 3.13.
% l 1
l SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET : n No. ,A E ,, CCN CONVER$10N Project or DCP/M P SONGS 2 Calc No. M-DSC-280 ccN No. CCN - subject see title sheet % Sheet No. REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O R. cashu Q 7/26/93 Jun Gaor [4 7/28/93 l H 5L-AkIQ >P/9] pg . 'frfq)
3.0 ASSUMPTIONS
- 1. The material is isotropic and elastic (the nominal stress is within the yield strength).
- 2. None of the specifications of the used filler metal in the tank shell welding (E308, E308L, E309), requires material toughness value. But the data published by EPRI and others (Reference 4) provide toughness valucs in the form of J 1e which was used to calculate K gc of the filler metal.
- 3. The tank was assumed to undergo 400 cycles of fill and refill corresponding to the number of plant shut downs over 40 years.
i
)
SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET : ," % No. ,Ax ,, CCN CONVIRSION Project or DCP/>tiP SONGS 2 Calc No. M-DSC-280 CCN No. CCN - subject see title sheet sheet No. 7 7 6 BEV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE 1RE DATE 0 R. Qashu y 7/26/93 JunCaorf,r, 7/28/93 l M EL-ftVt L)' l0P/VJ SC , "/$% 4.0 DESIGN INPUT: Tank material SA-240-304 Reference 8 Tank Radius, 240 inch Reference 8 1 Filler metal E308,308L,309 Reference 6 J ze , 990 in-lb/in 2 Reference 4 E, 25 E3 Ksi Reference 4 { Material Yield Strength 29.8 Ksi 0104 F Reference 7 ! Tank shell thicknesses 5/16", 1/4" l and 3/16" Reference 8 Maximum defect 4.875 Appendix E 1 1 i i SCE 26-426 NEW 4/90 . 1
l 1 NES&L DEPARTMENT CALCULATION SHEET ="n No. ,Ax ,, Project or DCP/MMP SONGS 2 CCN CONVER$!CN Calc No. H-DSC-280 CcN No. CCN - Subject see title sheet REV Sheet No. Ml ORIGINATOR DATE IRE DATE ORIGINATOR REVf DATE IRE DATE 0 R. eashu y 7/26/93 JunGaorf.(, 7/28/93 l Il-5.-fgkri.y (0):lf] , . - 3, / b
5.0 METHODOLOGY
From appendix 3 the worst (largest) defect is identified as 4.875 J inch long lack of fusion (radiograph G2-3, in the second horizontal seam 14 feet from the tank bottom). i For the purpose of the analysis the defect will be assumed as a j fiv-inch long vertical flaw (the ratio of hoop stress to met...lonal stress is about 3), extending halfway through the platu thickness as shown in figure 1. Also in figure 1, in , dotted lines the credible paths of flaw propagation 1 j are.shown. Hi
-.A I ~h The stress intensity factor at c3 the crack tip can be h
conservatively calculated I a l 1 as if the crack front is in , l
~. ,#
- the radial direction as in /
j profile c2 Figure 1. A h kt# Figure 1 4 i } J i SCE 26-426 NEW 4/90 ! m
NES&L DEPARTMENT CALCULATION SHEET :: 1 2. ,AoE ,, CCN CONVERSION Project or DCP/MHP SONGS 2 Calc No M-DSC-280 ces No. CCN - , subject see title sheet Sheet No. N REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE 1 R. Qashu 8/23/93 JunGaor[f, 8/23/93 For such a case the crack tip stress intensity is defined by the ; 1 expression from Reference 1. k=Go ov(na/0) (1) where Go= Free surface correction. factor for the given stress variation provided in Tables A-3320-1 as function of l flaw aspect ratio (a/l = 0), and flaw tip position 1. o= Maximum hoop stress Ksi in the tank including effects of water sloshing due to earthquake and local stress due to the ring, calculated using . l finite element analysis. l a= Crack depth (half plate thickness = 0.125") Q= Flaw shape parameter as given by l equation 2 below: O=1-[Go o/c y,) 2/6 (2) Where oy ,is the material yield strength SCE 26-42G NEW 4/90
i CALCb5T5dN dHEET grm. ,, ,, CCN CONVERSION Project or DCP/944P SONGS 2 Calc No. M-DSC-280 CCN NO. CCN - subject see title sheet Sheet No. N '~) j REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE O R. Qashu g 7/26/93 JunGaor[.(, 7/28/93
/ u EL-/HctL.'( b/S/93 p& . '*/;fqy 1
4 Another credible path for the flaw to propagate, is to become thrcugh wall and extend longitudinally as in profile c in Figure 3
- 1. ,
1 J Given the crack is through wall, and 5 inches long, the stress intensity factor can be calculated for this case using linear elastic fracture mechanics (LEFM) provided in standard computer program PcCrack. LEFM crack model E, through wall axial crack in i i a pressurized cylindrical shell was chosen to perform the l analysis. Detail discussion of this methodology is provided in I l Reference 2. i. i
- The crack growth will be calculated based on Figure A-4300-1 of i reference 5, assuming water environment and R = 0.25. DK is q conservatively assumed equal to K ,x.
