ML20203E902
| ML20203E902 | |
| Person / Time | |
|---|---|
| Site: | LaSalle  |
| Issue date: | 02/03/1998 |
| From: | Eberhardt A COMMONWEALTH EDISON CO. |
| To: | |
| Shared Package | |
| ML20203E435 | List: |
| References | |
| L-001337, L-001337-R02, L-1337, L-1337-R2, NUDOCS 9802270156 | |
| Download: ML20203E902 (109) | |
Text
{{#Wiki_filter:. - - .- COMMONWEALTil EDISON COMPANY CALCULATION TITLE PAGE i CALCULA~llON NO'.: L-001337 PAGE N'0'
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1 X SAFETY RELATED D REGULATOldY RELATED 0 NON SAFETY RELIATL. y
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CALCUl ATION TITLE Containment Liner I.cak Chase Chi. del Assessment e
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STAllON/ UNIT: LaSalle County / Unit i SYSTEM ABBREVIAllON: NA EQUIPMENT NO.: in ami NA PROJECT NO.: 4. Ami 10246 012 lbV:T STXTUSTApproViF VATL'kTACRE01stITkON RU.~ - ITAE.~ ~
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. A PREPARED BY: A. C. Eberhardt/ /d M #7M p.yF DATE: 10/28/97 REVISION
SUMMARY
- Initialissue ELECTRONIC CALCULATION DATA FILES REVISED: NA (Name ext / sire /date/ hour: min / verification method / remarks)
DO ANY ASSUMPTIONS IN THIS CALCULATION REQUIRE LATER VERIFICATION YESO NO X REVIEWED BY: R. Namnerumall Med
/
DATE:/f @ O REVIEW METllOD: Detailed COMMENTS (C, NC OR Cl):._G1 APPROVED BY: . ..k* M kA~fftl DATE: l[-3.-47
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9002270156 980220 N* PDR ADOCK 05000373 P PDR
CALCULATION TITLE PAGE PAGE No.: 1,1 C ALCULATION NO: 1 001337 DESCIllPTION CODE (C018):_S02 DISCIPLINE CODE (Coll):_ S LASALI E STATION sYsTEnt CODE (Coll): NA . - - -
@ Unit i O Unit 2 O Unit 0 ELEVATION (Col 6): NA i
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Title:
Containment Liner Leak Chase Channel Assessment g Safety Itclated O ltegulatory Itelated O Augmented Quality O Non Surety Itelated itEFERENCE NUh111ERS: (Coll Panel) Type Number Type Number AEDY PD SED Elf L1997 06237 CIIRN
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PAL 3265 , PitOG 1 P!(OJ 10248 012 SSYS RNID COh1PONENT EPN: (Col 4 Panel) DOCUh1ENT NUhlHEllS: (C012 Panel) EPN Component Doe Sub Document Number - Assoe. i Type Type Type Cale. l Cale Eng 164 SYes ONo Oyes ONo Oyes ONo Oyes ONo Oyes ONo ItEntAltKS: i llEV. No. ItEVISING APPilOVED DATE OltGANIZATION (Prjnt & Sign) 1 SO40/ r(t Nt) S._M. Kazmi %h /A. oV.-9 7 2 SOWO/s 4 t. HPD 5. H~IlA h+tI
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19 03-7g A i i Controlled Electronic Form Page 1 of 2 File: 12-02c. doc r See NEP Table of Contents issued: 9/23/97 NEP 12 020 l l
l CALCULATION NO. L 001337 PAGE NO.: I e '2-REVISION SUMMARIES REV:1 REVISION SUMhtARY: Incorporated Administrative Review Comments: Added Pgs 1.1,1.2, & 25.2, Revised Pgs 2,3,25.1, E g p6. Ac ro PA c. # A. y Electronic Calculation Data Files: (l'rogram Name, Version, file name eWsire'date/ hour /: tr.ir.) NA Prepared by: A. C. Eberhardt g(( / - V / 4 [17 Print Sign Date Reviewed by: R. Namperumal ,hM-w1 /2 y - F 7 Print ' Sign Date Type of Review: O Detailed O Alternate O Test LU ANY ASSUMP110NS IN 1111S CAlfUIAllON R14)UIRE LATIR VERIHCAllON OYES S NO Tracked by: EA REY: 2 REVISION
SUMMARY
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G R,, h t l W 4 GMBCD Ptrics. R. t v s cu t> pac,ns I.8,t.) 1, 3, 2(,, A taco M.s . 2 9 - 31. A H.b A 'i r A CHM EN T C, Pr b El- GG o Elecnonic Calculation Data Files: (l'rogram Name. Version. File name eWsite/date' hour /: min) Prepared by: J . C EBEM GT'" M ~/1. k dT / f6 '-98' Print Sign Date Reviewed by: E .MA-4 P F /R v M A L h %,l.e % / 2 7- T Print Srgn Date Type of Review: @ Detailed / O Alternate o Test DO ANY ASSUMPilONS IN 1HIS CALCUIAllON RLQUIRE IATER VERIHCATlON O YES @ NO Tracked by: MA,, Controlled Electronic Form Pape 2 of 2 File: 12-02c. doc See NEP Table of Contents - Issued: 9/23/97 NEP 12-02C
i a l COMMONWEALTH EDISON COMPANY CALCULATION TABLE OF CONTENTS PROJECT NO. 10248 012 j CALCULATION NO. L 001337 REV. NO. 2 PAGE NO. 2 i DESCRII'llON PAGE NO. SUIl PAGE NO. TITLE PAGE I l.1 ' REVISION
SUMMARY
l 1.2 TAl3LE OF CONTENTS 2 PURPOSE /OllJECTIVE 3 & 27 METilODOLOGY AND ACCEPTANCE 3 & 27 CRITERIA 3 ASSUMPTIONS 3 & 27 DESIGN INPUT 3 4 & 27 REFERENCES 4 & 27 4 CALCULATIONS S - 25.2 & 28 31 5.1,5.2.12.1.13.1,18.1.25.1,25.2
SUMMARY
AND CONCLUSIONS 26 & 32/ FINAL ATTACllMENTS Al A7, B1. B7, Cl . C8, D1 D39, El - E6/ FINAL 4
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1 Calc, No, L 001337 R:v,2 Pago No 3 Proj, No. 10364 004 TNs Calculatsin has tieen prepared usmg Methcad Plus $. S&L Program Numtaet 03 7.64s-6 0 i l
-~
j Purpose and Ohle.g.hg To perfcmi a design assessment of 2" and 3" containment liner leak chase channels in the suppression pool u and drywell. Discrepancies between design material yield strength and specified minimum material yield . strength are addressed. In addition, the margin between specified yleid and ultimate t'enslie strength as. determined from vendor supplied certified material test reports (CMTRs) will be venfied. Results are given in terms of margin factor which is defined as the ratio of allowable stress divided by actual stress. This calculation is performed in response to PIF # L1997 06237, Rev.1 provides an enhancement to the discussion of jet impingement loads in the containment drywell but has no impact on the summary or conclusion. See page 27 for Rev. 2. g Methodolony and Acceptance Criteria This calculation shall be performed in accordance with the applicable documents listed as Design inputs
- below. The acceptance criteria used for this assessment is given in Subsection 4.3.2 of the LaSalle Design Assessment Report (DAR)(D.l. 32). Applicable load combinations are defined in Table 4.3 2 of the DAR.
Allowable stresses for load combinations 1 through 3 are per the 1969 AISC Specification. However, it has been demonstrated !n previous calculations (see D.I. 33) that the governing load combinations involve either j hydro-dynamic loads or jet impingement loads. For these load combinations, the allowable stress is limited to 0.95 fy. As permitted in Ref. 3, Sect. Ill.2.a. a 10% increase ir minimum specified yield strength will be used to account for strain rate effects associated with impact loads. The allowable stress used for weld assessment is 2 I ksi for allload combinations. Assumptions There are no unverified or unconservative assumptions used in this calculation. i Deslan Inouts (Check where applicable
- APP")
APP
- 1) 1 DC SE 01 LS, Rev. 7, Structural Project Design Criteria
- 2) ,,,_ AISC's Manual of Stect Construction. Eiahth Edition
- 3) 1 AISC's Manual of Steel Construction. Seventh Edition 4a) ,,,,,,,, ACl 318 Buildina Code Reauirements for Reinforced Concrete Structures.1983 4b) ,,,,,, ACl 349 Buildina Code Reautrements for NSR Concrete Structures.1980
- 5) __, AISl's Cold Formed Steel Desian Manual.1983
- 6) 1 DC-SE 02 LS, Rev. O, Seismic Response Spectra
- 7) 1 DC SE 03 LS through DC SE-09 LS, All Rev. O, Hydrodynamic Response Spectra
- 8) ,_,,,, Calculation 802100 2, Rev. O, Pages 25 37, Peak g values for Pipe Supports
- 9) ,_,, Calculation 802100 2, Rev. 8 Pages 4144, Peak g values for Pipe Supports in the Drywell 10)_ Calculation 802100.2, Rev. 8, Page 40, Peak g values for Electrical Supports in the Drywell
- 11) , Calculation 795, Rev. O, Pages 42-43, Peak g values for Cable Trays and Conduits
- 12) ,_,, DIT No. LS EPED-0077 01 and Calculation No. GDS 3.6 6, Rev,1. Reduced Conduit Weights 13),,,_ S&L's SD&D Report No. 78, Rev. 4. Concrete Masonry Wall Design '
- 14) S&L's SDC ES.0, Rev.1, Loads, Load Combinations, and Allowables 15),,,,,_ S&L's SDS E11.0, Rev. 2 Hitti Kwik Bolt Design 16),,,,,,,,,, S&L's SDS-E11.0, Rev. 3 Hilti Kwik Bolt 11 Design
- 17) ,,- S&L's SDS-E30.0, Rev. O Cable Tray Design L,1337R2 MCD
_. ,_ _ _ ._ _ __.____ _ _ _ _ _ . _ .._ _ - - _ . _ _ -_.-_ ~ , - .. _ _ _ _ _ _ _ . _
C:Ic, No. L 001337 R';v, O Proj.Na, 10248-012 Pago No. 4
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- 18) S&L's SDS E31.0, Rev. 2 Cable Trey Support Design
- 19) S&L's SDS E33 0, Rev. 3 Conduit and Conduit Support Design 20)1 S&L's SDS E37.0, Rey,6 Pipe Support Design
- 21) S&L's SDS E41.0, Rev. 2 Weld Design !
- 22) S&L's SDS E44.0, Rev. 0 Embedmont Plate Design ;
- 23) Calculation 802104.4, Rev. 9, Pages 4 5, Design Equations for Embedmont Plates 24)1 LaSalle County Station Updated Final Safety Report, Rev.11 25)1 LaSalle County Station Drawing S-384, Rev. U
- 26) S&L's GDS 3.6.3, Rev. 3
- 27) _ S&L's Project lastruction LSNS 22. Rev. 3 ,
28)1 NUREG \CR 2913. "Two Phase Jet Loads" Published Jan.1983 by SANDIA National Laboratories -
- 29) S&L's Project Instruction LSNS.16, Appendix 1. Rev. 0 39)1 CBI Shop Drawings (See specific references below for Revision nos.)