t 3 I i SCE 26-426 NEW 4/90
i NES&L DEPARTMENT ] CALCULATION SHEET :rs . ,A , ,, Project or ocP/ seep SONGS 2 cale No. M-DSC-280 CCM CONVERSION CCM No. ccN - ) srbject see title sheet sheet No. N REV OWIGINATOR DATE tRE DATE REV ORIGlWATOR DATE 1 IRE DATE
- / R a** t./ Shr a c-6 %,,,
/
- 6.0 "EFERENCES
J . A.iME Section XI working group on flaw evaluation, replacement J j of stress intensity factor calculation of article A-3000 of appendix A of section XI, based on Stress analysis of cracks. handbook by Tada and Paris, second edition (Sechior) 2 ). i 2. PcCrack Fracture Mechanics Software, Version 2.1, Structural 4 { Integrity Associates, Inc. 1 i 3. ANSYS User's Manual, Revision 4.4A, Swanson Analysis System. i i t
- 4. Journal of Pressure Vessel Technology, Vol 108, August 1986.
j 5. ASME Code Seccion XI, 1989 Edition. j 6. Data report SA-1415-1.
- 7. ASME Code Section III, Appendices, 1989 Edition.
1 i 8. Drawing S023-407-3-61-2, Primary Make-up Storage Tank shell I i plate layout. l l l l l i l l
- i l
l l l l I SCE 26-428 NEW 4/90
i NES&L DEPARTMENT ' CALCULATION SHEET = n ,.. ,A , o, l l CCN CONVERSION Project or DCP/MHP SONGS 2 Calc No. M-DSC-280 CCN No. CCN -
,e '
subject see title sheet Sheet No. d4 l l REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE j 0 R. cashu Q 7/26/93 Jun Geor h , 7/28/93
) tu k.-puiq \ci:It'7 76 /y'$)
7.O NOMENCLATURE: a Crack depth (in) ; l F Factor of safety (Kre/K I) Go Correction factor (2.8254) I Tank cross section moment of inertia (in ) d r Tank radius (in) , t Tank shell plate thickness (in) K Stress intensity factor (Ksi[in) ) K 2e Critical stress intensity (Ksi[in DK Stress intensity range (Ksi[in) M Bending Moment (in-lb) l N Number of stress cycles 1 Q Flaw shape parameter a stress (Ksi) a, y Material yield strength E Modulus of elasticity (Ksi) I l i 1 SCE 26426 NEW 4/90 I l
l I l NES&L DEPARTMENT l CALCULATION SHEET ' r" n ,.. ,A , ,, i CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccN NO. CCN - subject see title sheet Sheet No. Db REV ORIGINATOR CATE IRE DATE REV ORIGINATOR DATE IRE DATE O R. Qashu 7/26/93 JunGaorfh, 7/28/93 l U Eu-p utCI' ic/sl93 7. c . /rfq1, 8.0 CALCULATIONSt 1 l 8.1 STRESS CALCULA'.OIONS: j l 8.1(a) Meridional Stress, the meridional stress is calculated from the over turning moment as follows: I From page A34 the overturning moment is given at the ring i elevation (M = 237,927,613 in Ib). l l l The meridional stress a at the ring location can be calculated )
- as
j a=Mr/I I where r = 240 inch, tank radius I = r t r3 l t = 1/4 inch, tank thickness at location of maximum stress a = 237927613*240/r*0.25*240 3
= 5.3 Ksi 8.1 (b) Hoop Stress, To account for the discontinuity of the tank shell at the ring location, a three dice!!sional finite element analysis was performed using standard computer program ANSYS (Reference 3). The tank finite elemcnt model is depicted in CCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::rm. . ,, ': CCN c0NVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccN No. CCN - subject see title sheet Sheet No. 2 7 REV CRIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRF DATE 1 R. Qashu 8/23/93 JunCaor[6 8/23/93 i Figure 2. The stress analysis results are provided in Figure 3. The computer input image listing is provided in the attachment section. The water sloshing effect due to earthquake (SSE) was 1 l converted to hydrostatic pressure and added to the tank j hydrostatic pressure. The maximum hoop stress calculated by ANSYS is 15.9 Ksi, i l 8.2 FRACTURE MECHANICS CALCULATIONS: The stress intensity factor can be calculated using Equations 1, l and 2. Go = 2.8254 from table A-3320-1 0 a/t=0.5 and a/l=0. Q = 1-(15.9*2.8254/29.8)2/6 ) l
= 0.6213 l ?
K = 2. 8 2 54
- 15. 9 (T* 0.12 5 / 0. 6213 ) 1/2
= 35.72 Ksi /in A factor of safety is calculated by ratio of Krc/K, Kre = [(Jrc*E)
=
(( 990*25E6)
= 157.32 Ksilin F = 157.32/35.72
= 4.4 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::n No . ,,,E o, CcN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CcN NO. CCN - i subject see title sheet 1 Sheet No. 3 7 7 REV ORIGINATOR DATE 1RE DATE , REV ORIGINATOR DATE IRE DATE 0 R. Qashu 7/26/93 JunGaorh/,. 7/28/93 i H - S L-h 4I L.'( lo]S/ 9] pg /fgf(9 The analysis was repeated using PcCrack Reference 2, assuming a j through wall crack of 5 inch. The results of PcCrack are graphed . in Figure 4. The calculated stress intensity is 50.802 Ksi [in.
- Based on the PcCrack results a factor of safety equals to 3.13 is calculated.
l 8.3 da/dN CALCULATION The crack growth is calculated using figure A-4300-1
- (Reference 5) for water environment, and R = 0.25. DK = 50 Ksi[in, which is the maximum stress intensity based on 5 inch axial crack.
4 From figure A-4300-1 @ DK = 50 Ksi[in find da/dN = 200 E-6 inch / cycle. d conservatively assume that the tank will undergo 400 cycles of f filling and refilling, corresponding to the number of plant shutdowns over 40 years. Crack growth = 400
- 200E-6 l = 0.08 inch 4
The remaining tank thickness at defect location = j i = 0.125 .08 I i
= 0.045 inch SCE 26-426 NEW 4/90 I
NES&L DEPARTMENT CALCULATION SHEET :," % ,.. , A. ,, Project or DCP/MMP SONGS 2 CCM CONVER$10N Calc No. M-DSC-280 CcM No. ccN - subject see title sheet Sheet No. Mi REV ORIGINATOR DATE IRE DATE REV l ORIGINATOR DATE IRE DATE 0 7/26/93 JunGao/yG. R. cashu k.\ 7/28/93 I t1- 2L-AM i L 9 l0/s/13 pc _ /ffS3
- s. . ? -
x s y ..y x g .. 7-
, j %
7'/ - /j ..
.sss Y' Y ' ? f / , /
/ i ! ,
. \b
( <,'/, - ,
., \,\
/
- x. x x 's'x ,
- l k l
'r s N sh\ \
N "t.
?