31)1 SRV & LOCA Loads on Downcomer Bracing and Gusset Plates, NSLD Calc. 3C71179-002) 32)1 LaSalle County Station Mark ll Design Assessment Report, Rev.10 33)1 LaSalle Calculation 164," Suppression Pool Liner Assessment & Anchorage Assessment" 34)1 LaSalle Calculation 3C71075-001,
- Loads due to Loss-of Coolant Accident in LaSalle Containment,"
Rev,6 35)1 LaSalle Specification J 2534," Primary Containment Steel Liner Work", Amd. 3,914 81 References
- 1. PIF # L1997 06237
- 2. Staad-ll! Structural Analysis, S&L Program # 03.7,065 20.2)
- 3. USNRC Standard Review Plan 3.6.2, Rev.1. July 1981 GLODAL UNIT DEFINITIONS : kip ksb k}p kip 1000 Ibf O'llGIN : 1 psf a M ksfeM in I lbsa1Ibf Ib a 14 lbf CAL 13372 MCo
C:le. N3, L 001337 Rev. O Pro). No.10248-012 Pcgo No. 5
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1 ! Calculations & 92Rfrel Description ! f A total of three cases are considered to cover all variations in configuration, material properties, and governing
; load combinations. These three cases are described below as part of the calculation index.
i Calculation in,dag i The calculation is divided into three sections to consider tha following cases: Pages 5 to 11, 2"xi"x 3/16" stainless steel channel subject to allloads in the suppression pool. , Pages 12 to 17, 3x4.1 channel subjected to jet impingement loads in the drywell and hydro-dynamic LOCA and SRV loads in the suppression pool. Pages 18 to 24, 3x4.1 channel with one leg shortened by 1/2" to accommodate a thickened embed plate. This configuration is analyzed for hydro-dynamic LOCA and SRV loads in the suppression pool. Case 1: 2"x1"x Slit" Stainless Steel Channel P_ttparation of Inout to Stead Comnuter Model_ r This model includes the 2" channel as well as the half coupling and test plug connection detail shown in Section D-D on CBI dwg. 34, Rev. 3. This model covers all 2" channels on the wall and basemat. Joint coordinates are conter line coordinates. Additionaljoints are provided so that stresses can be determined at the end of the fillets at each corner of the channel. Member properties of the channel web and flanges are based on a thickness tw of 3/16" and an effective width of 3.0". This is based on the criteria given in D.l. 20, Fig. 37.6.6-4 where be is the side dimension of a square with an area equivalent to that of the 1/4" half coupling which has a diameter of 7/8", 3 3 dCf.in . T6 "
.g .s Equivalent square:
ba-a n g 'l ba = 0.78'In
. CAL 13372 MCD
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C:le. No. L 001337 R;v. O Proj. No. 10248 012 Pcg3 No. O I j Effective width b ba + 12 tw _. b = 3.0'in C 7 x 1 x Slit" Pronerties_of Flanne arid Web b 3.0 in t:=3g.in b1 8 AY = 0.5625'in' > IZ
- Sy i lZ e 0.00165'in d Note that Ax is calculated in the Stead program using too values of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Stand but are not used in the analysis.
Member Properties of 1/4" Dia. 3000 !b. half couellnn From Catalog W 68 Bonney Forge, Allentown. PA t J A
- 1.125 in C =.55Nn l B = f in Wall thickness t*
t = 0.16 *in b=8 . use t = 0.17 in b = 0.875'in AY *bt 8 AY = 0.1488 *in8 12
- b-1 gy Note that Ax is calculated in the Stand program using the values IZ = 0.0003582 ud of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Staar) but are not used in the analysis.
CAi1337ZMCo
Cde. N3, L 001337 Rev. O Proj, N3,10248-012 Paga No. 7 4 Loads: i The previous Calculation No.164 (D.I. 33) identifed the following critical k> ads: Maximum Accident Pressure =
- 45 psi (Ref. 32. Table 1.1 1) and LOCA Poolswell Impact.
As shown in Table 2 of D.I. 34, loads due to pool swellimpact act on structures above the suppression cool
- located between El. 700' 2"(High water levelin the suppression pool) and El. 718' 8"(Max. height of poolowell).
The maximum value of pool swellimpact pressure (= 643 psi)is used in this analysis. Member Loads Member loads due to poolswell act on members 1 and 2. The rnagnitude is equal to the pressure times the member width. Uniform load, members 1 and 2: GX = (643 + 45) 3.0 f GX = 2064'h Poolowellimpact pressure on circular half coupling and plug: j From D.I. 34. Table 3, the maximum value of pool swell impact pressure acting on circular pipe sections is 48.88 psl. ! I Uniform load, member 10: GX .= (48.88 + 45) 0.876 GX = 82.14 ' Member loads on Members aubjected to Accident Pressure = 46 pel l Uniform load, mems. 3 to 7 8 9: GX1 = 45 3.0 f GX1 = 135.0
- CAL 13371MCD 4
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l l C;lc. No. L 001337 Rev, O Proj. N).10248-012 PagaNo.8 l 1 Uniformload, members 11 & 12: c '2 = 45 0.875 GX2 = 39.4 *f l l Uniform load, member 8: Load on member 8 is equal to balance of load not acting on member 11. ! l 4 GY = GX1 - GX2 i GY=95.6sh . Joint Loads Member loads do not represent 100% of the pressure load acting on the channel because member length is based on center to center dimensions. Therefore, length times member width will not completely represent the total surface area subjected to pressure loads. For this reason, Joint loads are used to apply the additional load that acts on the missing surface area. Joint loads due to poolswell are applied to Joint 3. The magnitude is equal to the pressure times the missing sur' ace area of the channel flange. Flange length = 1" Length modeled in Stand = .9063" i- Effective width = 3.0" Missing surface area: A = (1 .9063).in 3.0 in A = 0.28 'in Pressure load = 688 pel FX = 688 psi A FX = 193.4 *lbf
. CAL 1337Z MCD
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C:Ic No. L-001337 R:v. O Proj. No. 10248 012 PcgaNo.9 Evaluate joint force at Joints 3 & 6 due to LOCA Pressure = 45 psi -- FY 45 psi A FY = 12.65 lbf Thermal Load; As stated in the previors Calculation No.164 (D.I. 33) the channel is analyzed with and without the effects of temperature. The temperature change for the poolswellload condition is 76 deg. F. Variatione in Material Properties Revlow of Vendor supolied CMTRs shows that ASTM A276 Type 304 material has been supplied with two types of finishes. Hot-finished material has a yleid of 30 kal and an ultimate of 75 kal, whereas cold finished material has a yield of 45 kai and an ultimate of 90 kal. CMTRs are reviewed to , determine the appropriate design yield strength for each channel configuration. Material Yield Stronath The following documents rotated to Vendor Specification 2534 are provided in Attachment 4 of the calculations:
- 1. Stores and Metal Verification Summary & Supplement Sheets, File # 5.1 CCM
- 2. Material Heat Number Sheet, File No. 8.16-2, Document #18
- 3. Certified Material Test Reports, File No. 5.2 These documents identify the following material heats for 2x1x3/16" channels:
Min. Specified Heat No. Yield Strength 23755 30,000 psi F30188 30,000 psi 30660 45,000 psi 30706 45,000 psi 30844 45,000 psi 40523 30,000 psi 42379 30,000 psi For the cases shown above, design yield strength'is controlled by min, specified yloid strength = 30 ksi. As permitted in Ref. 3, Section Ill.2.a. a 10% increase in min, specified design yield strength is used to account for strain rate effects associated with dynamic effects of LOCA loads such as jet irraingement and poolswell impact loads CAL 13372.MCD -
Calc. No. L-001337 Rev. O _ Proj.ND. 10248 012 Pcg3 No.10 Therefore, the allowable stress is: Fb
- 0.951.130.0-ksi Fb = 31.35'ksi Mosults of Stand lli Analvels:
Results of the analysis are shown in Attachment A. Maximum member stress occurs in member 1 = 29.00 kal, (See Page A7) Fb Mar 11 ~= gg Mar 11 = 1.08 Check weld based on reactions at Joints 1 and 8 (Max. reaction occurs at joint 1). I *' Wcld force: fw
- kip 3in fw a 0.50' Wold Allowable:
Fw = 0.707 21 ksi h in Fw = 2.78 ' Mar 12 's h Mar 12 = 5.56 CAL 13372 MCD .
e M C:Ic. N1 L401337 R:v. O Proj. No. 10248 012 Pago No.11 l l ! r I i, Check 3/18" weld between Channel and couplina for test alue: Diameter of circular weld a B = 0.875'in Assume 1/2 of weld length is effective for "i Member no.11 and 14 each l Therefore, weld length w L
- 3.14169 'g 2 I L = 1.37'in Weld allowable = . Fwi r Fw L P
Fwi = 3.83
- kip Actual force in weld (Member 12 govems): fw (.07432 + .04992 ) . kip fw = 0,09' kip l
Fwi Mar 13 = y i Mar 13 = 42.75 Inspection of this large margin shows that the half coupling and its attachment weld can easily resist the pool hydrodynamic loads.
- CAL 1337Z.MCD m.. . . _ , ~ , ,,,.., _ _ m . . -. m , .. . , . . _ ._ ,,_,-_,.,_.,mm.. ..._, .v. , . _ ... _ , , _ - , . , , , . .m._...,m ,m.,.,%__.- - ~ . _ _ , , . . . . .
i Cale, No. L-001337 Rev. O Proj. No. 10248 012 Pago No.12 Case 2: 3x4.1 Channel Sublocted to Jet imolnnement t.oads
- Prenaration of inout to Stand Computer Model ,
, This model covers the following two configurations:
- 1. l.eak Test Assembly 39 EE located in the suppression pool (see CBI Dwg. No. 39 Rev. 6)
?. All 3" ASTM A36 leak chase channels in the drywell.