K_ ' 2 t 9 I i . Figure 2, Tank shell finite element model SCE 26-426 NEW 4/90
l l Figure 3 Hoop stress distribution i t I i 500 i i , k 400 - r a ' n k " *a/isa : 300 - 1 e ; e I h t 200 - i n H % 1/4a 2 g -~ - .. .... ,
/
y 100 - J ; g gg g 1 5 5 g a /4- 5/16" n n n
?
-5 0 5 10 15 as .b \ E atreen Pal (Thousande) g
> L. t
$ & co I,_ '
a' V O: q
~=
m
Figure 4 K vs Crack size 100
, /
80 '
/
/
K / /
/ r K
./
/
s i 60 -'
'd s 4. ,/
G ' jq r ,/
/
/
\ 40 /r n c -' h
/
/ ~ -~
- - - - - - - - ~ ~ -
/
/
20
/
/ -
9 ?
/
/ l l
\
l
, ll I 0.2 1 2 3 4 5 6 7 8 9 3 Crack size Inch ,, g if ' I $
g T3 ope I
. knE*
- s" a,
._ ._m.._
. NES&L DEPARTMENT .i CALCULATION SHEET ="Lo. , A. ,, ! CCN CONVERSION j Project or DCP/letP SONGS 2 Cale No, M-DSC-280 CCN No. CCN - subject - see title sheet i Sheet No. N 'V l . REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE I DATE .) 0 R. Qashu 7/26/93 JunGaor}.y. 7/28/93
\
/ u e u -fr w u.Y totsj q) FC. '*/rfg y
- l l
{ ATTACHMENTS TO APPENDIX F 4 1 i ! 1 ! l l l I i < 4 k i i i 4 I l i i i i
)
I SCE 26-426 NEW 4/90 i .I
NES&L DEPARTMENT , i CALCULATION SHEET ::: n ,.. ,Ax ,, CCN CONVERSION i Preject or DCP/M4P SONGS 2 Calc No. M-DSC-280 CCN No. CCN - j Subject see title sheet Sheet No. 78 b REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE l 0 7/26/93 JunCaorff,. l R. cashu Q 7/28/93
/ V - EL-/}la L_Y' l0lsjgy pg. t>lf9 l 1 j
4 j \
/ PREP 7 '
\
/ TITLE, PRIMARY PLANT MAKE-UP TANK l
i C*** FILE NAME: PPMSI. 4 C*** 1 C*** FORCE APPLIED NEAR THE TOP C*** KAN,0 j C*** 4 j C*** ELEMENT TYPE: ELASTIC SHELL i 1 ET,1,63 ET,2,8 J C*** C*** MATERIAL PROPERTIES EX,1,28.3E6
- TANK SHELL (TYPE 304 SS) ,
\
- NUXY,1,O.3
- EX,2,30.OE9 i
NUXY,2,0.3 i C*** 1 C*** REAL CONSTANTS 1 R,1,0.25
- BOTTOM
; R,2,0.3125
- FIRST TIER R,3,0.25
- SECOND TIER SCE 26-426 NEW 4/90 1
NES&L DEPARTMENT l CALCULATION SHEET =",NC,,,. ,A,E ,, ! l CCN CONVER$!ON I Project or DCP/MP SONGS 2 calc No. M-DSC-280 CCN NO. CCN - subject see title sheet Sheet No. N I i i i REV ORIGINATOR DATE 1RE DATE REV ORIGINATOR DATE IRE DATE . i l 0 R. Qashu A.r( 7/26/93 JunGaorf.(,, 7/28/93
- I W D -Awi@ MIS /O Fc . "/$i; \
R,4,0.1875
- THIRD TIER l
! R,5,0.25
- ROOF
( R,6,1.0
- SPOKES C***
I C*** GEOMETRY RT=240.0
- TANK RADIUS l H1=95.625
- HEIGHT TO TOP OF FIRST TIER H2=167.25
- HEIGHT TO TOP OF SECOND TIER HT=408.0
- TANK HEIG iT RBL=243.0