Joint coordinates are center line coordinates. Additionaljoints are provided so that stresses can be determined at the end of the fillets at each cortar of the channel. Member properties of the channel web and flanges are based on an effective wiJth of 1.0'f. Test couplings are not modeled for channels in the drywell because the design evaluation of the drywell chhnnels is governed by jet impingement loads which are defined in D.I. #35, Sketch JF 1 A on Page 2 2 7. The presence of a test coupling is not significant in the evaluation of "EE" assemblies because it is attached to a vertical channel which is not a highly loaded member in the assembly. Member Probertlee C3x4.1 Flanne Propertiet (Members 1. 2. 6. 71 b e 1.in t = 0.273.in AY =bt iZ r - lZ = 0.0016955'ind AY = 0.273 in 8 Note that Ax is calculated in the Stand program using the values of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Stand but are not used in the analysis. C3 4.1 Web Properties (Members 3. 4. 61 b 1 in t = 0.170 in A5bt IZ d 12 = 0.0004094 *in g Note that Ax is calculated in the Stead program using the values A = 0.1700 *in of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Stand but are not used in the analysis. ( CAL 13372.MCD -
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C:Ic. No L-001337 R:v. O Proj. N).10248 012 P ge No.13 Loads: Cntical Assembly for C3x4.1 Evaluation Review of CBI Dwgs. 32 Rev. 4 and 39 Rev. 5 indicates that all 3" leak test channels in the suppression pool have the inside leg of the channel shortened by 1/2" to accommodate attachment to the thickened liner embed plate. See Section A A on Dwg. 32, Section D-D on Dwg. 39 and the related table which give the *C" dimension of 1/2". The only exception to this is i.eak Test Ass'y EE on Dwg. 39 which has a *C" dimension of 0". This assembly is analyzed as a separate case since its specific configuration is more severe that those channels that have a C dimension a 1/2". The previous Calculation No.164 (D.1,33) identified the following criticalloads: Maximum Accident Pressure = 45 psi (Ref. 32. Table 1.1 1) and LOCA Poolswell Impact. Review of CBI Dwgs. 34 through 37, Rev. 3,7,3,6, respectively, shows that Ass'y EE is used at 8 locations: Four at El 679' 0" and four at El. 726' 0". (Dwgs 1D through 1G, Revs. 8,7,4,6 respective ly.) These elevations will be und to reduce the pootswell impact loads on these critical channels. As shown in Table 2 of D.I. 34, loads due to pool swell impact act on structures above the suppression pool located between El. 700' 2"(High water level in the suppression pool) and El. 718' 8"(Max. height of poolswell). Based on Table 2, none of the "EE" assemblies lie in the zone subject to Pootswell impact forces. Other forces acting on the Ass'y EE leak test channels are tabulated in the load combination table given on page 26 of Calc.164 (Ref. 33). After pool swellimpact, the next most criticalload combination is #8 which is jet implagement load. This load case governs the design of A36 channels in the drywell. Jet loads in the suppression pool are much smaller than in the drywell. The jet pressure on the basemat is a maximum of 33 psi and reduces to zero at El. 700' 2"(See Fig. 4 in D.l. 34). The related joint and member loads for the jet impingement load in the drywell are described below. After pool swell impact, the next most criticalload combination for channels in the suppression pool is Case #7 which applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi. Results of the Ass'y EE analysis for Load Combinations 7 are presented below. Results for the other 3" chantiels which have a "C" dimension = 1/2" and which are located in the poolswell impact zone are evaluated later using another Staad ill model(See Case 3 below). Review of CBI Dwgs. 288 through 291 and 294 through 297 Rev. 3,3,3,4,3,3,2,3 respectively, shows that 3x4.1 channels (ASTM A36) have been used as leak chas(, channels in the drywell. Channels in the drywell are not subject to hydrodynamic impact loads, therefore the criticalload for these channels is jet impingement. See load combination #8 in the load combination table given on page 26 of Calc.164 (Ref. 33). CAL 1337ZMCo
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Calc, No. L 0('1337 R;v. O Pr:J. No.10248 012 Pcg] No.14 Inomber Loads Member loads due to Load Combination #7 applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi.. The magnitude of the member load is equal to the pressure because the member width is 1". The vertical pressure is applied to members 1 & 2 and the horz. pressure is applied to Members 3 to 5. The load on members 6 and 7 is the same as on members 1 and 2 minus the drag loads. From Calc.164, Page 21, the LOCA drag load is 71.56 psi and the SRV drag load is 1.67 PSI. Net Load on Members 6 & 7: GX r (197.03 - 71.56 - 1.67). psi GX = 123.60
- psi Jet impingement loads o Members 3,4, and 6 ,
As shown on Pages 26 and 27 of Calc.164, Load Case 8 is the jet impingement pressure load of 467 lbshn acting on members 3,4. and 5 which represent the channel web. Note: See Page 25 for further d!scussion of jet loads in the containment drywell area. Joint LoaI.sI Member loads do not represent 100% of the pressure load acting on the channel because member length is based on center to center dimensions. Therefore length times member width will not completely represent the total surface area subjected to pressure loads. For this reason, Joint loads are used to apply the additionalload that acts on the m'ssing surface area. Joint loads for Load Combination 7 are applied to Joints 3 and 6. The magnitude is equal to the pressure times the missing surface area of the channel flange and web. Flange length = 1.41" Web length = 3" Length modeled in Stand = 1.325" Length modeled in Staad = 2,727 Effective width a 1.0" Missing surface area: 2 Aw 2 (3 - 2.727) idn Af = (1.41 - 1.325) in 1.0 in Aw is distributed to joints 3 and 6. therefore: Af = 0.0850 *in2 Aw Aw = 0.14 *in' CAL 13372.MCD
Cdc. No. L.001337 R:v, O Proj. No. 10248-012 Pcge No.15 i i f ! i I Pressure load for Jt .' in X & Y directons = 197.03 psi & .161.13 psi, respectively l I FX = 107.03 pol. Af FY = .161.13 pal Aw FX = 16.75'Ibf FY = -21.99 'lbf Pressure load for Jt. 6 in X & Y direct 6ons = .123.8 pel & .161.13 psi, respectively FX 's 123.8 pol Af FY = -161.13 pol Aw I l FX = -10.523 albf FY = -21.99 *lbf l Evaluate Joint Force at Joints 3 & 6 due to Jet Pressure = 467 pal 4 FY * -467 psi Aw FY = -63.75 'Ibf i i Thermal Load: As stated in the previous Calculation No.164 (D.I. 33) the channelis analyzed with and without the effects of " temperature. The temperature change for the pootswell load condition is 76 deg. F, and the change for Jet Impingement Load is 30 dog. F. The 30 dog. change is accomplished by using a load factor of 0.4 in Load Combination 5. i
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C:le. N). L-001337 R:v. O Pr:J. No.10248 012 Pcge No.16 Material Yield Stronath The following documents related to Vendor Specification 2534 are provided in Attachment 4 of the calculations: I j 1. Stores and Metal Verification Summary & Supplement Sheets, File # 5.1 CCM
- 2. Material Heat Number Sheet, File No. 8.16 2, Document #18
- 3. Certifed Material Test Reports. File No. 5.2 These documents identify the following materiai heats for the 3x4.1 channels in Assembly 39-EE in the suppression pool:
Min Specified Actual Ultimate Heat No. Yield Strength Strength Per CMTR ; 40079 30,000 pal 85,350 40489 45.000 pel 89.200 For tne cases shown above, design yield strength is equal to the min, specifed yield strength = 30 kal. As permitted in Ref. 3, Section Ill.2.a. a 10% increase in the design yield strength is used to account for strain rate I t?!ects associatov . . dynamic effects of 1.OCA loads such as jet impingement and pootswell impact loads. Tivelms, the ellowable stress for channels in the suppression pool is: Fb1 = 0.951.130.0.ksi Fb1 = 31.35 *ksi The CBI CMIR documents identify the following material heats for the ASTM A36 3x4.1 channels in drywell; Min. Specified ActusiTensile Heat No. Yield Strength Strength Per CMTR 93063 36.000 psi 68.100 psi 94541 36,000 psi 72,300 psi Design yield strength is equal to the min. specified yield strength = 36 ksl. In addition, a 10% increase in min. specified design yield strength is used as permitted to account for strain rate effects associated with jet impingement loads. Therefore, the allowable bending stress for channels in the drywellis: Fb2
- 0.951,136.0 ksi Fb2 = 37.62 *ksi CAL 1337tMCD
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i C:lc No. L 001337 Rev. O Proj. N3.10248-012 Page No.17 I ! Results of Stand til Analvels: Results of the analysis are shown in Attachmern B. For the 3x4.1 channels in Assembly 39 EE in the suppression pool, the maximum member stress due to hydrodynamic load (LC #1) occurs in member 4 (12.57 ksl), ard Fbi is the allowable stress. For A33 channels in the drywell, the maximum member stress due to jet impingement occurs in member 4 (35.77 kal). ; and Fb2 is the allowable stress. Assembly 39 EE ASTM A 36 Channels in Drywell l Mar 21
- g Mar 21a
- g Mar 21 = 2.49 Mar 21e = 1.05 t Check weld based on reactions at Joints 1 and 8 (Max reaction occurs in L.C. #5).
Weld force: fw = (.20382+ .7005 2s y . kip fw = 0.73
- kip t
Weld Allowable: Fw = 0.707 21 kol gin r Fw = 2.78 + kip Mar 22 = h Mar 22 = 3.82 CAL 1337Z.MCD
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f l C:le. No. L 001337 R:v. O Proj. No. 10248 012 PagaNo.18 i i Case 3: an4,1 Channel With Short Les ; Prenaration of inout to Staad Computer Model.
, This model covers all 3x4.1 channels billed on CBI Dwg. Nos. 32 (Rev 4) and 39 (Rev. 5) other than those :
Identified as Leak Test Assembly 39-EE (See Case 2). All Case 3 channels have one leg shortened by 1/2" as , shown on Dwgs. 32 (Section A A) and 39 (Section D-D). [ Joint coordinates are conter line coorr inates. Additionaljoints are pivvided so that stresses can be determined at the end of the fillett, at each comer of the channel. Member properties of the channel web and flanges are based on an effective width of 1.00". Test couplings are not modeled for this configuration because Ass'y A (Dwg. 32) and Detall E (Dwg. 39) show that test couplings on these assemblies are always mounted on a verticalleg of the assemb! /. The vertical leg is not the critical member for pool hydrodynamic loads becat.se i these impact l > ads primarily act in the vertical direction. Thus, the presence of a test coupling in the suppression pool is only significant when it is attached to a horizonttti channel. Altmber Propertltg , Member properties are the same as those used in the Case 2 model. MaterialYleid Stronath The following documents related to Vendor Specification 2534 are provided in Attachment 4 of the calculations: , t 1, Stores and Metal Verification Summary & Surplement Sheets, File # 5.1 CCM
- 2. Material Heat Number Sheet, File No. 8.16 2, Document #18 V Certified Material Test Reports, File No. 5.2 These documents identify the following material heats for the 3x4.1 channels billed on CBI Dwgs. 32 and 39.
Min. Specified Actual Ultimate Heat No. Yield Strength Strength per CMTR 30384 45,000 psi 91,400 - 40079 30,000 psi 85,350 40489- 45,000 pal- 89,200 f CAL 13372MCD l l l
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Heat number 40079 has the lowest yield strength (Fy = 30 kol, so the allowable stress is: [ t. Fb1 = 0.951.130.0 ksi
- i Fb1 = 31.35 *ksi 9
7 kS9d91 Critical Assembly fer C3x4.1 Evaluation: Review of the above specified CMTRs shows that channels from heat no. 40079 have a yield strength of 30 kel. Based on previous calculations, it is necessary to reexamine the poolswell impact loads acting on the channels from heat no,40079. As shown in Table 2 of D.l. 34, loads due to pool swell impact act on structures above the suppression pool located between EL 700' 2" (High water level in the suppression pool) and El. 718'-8" (Max. height of poolswell). Therefore, Cf)I dwgs. 34 through 37 (Revision Nos. 3, 7, 3. 6, respectively) were reviewed to identify all'32'- and , '39'-Series channel assemblies that fall within the poolswell zone. The following four assemblies were found to be subjected to significant poolswellimpact loads: 39 A,39 M,39-N,39-FF. Of these four, only Assembly 39-M had horizontal channels from heat no. 40079. The center line elevation of 39-M is 703' 6"(See CBI dwgs.1E and 1F, Revs 7 & 4, respectively). Due to'the poolswell phenomenon, the most critical load condition occurs when the lower flange of the bottom channel is impactsd due to poolswell. This elevation corresponds to 702' 11 1/4". However, conservatively, poolswell for this case will be based on El. 704'-0". From Table 2 of D.I. 34, the poolswell impact at 704'-0" is 421.9 psi (A value of 422 pal will be used in this calculation. LOCA pressure is added to yield a total applied pressure of 422 -
+ 45 = 467 psi.
Other forces acting on Ass'y 39 M are tabulated in the load combination table given on page 26 of Calc.164 4 (Ref. 33). As stated earlier, jet impingement load is not a governing load in the suppression pool. Therefore,
. after pool swell impact, the next most critical load combination for channels in the suppression pool is Case #7_
which applies a vertical pressure of 197.03 psi 2.nd horz. pressure of 161.13 psl. The Staad model for this third configuration is analyzed for a total of nine load cases as described below: Case 1. This case represents poolswellimpact on the lower flange of the upper channel of Ass'y 39-FF. Case 2., This case represents poolswell impact on the lower flange of the lower channel of Ass'y 39-FF. This case combined with thermal load produces the highest stresses and is used to qualify all channel assemblies :
' built using heat numbers other than 40079.
Case 3. This case represents poolswellimpact on the lower flange of the lower channel of Ass'y 39-M. CAL 13372.MCO .. l i J.i . - -.s -_._,,_1 _ a,,._ ,m. _ _ _ _ . ,,, , .-._m -.. - . . . . . - . . .
Calc. No. L-001337 R:v. O Proj. No. 10248-012 : Pcg3 No.- 20 l Case 4. This case represents Case #7 which applies a vertical pressure of 197.03 psi and horz. pressure of l 161.13 psi..
~
Case 5. This case represents thermal effects due to accident temperature. Cases 6,7, B, and 9 are the same as cases 1,2,3, and 4 combined with the appropriate thermal effects. Member Loads Load Case 1 , Member loads due to poolswell + accident pressure acting on members 1 and 2. The magnitude is equal to the pressure times the member width. Ibf Uniform load, Members 1 and 2: GX = (643 + 45) 1.07 GX = 680
- Member loads on Members subjected to Accident Pressure = 45 pel Uniform load, Members 3 to 7: GX1 451.00 GX1 = 45.00
- Joint Loads Joint loads are applied to Joints 3 and 6 to account for the additional poolswell load or accident pressure that acts on surface area not represented by member length times width. The magnitude is equal to the pressure times the missing surface area of the channel flange and web.
Flange length = 1.41" Web length = 3" Length modeled in Staad = 1.325" - Length modeled in Staad = 2.727
. Effective width = 1.0" CAL 1337Z.MCD
Calc. No. L-001337 R:v. O Proj. N3.10248-012 Pcg3 No. 21
~~'
Missing surface area: 2 Aw = ( 3 - 2.727)Mn Af = (1.41 - 1.325) in 1.0 in Aw is distributed to joints 3 and 6, therefore: Af = 0.0850 *in2 Aw Aw = 7 Aw = 0.14 *in t Pressure load for Jt. 3 in X & Y directions = 688 psi & 45 psi, respectively FX = 688 psi Af FY = -45 psi Aw FX = 58.48'Ibf FY = -6.14 'Ibf Pressure load for Jt. 6 in X & Y directions = -45 psi FX = -45 psi Af FY = -45 psi Aw FX = -3.825 'Ibf FY = -6.14 'Ibf Load Case 2 Load Case 2 is the same as Load case 1 except that poolswellimpact pressure acts on Members 6 and 7 and Joint 6 instead of members 1 and 2 and Joint 3. Therefore, the loads for these members and joints are just the reverse case of Load Case 1. Load Case 3 Load Case 3 represents poolswell impact on the lower flange of the lower channel of Ass'y 39-M. Member loads due to poolswell + accident pressure act on members 6 and 7. The magnitude is equal to the pressure times the member width. As stated earlier, the center line elevation of 39-M is 703'-6"(See CBI dwgs.1E and 1F, Revs. 7 & 4, respectively). Due to the poolswell phenomenon, the most critical load condition occurs when the lower flange of the bottom channelis impacted due to poolswell. This elevation corresponds to 702'-11 1/4". However, consertatively, poolsweh for this case will be based on El. 704'-0". From Table 2 of D.l. 34, the poolswell impact at 704'-0"is 421.9 psi (A value of 422 psi will be used in this calculation. LOCA pressure is added to yield a total applied pressure of 422 + 45 = 467 psi. CAL 13372.MCD
i Calc. No. L-001337 R;v. O Proj. No. 10248-012' Pega No. 22 E Uniform load, Members 6 and 7: GX = (422 4 45).1.0 GX = 467
- i Member loads on members subjected to Accident Pressure = 46 pel Uniform load, Members 1 to 5: GX1 :: 451.00 4
GX1 = 45.00' Joint Loads: 4 Joint loads are the same as for load case 2 except for 'olnt 6. Pressure load for Jt. 3 in the .X direction = 467 psl: FX
- 467 psi Af FX = 39.69 lbf Load Case 4: Alternate Load Case 7 (Calculation 164)
As shown on Pages 26 of Calc.164, there is an alternate Load Combination #7 which applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi.. The magnitudes of the member loads and the joint loads are the same as Case 2 given on page 14 of this calculation except that the loads for these members and joints are , just the reverse case, i.e. ,the maximum pressure load (197 03 psi) acts on Members 6 and 7 and Joint 6 instead of Members 1 and 2 and Joint 3. 4 4
Cde. No. L-001337 Riv, O Prcj, No. 10248-012 Pcg3 No. 23 , Load Case 5: Thermal Load As stated in the previous Calculation No.164 (D.l. 33) the channelis analyzed with and without the effects of temperature. Since jet impingement load in the suppression poolis not a governing load condition, the temperature charige corresponding to the poolswell load condition of 76 deg. F is used in the analysis. Loads Cases 6. 7. 8 and 9: These cases are the same as Cases 1,2,3, and 4 combined with thermal effects. Results of Stand hl Analysis: Results of the analysis are shown in Attachment C. Review of member stresses shown on Page C7 shows that design of channels made from Heat No. 40079 is govemed by Load Combination 8 (f8 = 26.17 ksi), and design . of all other 3x4.1 channels covered in Case 3 is governed by Load Combination 7 (f7 = 39.04 ksi). f8 = 26.17 ksi f7 2 39.04 ksi Procedure for Adiustino Desian Yield Stress The CMTR for heat no. 40489 reports a yield of 51.6 ksi and an ultimate of 89.2 ksi. The yield meets the ASTM specified minimum of 45 ksi for cold-finished material, but the ultimate value is 0.8 ksiless than the minimum value of 90 ksi. In order to maintain the ASTM specified stress margin of 45 ksi between yield and ultimate, the design yield stress is adjusted to meet the following criteria: Fy max 5 Fu - 45 ksi. 4 Allowable Stress: As stated previously, the 3x4.1 channel covered under this Case 3 analysis were manufactured from the following three heat numbers: Min. Specified Ultimate Strength Heat No. Yield Strength from CMTR : 30384 45,000 psi 91,400 > 90,000 0.K. 40079' 30,000 psi 85,350 > 75,000 OK 40489. 45,000 psi 89,200- Revised Fy = 89,200 - 45,000 a 44,200
' The heat number corresponding to Load Cases 3,4,8, and 9 is 40079, so Fy8 = 30.0 ksi.
Due to the adjusted design yield strength, Heat No. 40489 has the next lowest effective yield strength and controls for Load Case 7, so Fy7 = 44.2 ksi CAL 1337Z MCD
C:Ic. No. L-001337 R:v. O Proj. N2l 10248-012.- Pcg3 No. 24 The corresponding allowable stresses are: - 4 Fb8
- 0.951.130.0 kal Fb7
- 0.951.144.2 ksi Fb8 = 31.35 +ksi Fb7 = 46,19'ksi The resulting design margins are:
Fb7 Mar 31 = Fb8 Mar 31a p-f8-Mar 31 = 1.20 Mar 31a = 1.18 1 Check weld based on reactions at Joints 1 and 8 (Max. reaction occurs in L.C. #2 at Jt. 8): 4 Weld force: fw : (.59242 + .10642 ) kip fw = 0.60
- kip z
Weld Allowable: Fw = 0.707 21 ksi. in Fw = 2.78 kip
- Mar 32 . =
Mar 32 = 4.63 CAL 13372.MCD -
. ~ . - . . - -. . - - - - - - - - - - - - _ - . - .