- BOLT CIRCLE RADIUS l
.RBT=246.0
- OUTSIDE RADIUS OF THE BOTTOM 1
RR=576.0
- ROOF RADIUS Al=SQRT(RR*RR-RT*RT)
A2=HT-Al
- CENTER OF COORDINATE SYSTEM 11 A3=A2+576.O C***
C*** NODE DEFINTION N,1,1.0
- CENTER OF THE TANK N,7,RT
- TANK RADIUS FILL,1,7
- N,9,RT,H1 FILL,7,9,,,,,,O.328125 SCE 2s426 NEW 4/90
l NES&L DEPARTMENT i CALCULATION SHEET ::: n .. ,A , ,, CCN CONVER5!0N l j Project or DCP/MMP SONGS 2 Calc No M-PSC-280 CCn no. CCN - I s l
! Subject see title sheet Sheet No. N4 '
REV ORIGINATCH DATE IRE DATE REV ORIGINATOR DATE IRE DATE O R. cashu
% 7/26/93 Jun Caor$(, 7/28/93
/ N - EL-42. /c-/ 10/5/f5 y z; , '#/r/g y i l
l t ' l N,11,RT,H2 i ! FILL,9,11 I ', N,17,RT,HT FILL,11,17 C*** N,23,1.0,A3 N,9000,0.,A2 NGEN,2,1,9000,,,1.O NGEN,2,1,9001,,,,1.0 CS,11,1,9000,9001,9002 CSYS,11 l 1 FILL,17,23 1 l C*** I CSYS,0 l N,24,RBL 1 N,25,RBT l C*** l N,9003,0.,0.,0. N,9004,1.O,,-1.0 CS,12,1,9003,7,9004 l l l CSYS,12 NGEN,72,25,1,25,,,5.0 l SCE 26-426 NEW 4/90 1
j NES&L DEPARTMENT li CALCULATION SHEET g;~, ;N No. ,A. ,, Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN CONVERSION CcM No. CCN - Subject see title sheet sh..t no. MG 1 REV ORIGINATOR DATE !RE DATE REV ORIGINATOR DATE IRE DATE O R. Qashu 7/26/93 JunGeorj[+ 7/28/93 l 53- EL- A k-s L.Y Il/S/93 f.- C , "/3f4 y i l NDEL,9000,9004 i C*** l l CSYS,0 4 N,1801,,367.875 C*** i
- C*** ELEMENT DEFINITION l
MAT,1 i j TYPE,1 l REAL,1
- BOTTOM i
! E,1,2,27,26 i
- EGEN,6,1,1 1 j E,7,24,49,32 l i
1 j E,24,25,50,49 j EGEN,71,25,1,8 i
- E,1776,1777,2,1 l EGEN,6,1,569 i E,1782,1799,24,7 I l l E,1799,1800,25,24 l 1
i C*** ' J REAL,2
- FIRST TIER E,7,8,33,32 ,
EGEN,71,25,577 l l SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ;;r n ,.. ,A , ,, CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 ccN No. CCN - Subject see title sheet Sheet No. M) REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE IRE DATE ] O R. Qashu Q 7/26/93 JunGeorj[,. 7/28/93 l H-EL-A k I LY 10}$/T3 pg, G'fff, i i l
- I j E,7,1782,1783,8 J
! EGEN,2,1,577,648 j C***
!' l REAL,3
- SECOND TIER 1 i E,9,34,35,10 l f
l EGEN,71,25,721 ' E,1784,9,10,1785 l l EGEN,2,1,721,792 l l C*** ' REAL,4
- THIRD TIER i I I
E,11,36,37,12 l EGEN,71,25,865 E,1786,11,12,1787 EGEN,6,1,865,936 C*** 1 REAL,5
- ROOF 1
E,17,42,43,18
; EGEN,71,25,1297 i E,1792,17,18,1793 l l ) EGEN,6,1,1297,1368 C*** LOADING AND BOUNDARY CONDITIONS WSORT,ALL l