Calc. No, L 001337 Rsv.1 Proj. No. 10248-012 Pago No. 25 l Discussion of Jet Impinnement Loads on Liner Leak Chase Channels inside Containment Drvwell In the previous calculation (D.I. 33), the main purpose of he analysis was to analyze channels subject to hydrodynamic impact loads in the suppression pool. The jet impingament forces were not part of the goveming load case in the suppression pool. This calculation includes qualification of ASTM A36 channels in the drywell, so a study is included here to document that jet loads act on the web of the leak chase channels and do not apply signit.0 ant loading to the channel flanges. The UFSAR (D.I. 24), Section 3.6, Table 3.6 8 provides a list of postulated pipe breaks inside the containment. Two types of breaks are postulated: Circumferential and Longitudinal. Circumferential breaks cause Jets to develop parallel to the axis to the pipe, whereas Longitudinal brosks cause jets which act perpendicular to the axis of the pipe. Review of Figs. 3.61 through 3.6-15 shows that large bore high pressure piping inside the containment is close to the liner only at the containment wall penetration locations and these are always horizontal pipe runs. Thus, Circumferential breaks on these pipe runs govem the jet loads on the liner channel web while longitudinal breaks govem the load on the flanges of the channel. Vertical pipe runs are always away F from the containment liner plate.. Therefore, a jet force would apply a significant force to the channel flanges only if there is a postulated longitudinal pipe break at or very close to the containment wall pipe penetration. Figs. 3.6+1 through 3.615 and Table 3.6-8 can be used to determine the approximate location of all longitudinal breaks inside the containment. Based on this information, the closest longitudinal breaks to the liner channels are the break numbers C214 and C214S shown in Figs. 3.6 3 and 3.6-6, respectively Per Table 3.6-8, the pipewhip restraints which have been designed to restrain the pipe from whipping due to the postulated breaks at C214 and C214S are R-72 and R 88, respectively. These restraints are shown on LaSalle Dwg. S-384, Rev. U (01. 25). Using the dimensions shown on the plan view, the radial distance, D1, from the RPV center line to ] these restraints is obtained as: l H1 : 27 ft - 7.125 in H2 : 3 ft in D1 : 'Hl 2+ H2 2 45 A1:acosl"3lI\6 D1 e 27.84'ft A1 = 82.43 *deg i : 210 deg - A1 0 = 127.57 deg The elbow at which the break occurs is located funner from the liner than the restraint. Therefore, the location of the restraint conservatively can be used as the break location. From the sketch on Page 25.1, the distance, X, from the pipe break to the drywell liner is determined as shown on Page 25.2 4 CAL 13372.htCD i a J
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- Res p I Date Safety. Rela'ed Non-Safety Related Page f > , / of Client Propered by Date Project Reviewed by Date Proj.No. l$ j Y[ ~ / 7 Equip. No. Approved by Date
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C Ic. No. L-001337 R;v.1 Proj. No. 10248-012_ P:ge No. 25 2. i Radius to the drywellliner: R = 42 ft . _ _ , Angle B = asin - sin (f) B = 31,69'deg -
- a = 180 deg - T - D a a 20.74'deg X
- R *i"( )
sin (r) X = 18.77'ft According to NUREG \CR-2913 (D.I. 28), it can be conservatively stated that pipe break forces are not significant at distances greater than 8 pipe diameters from the pipe break Iccation. For the Main Steam line with a diameter of 26 in, this distance is: DIA 2 26-in D8 : 8 DIA D8 = 17.33'ft The calculated distance to the liner is 18.77 ft which is greater thal D8. Therefore, it can be concluded that none of the longitudinal breaks inside the containment will apply significant jet loads on the ASTM A36 liner leak ,- chase channels in the containment drywell. 4 I 4 4 CAL 1337Z.MCD _ _ . ~ . __ --
Calc. No. L-001337 Rsv.p'2 Proj No. 10248-012 Pago No. 26 c... i i n mw _
SUMMARY
AND CONCLUSIONS * - - - In response to PlF # L1997 06237, three channel configurations have been evaluated in the suppression pool and the drywell. .This assessment has been performed using minimum specified material yield strength as determined from vendor supplied certified material test reports (CMTRs). In addition, the design yield strength is reduced, if necessary, to maintain a minimum of 45 ksi between yield and ultimate. Results are given in terms of the margin factor which is defined as the ratio of allowable stress divided by actual stress. All margin factors are greater than 1.0 thus demonstrating that all leak chase channels have been found to meet the acceptance criteria and are th'Js able to serve as part on the containment pressure boundary. Margin factors are summarized below. Channel Section Weld Case 1: C 2 x 1 x 3/16 Mar 11 = 1.08 Mari2 = 5.56 Case 2: Assembly 39-EE Mar 21 = 2.49 Mar 22 = 3.82 Drywell Channels Mar 21a = 1.05 Case 3: C3x4.1, Heat No. 40079 Mar 31 = 1.20 Mar 32 = 4.63 All other C3x4.1 in Mar 31a = 1.18 Suppression Pool CALt337Z MCO l
Calc, No. L 001337 Rev. 2 Proj. No. 10364-004 Page No 27 Purpose / Objective (Rey, 2) To perform a design assessment of the containment liner leak chase system associated with the downcomer bracing embedment plates in the suppression pool. This assessment is required to support Licensing Event Report LER 97 030-00 which relates to the use of the liner leak chase system as part of the Containment pressure boundary. Methodoloav and Acceptance Criteria This calculation shall be performed in accordance with the applicable documents listed as Design inputs listed on Pages 3,4 and below. The acceptance criteria used for this assessment is given in Subsection 4.3.2 of the LaSalle Dese;n Assessment Report (DAR)(D.I. 32). Applicable load combinations are defined in Table 4.3-2 of the DAR. Allowable stresses for load combinations 1 through 3 are per the 1969 AISC Specification. As explained in the previous revisions of this calculation, the goveming load combinations for structural elements in the suppression pool are those which involve the various hydro-dynamic LOCA loads. For these load combinations, the allowable stress is limited to 0.95 Fy. As permitted in Ref. 3, Sect. Ill.2.a. a 10% increase in minimum specified yield strength will be used to account for strain rate effects associated with impact loads. The allowable stress used for weld assessment is 21 ksi for all load combinations. Assumptions There are no unvenfied or unconservative assumptions used in th!s calculation. Design input See Pages 3 and 4 for D.I.1 trWugh D.I. 35. 36)1 CBI Shop Drawing No.107, Rev. 2. LaSalle Specification J 2990,"Downcomer Bracing Work" 37)1 CBI Shop Drawing No.108, Rev. 2. LaSalle Specification J-2990,"Downcomer Bracing Work" 38)1 CBI Shop Drawing No.111, Rev.1, LaSalle Specification J-2990,"Downcomer Bracing Work" 39)1 CBI Shop Drawing No.114, Rev. 3, LaSalle Specification J 2990, "Downcomer Bracing Work" 40)1 CBI Shop Drawing No.123, Rev.12, LaSalle Specification J 2990,"Downcomer Bracing Work" 41)1 CBI Shop Drawing No.124, Rev. 2, LaSalle SpecVication J 2990,"Downcomer Bracing Work" 42)1 CBI Shop Drawing No.129, Rev. 3, LaSalle Specification J 2990,"Downcomer Bracing Work" 43)1 CBI Shop Drawing No.137, Rev. 2, LaSalle Specification J 2090,"Downcomer Bracing Work"
- 44) X LaSalle Specification J-2990,"Downcomer Bracing Work," Amd. 2,72778.
References See Page 4 for References 1 through 3. L,1337R2.MCD
Calc. No. L 001337 Rsv. 2 Proj No. 10364-004 Ptge No. 28 CALCULATIONS As stated above, the purpose of Rev. 2 of this calculation is to perform a design assessment of the containment liner leak chase system associated with the downcomer bracing embedment plates in the suppression pool. (See CBI drawings hsted as D.I. Nos. 36 through 43.) The objective is to show that stresses under the critical load combinations meet the acceptance criteria so the plates and welds which form the leak chase can quahfy to serve as part of the Containment Pressure Boundary. In those cases where the leak chase cannot be quahfied, the air spaces must be unplugged so that the leak chase no longer serves as part of the containment pressure boundary. The leak chase system consists of 3/8" Stainless Steel plates that form an air space which ccn be pressurized to test the weld between the containment liner plate and the downcomer bracing embed plates. As stated previously the controlling loads acting on the leak chase plates are the hydrodynamic LOCA loads which are defined in D.l. # 34. As stated above under Methodology, acceptance of the leak chase system as part of the pressure boundary requires stresses to meet the allowable stress of 0.95 Fy under accident load combinations. This calculation will show that the leak chase for downcomer bracing embeds below El. 700' meets the acceptance enteria and are quahfied to serve as part of the containment pressure boundary. On the other hand, hydrodynamic loads increase greatly above El. 700'such that the leak chase for downcomer bracing embed plates above El. 700* cannot be quahfied for use as part of the pressure boundary, in this case, the plugs should be removed from the test couplings for the eighteen embed plates above El. 700'so that they no longer terve as part of the containment pressure boundary. The following sention describes the STAAD computer model which has been used to evaluate the hydrodynamic pressure load capacity of the leak r hase for the downcomer bracing embed plates. The geometric properties of the STAAD model are based on the properties of the embed plates located most closely to the elevation where the pool swell impact load reaches itr maximum value which is El. 709' 4" (See D.1. Nos. 34 and 36 to 43 ) L 1337R2 MCD
1 Cric. No. i.-001337 Rcv. 2 Proj. No. 10364-004 Pege No. 29 [ I sTAAo comout.r Analysis Model 6 --
- 2 6
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Calc, No L-001337 Rev,2 . Proj, No. 10364 004 Pcga No. 30-Analysis of Peak Pressure Load Capacity _ _ , . i The purpose of the STAAD analysis is to determine the vertical pressure load which produces the maximum allowable stress of 0.95'1.1'Fy = 31,35 kai where Fy = 30 ksi for SA 240 Type 304 per Spec. J 2990 (D.I. 44). The horizontal pressure for this analysis is set equal to the LOCA design basis accident pressure of 45 psi. Results of STAAD Analysis Through an iterative process, the allowable vertical pressure on the leak chase which meets the above stated acceptance criteria has been found to be 295 psi. This pressure produces a dress of 31.35 ksiin Member 3 of the STAAD model. (See page 6 of Attachment E). The maximum allowable hydrodynamic pool swellimpact pressure is then found to be equal to 295 45 = 250 psi, where 45 psiis the LOCA design basis pressure. The next step is to use the load data in Table 2 on Page 47 of D.I. 34 to determine the elevation where the pool swellimpact pressure exceeds the allowable pressure of 250 psl: As shown in Table 2, the impact pressure exceeds 250 psi between Elevations 702'X and El. 717*-0", Review of D.1, Nos. 40 and 41 shows that there are 18 downcomer bracing embed plates that fall within this range. Based on this analysis, it is concluded that the leak chase for these 18 embedment plates do not meet the acceptance criteria and thus do not qualify for use as part of the containment pressure boundary For this reason, the plugs for these specific portions of the leak chase should be removed so that the leak chase no longer serves as part of the containment pressure boundary,
- All remaining downcomer bracing embedment plates are below El. 700', Therefore, the leak chase for these
- embedments are below the surface of the suppression pool and will be subjected to drag and lift loads as
! described in D.1, # 34. Pool Swell Drag and Lift Loads on Leak Chase Plates Below El. 700'-0" As stated in Section 3.5.3 of D.I. # 34, the standard drag pressure on plates. Ps, is determined from Fig 12 of , , D.I. # 34, and the acceleration drag load, Pv is determined from Fig.14: Ps max. = 15.4 psi Pv = Fv
- T = 0.57 lbf/in3
- 3/8" = 0.214 psi where Fv is the acceleration drag load from Fig.14 in ibflin3 and T is the plate thickness (in).
The total drag pressure is: Pd = Ps + Pv = 15.4 + 0.2 = 15.6 psi < 250 psi O.K. L,,1337R2.MCD f .
Calc. No. L-001337 Rev. 2 Proj. No. 10364-004 Paga No. 31 Drag Loads due to Fallback: __ Per Section 3.5.7 of D.I. # 34, the standard drag pressure on plates, Ps, is determined from Fig. 28, and the acceleration drag is determined from Fig. 30 as follows: Ps max. = 45.23 psi Pv = Fv
- T = 0.3226 lbf/in3
- 3/B" = 0.121 psl where Fv = fan = 200 lbs/ 620 in =3 0.3226 lbf/in3 (Fv is the acceleration drag load from Fig. 30 in Ibflin3 and T is the plate thickness in inches.)