i SCE 26-426 NEW 4/90 J
I j NES&L DEPARTMENT CALCULATION SHEET ;;;" n No . ,A, ,, i ' CCN CONVERSION Project or DCP/M P SONGS 2 calc No. M-DSC-280 ccN No. CCN - subject see title sheet 3 Sheet No. Y[d REV ORIGINATOR DATE IRE ] DATE REV ORIGINATOR DATE IRE DATE j 0 7/26/93 7/28/93 R. Qashu Q Jun Gaor4 (, . j l M EL-/>k-t LY l0}S/$3 f*G , fyffgf s, i i i NSEL,,24,1799,25
- FIXED NODES ALONG THE BOLT E
CIRCLE D,ALL,ALL
- NSEL,,9,1784,25 D,ALL,ALL NALL
- NSEL,Y,0 D,ALL,UY,O NALL I C***
l ITER,-100,100,1 I ESEL,,649,720 EP,ALL,1,14.4 ESEL,,721,792 EP,ALL,1,13.6 I ESEL,,793,864 EP,ALL,1,12.4 ESEL,,865,936 EP,ALL,1,11.2 ESEL,,937,1008 , l EP,ALL,1,9.85 i ESEL,,1009,1080 1 SCE 26-426 NEW 4/90 l l
1 NES&L DEPARTMENT CALCULATION SHEET ;g"n No. ,A. C, CCN CONVERSION Project or DCP/MMP SONGS 2 Calc No. M-DSC-280 CCN NO. CCN - subject see title sheet Sheet No. 9Yh REV ORIGINATOR DATE IRE DATE REV ORIGINATOR DATE !RE DATE O R. Qashu Q 7/26/93 JunGaor/f. 7/28/93
/ N ' e L- k tt- Y lois/93 i c. %fp>
EP,ALL,1,8.5 ESEL,,1081,1152 EP,ALL,1,7.2 ESEL,,1153,1224 EP,ALL,1,S.8 ESEL,,1225,1296 EP,ALL,1,4.5 EALL AFWRITE j FINISH j / INPUT,27 : ' i FINISH ' 4 l l l I ) l l 1 i s i 4 3 l I l
- \
l l 1 l i , SCE 26 426 NEW 4/90
ca na/ PRELAL CCN NO. PAGE tm S (C) COP IG 984, 1990 CALC NO. M"N' N REV.8. STRUCTURAL INTEGRITY ASSOCIATES, INC S M ENT ~ SMT '# 4 # SAN JOSE, CA (408)978-8200 VERSION 2.1 'OMMTOR d DAM M4 pg >% DAT5 Dato: 22-Jul-1993 Timm: 18:27:11.99 LINEAR ELASTIC FRACTURE MECHANICS EVALUATION tS6 crcck model:THROUGH WALL AXIAL CRACK IN PRESSURIZED CYLINDER WALL THICKNESS (t) = 0.2500 OUTER DIAMETER (OD)= 480.0000 CASE ID STRESS 1 15.9000 kk )4, CRACK ---------------STRESS INTENSITY FACTOR---------------- SIZE CASE 1 0.1000 8.943 0.2000 12.693 0.3000 15.605 0.4000 18.092 0.5000 20.312 0.6000 22.347 0.7000 24.247 0.8000 26.042 0.9000 27.756 i 1.0000 29.403 l 1.1000 30.996 1.2000 32.544 1.3000 34.056 1.4000 35.536 1.5000 36.991 1.6000 38.424 1.7000 39.840 1.8000 41.240 1.9000 42.627 2.0000 44.005 2.1000 45.374 2.2000 46.737 2.3000 48.095 2.4000 49.450 2.5000 50.802 1 1 I 1 I 1
ICCN NO/ { PREUM. CCN NO. 8 AGE I ccN coNvsns:cN: om No. CCN-I 0"E CALC NO. N ' 0$f bb RW. $ I N/fl ) Pc-CRACK VERSION 2.1 PAGE 2 SUPPLEMENT SHT ,/ 2.6000 52.154 ORIGlhMTOR
- 2.7000 53.505 SkDADEMI4kh%