The tctal drag pressure " Pd = Ps + Pv = 45.23 + 0.12 = 45 35 psi < 250 psi O.K On the basis of the large stress margin and the analyses performed earlier in this calculation, the leak chase welds are acceptab4 based on engineering judgment. Therefore, it is concluded that the downcomer bracing embedment plate leak chase system located below El. 700'-0"in the suppression poolis subjected to hydrodynamic pressures that are less than the allowable of 250 psi. Therefore, the embedment pl#e leak chase below El. 700' 0" and the associated welds meet the stress acceptance criteria necessary to qualify for use as part of the containment pressure boundary. Evaluation of Leak Chase for Bolt Cover Assembly (Ref. D.l. Nos. 39 and 42) As shown in D.l. # 39, the leak chase for the bolt cover assembly is fabricated from 6" dia. seamless schedule 40 pipe, and the total length of the assembly, L, is 8". From D.I. # 44, the pipe material is SA-312, Type TP 304 which has a yield, Fy, of 30 ksi. The pipe section modulus, Sx, is 8.50 in3 and the outside dia. (OD)is 6.625" (D.I. # 3). From Table 3 of D.l. #34, the maximum pool swell impact pressure, P, is found to be 48.88 psi. Calculate Bending Stress, fb, due to Pool Swell Impact Load: P : 48.88 psi L :8in OD = 6.625-in Fy = 30-ksi Sx : 8.50 in 3 Mx - OD P 2 Mx = 1.036104 'in Ibs 6:b Sx fb = 1.22 aksi 6 IC = E5$UFy IC = 0.04 <1.0 O.K On the basis of this very low IC value, the leak chase welds are acceptable based on engineering judgment. Therefore, the leak chase for the downcomer bracing embedment plate bolt cover assemblies at all elevations within the wetwell and the associated welds meet the acceptance criteria. L.,1337R2.MCD
. . - - ~ _ - - - . . - - . . - . - - - - . . . - . - , _ . . .-
i
- Calc, No, L 001337 Rev. 2 Proj. No. 10364-004 Paga No,32 .
- FINAL.
+
i g Summary and Conclusion (Revision 2 only) , _ _ . Revialon 2 of this calculation covers the design assessment of the containment liner leak chase system associated with the downcomer bracing embedment plates in the suppression pool. The following conclusions can be drawn. , l
- 1. The containment liner leak chase system associated with the downcomer bracing embedment plates is !
located in the suppression pool between Elevations 681' and 710'. The leak chase located abovs El 700* is > subjected to pool swellimpact pressures greater than the allowable of 250 psi. Therefore, this portion of the leak chase does not meet the established criteria and therefore cannot be considered to serve as part of the containment pressure boundary. The plugs for this portion of the leak chase should be permanently removed.
- 2. The leak chase located below El. 700' is subjected to pool swell drag and fallback presnures less than the allowable of 250 psi. As a result, this portion of the leak chase does meet the accepts ice criterion, and therefore, this portion of the downcomer bracing embodment leak chase and the associated welds are considered acceptable for use as part of the containment pressure boundary,
- 3. The Leak Chase for the Bolt Cover Assembly has been evaluated for the maximum hydrodynamic pool swell impact pressure within the suppression pool and has been found to meet the acceptance criteria by a large margin. Therefore, the leak chase for Bolt Cover Assembly and the associated welds are considered acceptable for use as part of the containment pressure boundary.
This assessment has been performed to support Licensing Event Report LER 97 030 00 which relates to the use of the liner leak chase system as part of the Containment pressure bnundary. See Page 26 fCr the Summary and Conclusions relating to Revisions 0 and 1 of this calculation.
- L 1337R2.MCD
t Calculation L-001337, Rev. 0. Project No. 10248-012- Attachment A Page A1 of 7 l PAGE NO. 1- .; ! S T A A D - III Revision 20.2
* . Proprietary Program of. *
- Research Engineers, Inc.- * :
i
- OCT 22, 1997 *
} Date= j
- Time- 9: 5:13 * '
USER ID: SARGENT.& LUNDY ENGRS ! 5
- 1. STAAD PLANE 2XIX3/16 CHANNEL & TEST PLUG !
- 2. INPUT WIDTH 72 ;
- 3. UNIT INCHES POUND
- 4. JOINT COORDINATES 5, 1 0. 0 ; 2 0. 7394; 3 0, .9063; 4 .1669 .9063; 5 1.6456 .9063
- 6. 6 1.8125 .9063; 7 1.0125 .7394; 8 1.8125 0.
- 7. 9 0.5475 .9093; 10 1.264 .9063; 11 .5475 2.33; 12 1.264 2.33 8 MEMBER INCIDENCES
-9.112;223;334;449;556;667;778
- 10. 8 9 10; 9 10 5; 10 9 111 11 11 12; 12 10 12
- 11. MEMBER PROPERTY AMERICAN
- 12. 1 TO 9 PRI IX .1 IY 8.E-4 IZ 1.65E-3 AY .5625 AZ .3 YD .1875 ZD 3.00
-13.1011 12 PRI IX .1 IY 4E-4 IZ 3.582E-4 AY .1488 AZ .1 YD .17 ZD .875
- 14. MEMBER RELEASE
- 15. 10 12 START MZ
- 16. CONSTANTS
- 17. E STEEL ALL
- 18. POISSON STEEL ALL
- 19. DENSITY STEEL ALL
- 20. BETA 0. ALL
- 21.
- STAINLESS STEEL
- 22. ALPHA 99E-7 ALL
- 23. SUPPORTS
- 24. IL8 PINNED
- 25. LOAD 1 LC 4,5,7 126. JOINT LOAD 127. 3 FX-193.4 FY -12.65
- 28. 6 FX -12.65 FY -12.65.
- 29. MEMBER LOAD
-30, 1 2 UNI GX 2064.
31.f3 4-5-9 UNI GY -135.
- 32. 6 7 UNI GX -135.
.33. 8 UNI GY -95.6
- 34. 10 UNI-GX-82.14-
- 35. 11 UNI GY -39.4
- 36. 12 UNI GX -39.4 37.-LOAD 2 THERMAL'
-38. TEMP LOAD
- 39. 3 4 5 8 9 11 TEMP 76.
- 40. LOAD COMB 3
- 41. I 1. 2 1.
4 Calculation L-001337, Rev. O. Project No.10248-012 ' Attachment A Page A2 of 7- : 2X1X3r16 CHANNEL & TEST PLUG' -- PAGE NO. 2
- 42. LOAD LIST ALL,
- 43. PERFORM ANALYSIS P R 0 B-L E M. STATISTICS d
?
N' UMBER OF JOINTS / MEMBER + ELEMENTS / SUPPORTS = 12/ 12/ 2 ORIGINAL / FINAL BAND-WIDTH = 5/ 2 TOTAL PRIMARY LOAD CASES = 2,-TOTAL DEGREES OF FREEDOM = 32 SIZE OF-STIFFNESS MATRIX = 288 DOUBLE PREC. WORDS _ t
~
REQRD/ AVAIL. DISK SPACE = 12.02/ 1069.5 MB, EXMEM = .1.02 MB
++ PROCESSING ELEMENT STIFFNESS MATRIX. 9: 5:14 9: 5:14
_i
++ PROCESSING GLOBAL STIFFNESS MATRIX.
++ PROCESSING TRIANGULAR FACTORIZATION. -9: 5:14
, ++ CALCULATING JOINT DISPLACEMENTS. 9: 5:14 9: 5:14
++ CALCULATING MEMBER FORCES.
- 44. PRINT JOINT DISP LIST 3 6 3
f 3 ---- l 9 f b' h.- 4 1 u-
-,.,_w.-w.r-r , e v v r -- e f _,+4
-- --cr=,' r M -e -+m\+ -r-wr---rrer- wm=-- rm er m4 - w~ -
Calculation L-001337, Rev. O Project No. 10248-012 Attachment A Page A3 of 7 2XIX3/16 CHANNEL 6 TEST PLUG -- PAGE No. 3 JOINT DISPI.ACEMENT (INCH RADIANS) STRUCTURE TlPE = PLANE JOINT LOAD. X-TRANS Y-TRAN'3 Z-TRANS X-ROTAN Y-ROTAN Z-ROTAW 3 1 0.00652 0.00002 0.00000 0.00000 0.00$00 -0.00293 2 -0.00068 .00000 0.00000 0.00000 0.00000 0.00056 3 0,00605 0.00002 0.00000 0.00000 0.00000 ~0.00237 6 1 0.00645 -0.00004 0.00000 0.00000 0.00000 -0.00358 2 0.00068 0.00000 0.00000 0.00000 0.00000 -0.00056 3 0.00713 -0.00004 0.00000 0.00000 0.00000 -0.00414
************** END OF LATEST ANALYSIS RESULT **************
- 45. PRINT MEMBER FORCES LIST 1 4 7 9 10 12
1
- Calculation L-001337, Rev. O Project No.10248-012 ? Attachment A Page A4 of 7
'2XIX3/16 CHANNEL 6: TEST PLUG' - - PAGE NO. 4 t
MEMBER END FORCES STRUCTURE TYPE = PLANE- , ALL UNITS ARE -- POUN INCH ;
. MEMBER -LOAD JT : AXIAL. SHEAR-Y SHEAR-Z TORSION MOM-Y' MOM-Z r
11" 1 1 - 446.67 1434.44 . 0.00 0.00 0.00 '0.00
- 2' 446.67 91.68 0.00 0.00 0.00 496.42
-2 1 0.00 -32.51 0.00 0.00 0.00 0.00 2 0.00' 32.51 - 0.00 0.00 0.00 -24.04 3 1 -
446.67 1401.93 0.00 0.00 0.00 . 0.00 2 446.67 124.19- 0.00 0.00 0.00 472.38 4 1 4 625.78 -486.00 0.00 0.00 0.00 -373.83 4 9 - 625.38 538.18 0.00 0.00 0.00 178.77 2 4 32.51 -0.26 0.00 0.00- 0.00 29.46 9 -32.51 -0.26 0.00 0.00 0.00 -29.56 3 4 658.29 -487.06 0.00 0.00 0.00 -344.36 9 - 657.89 538.44 0.00 0.00 0.00 149.21 J-7 1 7- 716.66 654.98 0.00 '0.00 0.00 447.39 8 -715.66 -555.17 0.00 0.00 0.00 0.00 2 7 0.00 32,51 0.00 0.00- 0.00 24.04 8 . 0.00 -32.51 0.00 0.00 0.00 0.00 ' 3 7 716.66 687.50 0.00 0.00 0.00 471.43 8 -716.66 -587.68 0.00 0.00 0.00 0.00 I' 9 1 10 690.17 ~629.97 0.00 0.00 0.00 192.75 5 -690.17 681.48 0.00 0.00 0.00 -442.97 f 2 10 32.51 0.00 0.00 0.00 0.00 29.46-5 -32.51 0.00 0.00 0.00 0.00 -29.46 3 10 722.68 -629.97 0.00 0.00 0.00 222.21 5 -722,68 601,48 0.00 0.00 0.00 -472.43 10 1 9 -46.06 66.85 0.00 0.00- 0.00 0.00 11 -46.06 49.85- 0.00 0.00 0.00 12.08 2 9 0.00 0.00 0.00 0.00 0.00 'O.00
- 11 0.00 0.00 l).00 0.00 0.00 -0.01
! 3 9 -46.06 66.84 0.00 0.00 0.00 0.00 11 46.06 49.85 0.00 0.00 0.00 12.07
~
! 12 1 10 74.29 -6.25 0.00 0.00- 0.00 0.00
-74.29 -49.85 0'.00 0.00 0.00 31.04 2- 10 0. 0 0 -- 0.00 0.00 0.'00 0.00 0.00
- 12 0.00- 0.00- 0.00 0.00- -0.00 0.01'
-3 - 10 -74.29' -6.24- 0.00- 0.00 0.00. 0.00
- 12 -74.29 1-49.85 ' 0.00 1) 00 0.00 31.05
-_ = ,
4 r e + e -Ae w .c w w +- -s 1
-e w ,<..+m- .>+ -,-r-w6-w e ww+v,se y - , --sr+-
- - ._.. . _ _ .. - . .... ... . .... - . . .-.. ._--~ - . . _ - . . . . . - - . - - - .
t r Calculation L-001337, Rev. O Project No. 10248-012 Attachment A. Page A5 of 7 2XIX3/16 CHANNEL & TEST-PLUG -- PAGE NO, $ 9 P Wup ' 4
* ************* END Of' LATEST ANALYSIS RESULT **************
- 46. PRINT SUPPORT REACTIONS i
I r e C s
=h+ e'ue6w ile +e._wf-Pe--g v " w v tvTe - 7 O- 4 - N e N+. Y f 7m '
Calculation L-001337, Rev. O Project No.- 10248-012 Attachment A. Page A6 of 7-
'2XIX3/16 CHANNEL & TEST. PLUG. -- PAGE NO. 6
_ __ SUPPORT. REACTIONS.-UNIT POUN INCH STRUCTURE TYPE = PLANE-JOINT.-14AD ' TORCE-X ~ FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z
-1 1 -1434.44 -446.67 0.00 0.00 0.00 0.00 2 32.51- 0.00 0.00 0.00 0.00 0.00 l 3 -1401.93 -446.67 0.00 0.00 0.00 0.00 l 8 1. -555.17 716.66 0.00 0.00 0.00 0.00 2 -32.51 0.00 0.00 0.00 0.00 0.00 3 -587.68 716.66 0.00 0.00 0.00 1.00
************** END OF LATEST ANALYSIS RESULT **************
- 47. PRINT MEMBER STRESSES LIST 1 4 7 9 l
t G
i i
- Chiculation L-001337, Rev 0: _
Project No. 10248-012 Attachment A Page A7 of 7
---PAGE NO. 7/ #FFt N Ar i_, '
2XIX3/16' CHANNEL & TEST PLUG j-
-MEMBER STRESSES
.ALL UNITS ARE POUN/SQ INCH ,
l MEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z
- 1 1 .0 794.1 T 0.0 0.0 794.1 2550.1 0.0 ,
1.00 794.1 T 0.0 28205.6 28999.7 163.0 0.0 i 2 .0 0.0 T 0.0 0.0 0.0- 57.8 0.0 1.00 0.0 T 0.0 1365.0 1365.8 57.8 0.0 3 .0 794.1 T 0.0 0.0 794.1 2492.3 0.0 t 1- 1.00 794.1 T 0.0 26839.8 27633.9 220.0 0.0 4 1 .0 1112.5 C 0.0 21240.2 22352.8 865.4 0.0 956.8 0.0 i 1.00 1111.8 C 0.0 10157.3 11269.0 4 2 .0 57.8 C 0.0 1674.1 1731.9 0.5 0.0 ' 1.00 57.8 C 0.0 1679.6 1737.4 0.5 0.0 3 .0 1170.3 C 0.0. 19566.2 20736.4 865.9 0.0 1.00 1169.6 C 0.0 8477.6 9647.2 . 957.2 0.0 7 1 .0 1274.1'C 0.0 25420.0 26694.1 1164.4 0.0 3 1.00 1274.1 C 0.0- 0.0 1274.1 987.0 0.0 0.0 2 .0 0.0 C 0.0 1365.0 1365.8 57.8 1.00 0.0 C 0;0 0.0 0.0 57.8 0.0-3 .0 1274.1 C 0.0 26785.8 20059.9 1222.2 0.0 1.00 1274.1 C 0.0 0.0 1274.1 1044.8 0.0 9 1 .0 1227.0 C 0.0 10951.5- 12178.4 1119.9 0.0 1.00 1227.0 C 0.0 25168.7 26395.7 1211.5 0.0 2 .0- 57.8 C 0.0 1674.1 1731.9 0.0 0.0 1.00 57.8 C .0. 0 1674.1 1731.9 0.0 0.0 3 .0 1284,8 C 0.0 12625.6 13910.3 1119.9 0.0 1.00 1284.8 C 0.0 26842.8 28127.6 1211.5 0.0
* * * * * * * * * * * * *
- END OF LATEST ANALYSIS RESULT * * * * * * * * * . + . . .
i
-48. FINISH
. . . . . . * . . * * * * * *
- E N D O F S T AA D- I I I * * * * * * * * * * * * * * *
'**** DATE= OCT 22,1997. TIME- 9: 5:15 ****
- For questions.on STAAD-III, contact: *
- Research Engineers,-Inc at
- Ph: (714) 974-2500 Fax: (714) 921-2543
+- h a
- ,-ec..
. Calculation L-001337, Rev. O Project No.'10248-012 Attachment B ~ Page B1'of 7 l t
PAGE No. 1-i
-* S T A A D - I!!
Revision 20.2 i
- Proprietary Program of *
- Research Engineers, Inc.
- FEP 30, 1997
- j
- Date=
Time = 10:42:16 l USER ID: SARGENT & LUNDY ENGRS 4 l
- 1. STAAD PLANE 3X4.19 CHANNEL 2.' INPUT WIDTH 72
- 3. UNIT INCHES POUND
- 4. JOINT COORDINATES U 5, 1 0. 0.; 2 0. 774; 3 0. 1.325 4 0.551 1.325; 5 2'176 1.325
} 6. 6 2.727 1.325; 7 2.727 0.774; 8 2.727 0.
- 7. MEMBER INCIDENCES 8.112;223;334;445;556;667;778
- 9. MEMBER PROPERTY AMERICAN
- 10. 1 2 PRI IX .1 IY .0016955 IZ .0016955 AY .~273 AZ .2 YD .273 ZD 1
- 11. 3 4 5 PRI IX .1 IY .0004094 IZ .0004094 AY .170 AZ .2 YD .170 ZD-1 c '12, 6 7 PRI IX .1 IY .0016955 II .0016955 AY .273 AZ .2 YD .273 ZD 1
- 13. CONSTANTS
- 14. E STEEL'ALL
- 15. POISSON STEEL ALL
- 16. DENSITt STEEL ALL
- 17. BETA 0. ALL i 18. STAINLESS STEEL
- 19. ALPHA 99E-7 ALL
, 20. SUPPORTS 21, 1 8 PINNED
- 22. LOAD 1 LC 4,5.7 t'
- 23. JOINT LOAD 24, 3 FX 16.75-FY -21.99
- 25. 6 FX -10.523 FY -21.99
- 26. MEMBER LOAD -
- 27. 1 2 UNI GX 197.03
- 28. 3 4'5 UNI GY -161.13 29, 6 7 UNI-GX -123.8 30.' LOAD 2 JET IMPINGEMENT
- 31. JOINT LOAD
- 32. 3 FY -63.75-
-33.'6 FY -63.75 *
- 34. MEMBER LOAD
, ; 35 - 3 4 5 UNI GY -467.0 3
-36. LOAD'3 THERMAL 37.' TEMP LOAD 4 38. 3 4'5 TEMP 76.
- 39. LOAD COMB 4
- 40. 1 1. 3-1.
41;' LOAD COMB 5 JET IMPINGEMT + THERMAL
- - - , .-. ,,r- --,ver - - -- -r- w-e + +---w-- ----:--b+-- - - -
- Calculation L-001337. Rev. 0 Project No.10248-012 Attachment B .Page B2 of _7 .
1 i 3X4.19 CHANNEL- ,-- PAGE NO.- : 2- . 42, 2-1. 3 0.40 .
/43.' LOAD LIST ALLl '
44.-PERFORM ANALYSIS -l s , PR0BLEM STATISTICS-1
~
NUMBER OF JOINTS / MEMBER +2LEMENTS/ SUPPORTS = 8/ -7/ 2
-ORIGINAL /TINAL BAND-WIDTH = 1/ 1
! TOTAL PRIMARY LOAD CASES = 3, TOTAL DEGREES Or FREEDOM = 20
-SIZE OF STIFFNESS MATRIX = 120 DOUBLE PREC. WORDS
-.REQRD/ AVAIL. DISK SPACE = 12.01/ 1070.8 MB, EXMEM = 1.02 MB 10 42:27
+4 PROCESSING ELEMENT STIFFNESS MATRIX.
j ++ PROCESSING GLOBAL STIFTNESS MATRIX, 10:42:17 i ++ PROCESSING TRIANGULAR TACTORIZATION.. 10:42:18
++ CALCULATING JOINT DISPLACEMENTS. 10:42:18 -
J ++ CALCULATING MEMBER FORCES, 10:42:18 P
- 45. PRINT JOINT DISP LIST 3 6 ;
a f 1 5-r. M
?
1 4 1 H r yir p w ,4 -y uss-e.s apgi++g y.- p. p -gw , m -"--
'dW
+4-+-.w - wew---i -r 4-d
i
- Omiculation L-001337, Rev. 0 .
Project No.10248-012 - Attachment B Page B3 of 7 1
-3X4.19 CHANNEL' -- PAGE NO. 3' l l 4
. _ . i
~
JOINT DISPLACEMENT-(INCH RADIANS) STRUCTURE TYPE = PLANE-
.In 4
JOINT LOAD -X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN , 3 1 0.00245 -0.00004 0.00000 0.00000 0.00000 -0.00200 l 2 0.00006 -0.00012 0.00000 0.00000 0.00000 -0.00251 , 3 -0.00102 0.00000 0.00000 0.00000 0.00000 0.00072 ! ! 4 0.00143 -0.00004 0.00000 0.00000 0.00000 -0.00129- - 5 -0.00035 -0.00012 0.00000 0.00000 0.00000 -0.00223 i 6' 1 0.00235 -0.00004 0.00000 0.00000 0.00000 -0.00061 , 2 -0.00006 -0.00012 0.00000 0.00000- 0.00000 0.00251 3 0.00102 0.00000 0.00000 0.00000 0.00000 -0.00072 , 1 4 0.00337 -0.00004 0.00000- 0.00000 0.00000 -0.00152 ,- 5 -0.00035 -0.00012 0.00000 0.00000 0.00000 0.00223 !