2.8000 54.856 IRA 'E I' DATc - \.#f% 2.9000 56.209 3.0000 57.565 3.1000 58.923-3.2000 60.284 3.3000 61.650 3.4000 63.020 3.5000 64.394 3.6000 65.774 3.7000 67.160 3.8000 68.551 3.9000 69.949 4.0000 71.353 4.1000 72.764 4.2000 74.182 4.3000 75.607 4.4000 77.039 4.5000 78.479 4.6000 79.926 4.7000 81.382 4.8000 82.845 4.9000 84.316 5.0000 85.796 END OF pc-CRACK 1 l l
. -. - - - - - . - . . . . . ~ . . . - . - - . . - . - . . - . - - - . . . _ - - . . - . _
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.w 0.15 1.0306 l
1.2670 1.1482 1.1954 1.0042 1. tem 1.0632 9.20 1.36s4 1.1744 j 1.121e 1.0928 1.e739 1.e442 0.25 1.4929 1.2170 1.1399 1.1035
- 1.0832 1.0543 0.30 1.es39 1.MM 1.1621 1.1160 1.8848 1.0614 yl.05c '2.So _ h 43 0.40 2.1064 1.3440 1.213s 1.1444 1.1190 1.e772 annage m -
0.50~2.EE 1.s12S 1.2H3 m 2.4 2.
O.'60 47MM 1.0 72 **1.3216 1.1757 1.14s7 1.8931 b 0.70 ,6.3743 1.7373 1.3610 1.2039 - 1.14e9 1.2237 -1.tede 1.1 58 111112-- _T f " ""7/23/f3 { 0.40 11.991 1.7999 1.3761 1.22 5 1.1902 1.1N5 g, gg ListAs 0.00 0.7622 0.M35 l 0.6826 0.7019 0.7214 0.7411 c1 0.05 0.7624 0.M51 1 0.10 0.4433 0.7022 0.7216 0.7413 ( 0.15 0.7732 0.7h5 0.6mc 0.6s55 0.m31 a.722t 0.741: 0.6780 0.6890 { 0.20 0.70u 0.7230 0.7426 0.8267 0.6891 0.6939 0.7067 0.7243 0.7420 0.25 0.4706 0.m29 0.7000 0.70% 0.30 0.7260 0.7451 i 0.9276 0.7193 0.7073 0.7124 0.7382 0.7468 0.40 1.09C7 0.7544 0.7249 0.7200 0.7334 0.7511 l C.50 { 1J 20 0.00M 0. 74 54 c.7314 0.7417 0.7546 0.60 1.7863 0.E44 0. 76 71 0.7641 0.7520 0.7631 1 0.70 2.6125 0.8908 i C.80 0.7582 0.7548 0.7653 0.7707
- 4.5727 0.9268 0.8063 0.7753 0.?t22 0.7M2 i
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C.15 0.5996 0.5109 0.s323 0.5540 0.5415 0.60 5 0.6048 0.5144 0.s340 0.5564 0.5415 0.6087 { 0.20 0.6247 0.s202 0.s364 0.5571 0.5815 0.6089 i 0.25 0.64 73 0.sut 0.n* 0.5 m 0.ui? 0.6 m 1 0.30 COPY FOR YOUR 0.u 0.6 775 0.s350 0.s430 0.1592 0.5420 0.6099 j l$$$$$g 8.uii 0. sus 0.ssa 0.Sur 0.5 m 0.6u5 0.s0 em, 0.s776 e.s432 0.5600 0.5069 0.6144 0.60 0.70 1.1382 4.4027 0.s762 0.5760 0.5931 0.6108 1.s7s7 0.6281 0.s907 0.ss74 0.4437 0.6255 0.00 2.s997 0.6513 0.6063 0.6031 0.6200 0.0s1 CLSit 0.00 0 0.05 e.s060 0.42u 4.4680 0.473s 0.s006 e.s290 e.M12 s.4250 0.4482 0.4736 0. sees e.s290 0.10 e.sett 0.4246 0.uas 0.4736 4.ses4 e.s290 0.n e.ws9 e.use 0.u9: 0.4737 0.smi 0.=
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