' '" * " * ' * ' END OF LATEST ANALYSIS RESULT "'" * " * * * '
. 46. PRINT MEMBER FORCES LIST 1 4 7 1- { b a k 5 1 M I E S i i w . . ,. , - . ~ . . ,, r . ,n-, , - , , ,,, ,
~ ~
-\ _-
Calculation L-001337, Rev. O Project No.:10248-012 Attachment B! Page B4 of 7 . , 3X4.19 CHANNELL - -- PAGE NO. f4- l 3 i , e' p MEMBER END FORCES STRUCTURE TYPE = PLANE J - 4 ALL UNITS ARE -- POUN INCH- ] MEMBER LOAD JT AXIAL SHEAR-Y -SHEAR-Z TORSION MOM-Y MOM-Z l' 1 1- 215.09 86.47 0.00. 0.00' ' O.00 -0.00 1 2 -215.09 66.03 0.00- 0.00 0.00 7.91 . 2 1 700.50 -201.91 0.00 0.00: 0.00 0.00 2 -700.50 201.91 0.00 0.00 0.00. -156.28 3 1 0.00 -4.70 0.00 0.00 0.00 0.00 2 .
~0.00 4.70 0.00 0.00 0.00- -3.64
-4 1 215.09 81.76 0.00 0.00 0.00 0.00 1
2 -215.09 70.74 0.00 0.00 0.00 4.27 5 1 700.50 -203.79 0.00 0.00 0.00 0.00 ' 2 -700.50 203.79 0.00 0.00 0.00 -157.74 j 4 1 4 191.35 104.32 0.00 0.00 0.00 -23.55 i 5 -191.35 157.52 0.00 0.00 0.00 -19.67 2 4 201.91 379.44 0.00 0.00 0.00 -12.43 5 -201.91 379.44 0.00 0.00 0.00 12.43 3 4 4-70
. 0.00 0.00 0.00 0.00 6.23 i 5 . -4.70 0.00 0.00 0.00 0.00 -6.23
- 4 4 196.05 104.32 0.00 0.00 0.00 -17.32 i 5 -196.05 157.52 0.00 0.00 0.00 25.90 5 4 203.79 379.44 0.00 0.00 0.00 -9.93 5 -203.79 379.44 0.00 0.00 0.00 9.93
- 7 1 7 268.29 112.61 0.00 0.00 0.00 50.08 8 -268.29 -16.79 0.00 0.00 0.00 0.00 2 7 700.50 201.91 0.00 0.00 0.00 156.28 8 -700.50 -201.91. 0.00 0.00 0.00 0.00 3 7 0.00 4.70 0.00 0.00 0.00 3.64 8 0.00 -4.70 0.00 0.00 0.00 0.00-4 7 268.29 117.31 0.00 0.00 0.00 53.72 8 -268.29 -21.49 0.00 0.00 0.00- 0.00 1 5 7 700.'50 203.79- 0.00 0.00- 0.00 157.74 8 -700.50. -203.79 0.00 0.00 -0.00 -0.00
* * * * * * * * * * * * *
- END OF LATEST ANALYSI S RESULT * * * * * * * * * * * * *
- 1 47.-SECTION 0, .5 1. MEMB 4 >
- 48. PRINT SUPPORT REACTIONS ~
( y g , , , , , -,' -- --- , ,w,-.m3,g.
,,,.yy w ,-y i m,.m,-ny ,,y,,r- r - v
Calculation L-001337, Rev. O Project No. 10248-012 Attachment B Page B5 of 7 3X4.19 CHANNEL -- FACE NO. 5
~~
3UPPORT REACTIONS
- UNIT POUN INCH STRUCTURE TYPE = PLANE JOINT LOAD FORCE-X TORCE-Y l'ORCE-Z HOM-X MOM-Y MOM 2 1 1 -86.47 215.09 0.00 0.00 0.00 0.00 2 201.91 700.50 0.00 0.00 0.00 0.00 3 4.70 0.00 0.00 0.00 0.00 0.00 4 -81.76 215.09 0.00 0.00 0.00 0.00 5 203.79 700.50 0.00 0 00 0.00 0.00 0 1 -16.79 268.29 0.00 0.00 0.00 0.00 2 -201.91 700.50 0.00 0.00 0.00 0.00 3 -4.70 0.00 0.00 0.00 0.00 0.00 4 -21.49 268.29 0.00 0.00 0.00 0.00 5 -203.79 700.50 0.00 0.00 0.00 0.00
. . . . . . . . . + + + + + END Or IATEET ANALYSIS RESULT * * * " * * * * * * * * *
- 49.
- UNIT INCH K!P
- 50. PRINT MEMBER STRESSES LIST 1 4 7 4
\
Calculation L 001337 Rev. O Project No. 10248 012 Attachment B Page B6 of 7 3X4.19 CHANNEL -- PAGE NO. 6
~~
NEMBER STRESSES ALL UNITS ARE POUN/SQ INCH HEMB LD SECT AX1AL DEND-Y BEND-Z COMBINED SHEAR-Y SHLAR-2 1 1 .0 787.9 C 0.0 0.0 787.9 316.7 0.0 1.00 787.9 C 0.0 636.7 1424.5 241.9 0.0 2 .0 2565.9 C 0.0 0.0 2566.0 739.6 0.0 1.00 2565.9 C 0.0 12581.7 15147.7 739.6 0.0 3 .0 0.0 T 0.0 0.0 0.0 17.2 0.0 1.00 0.0 7 0.0 293.1 293.1 17.2 0.0 4 .0 787.9 C 0.0 0.0 787.9 299.5 0.0 1.00 7A7.9 C 0.0 343.6 1131.4 259.1 0.0 5 .0 2565.9 C 0.0 0.0 2566.0 746.5 0.0 1.00 2565.9 C 0.0 12699.0 15264.9 746.5 0.0 4 1 .0 1125.6 C 0.0 4890.4 6015.9 613.6 0.0 0.50 1125.6 C 0.0 11445.9 12571.5 156.5 0.0 1.00 1125.6 C 0.0 4083.4 5209.0 926.6 0.0 2 .0 1187.7 C 0.0 2579.8 3767.5 2232.0 0.0 0.b0 1187.7 C 0.0 34583.8 35771.6 0.0 0.0 1.00 1187.7 C 0.0 2579.8 3767.5 2232.0 0.0 3 .0 27.7 C 0.0 1294.0 1321.6 0.0 0.0 0.50 2 7.7 C 0.0 1294.0 1321.6 0.0 0.0 1.00 27.7 C 0.0 1294.0 1321.6 0.0 0.0 4 .0 1153.2 C 0.0 3596.4 4749.6 613.6 0.0 0.50 1153.2 C 0.0 10151.9 11305.2 156.5 0.0 1.00 1153.2 C 0.0 5377.4 6530.6 926.6 0.0 5 .0 1198.8 C 0.0 2062.2 3261.0 2232.0 0.0 0.50 1198.8 C 0.0 34066.3 35265.1 0.0 0.0 1.00 1198.8 C 0.0 2062.2 3261.0 2232.0 0.0 7 1 .0 9P2.7 C 0.0 4031.6 5014.3 432.5 0.0 1.00 982.7 0 0.0 0.0 982.7 61.5 0.0 2 .0 2566.0 C 0.0 12581.7 15147.7 739.6 0.0 1.00 2566.0 C 0.0 0.0 2566.0 739.6 0.0 3 .0 0.0 C 0.0 293.1 293.1 17.2 0.0 1.00 0.0 C 0.0 0.0 0.0 17.2 0.0 4 .0 982.7 C 0.0 4324.7 5307.4 429.7 0.0 1.00 982.7 C 0.0 0.0 982.7 78.7 0.0 5 .0 2566.0 C 0.0 12699.0 15264.9 746.5 0.0 1.00 2566.0 C 0.0 0.0 2566.0 746.5 0.0
************** END OF LATEST ANALYSIS RESULT ********* ...
- 51.
- PARAMETERS
- 52.
- CODE AISC
- 53.
- CHECK CODE 1 TO 12 14 TO 22
- 54. FINISH
. . . . . . . . . . . . * *
- EN D O F S T AA D- I I I * * * * * * * * * * * * *
- Calculation L 001337 Rev. O Project No. 10248 012 Attachment B Page B7 of 7
' ' ' DATE = S E P 30,1997 TIME- 10:42:19 ""
for questions on STAAD-111, contact: *
- Research Engineers, Inc at * ~~
- l Tax: *
(714) 974-2500 (714) 921-2543
.........'h................................................
Calculation L 001337, Rev. O Project No. 10248 012 Attachment C Page C1 of 8 PAGE NO. 1 S T A A D - III
- Pevision 20.2
- Proprietary Program of *
- Research Engineers, Inc. *
- OCT 28, 1997
- Date=
Time = 13:37: 2 USER ID: SARGENT & LUNDY ENGRS
- 1. STAAD PLANE 3X4.19 CHANNEL
- 2. INPUT WIDTH 72
- 3. UNIT INCHES POUND
- 4. JOINT COORDINATES
- 5. 1 0. 5; 2 0. 774; 3 0. 1.325; 4 D.551 1.325; 5 2.176 1.325
- 6. 6 2.727 1.325; 7 2.727 0.774s 8 2.727 0.
- 7. MEMBER INCIDENCES
- 8. I 1 2; 2 2 3 3 3 4s 4 4 $s 5 5 6; 6 6 7; 7 7 8
- 9. MEMBER PROPERTY AMERICAN
- 10. I 2 PRI IX .1 IY .0016955 II .0016955 AY .273 AZ .2 YD .273 ZD 1
- 11. 3 4 5 PRI IX .1 IY .0004094 IZ .0004094 AY .170 AZ .2 YD .170 ZD 1
- 12. 6 7 PRI IX .1 IY .0016955 IZ .0016955 AY .273 AZ .2 YD .273 ZD 1
- 13. CONSTANTS
- 14. E STEEL ALL a
- 15. POISSON STEEL ALL
- 16. DENSITY STEEL ALL
- 17. BETA 0. ALL
- 18.
- STAINLESS STEEL
- 19. ALPHA 99E-7 ALL
- 20. SUPPORTS
- 21. 1 8 PINNED
- 22. LOAD 1 LC 4,5,7 UPPER CHANNEL
- 23. JOINT LOAD
- 74. 3 FX $8.48 FY -6.1425 25, 6 rX -3.825 FY -6.1425
- 26. MEMBER LOAD 27, 1 2 UNI GX 688.
- 28. 3 4 5 UNI GY -45, 29, 6 7 UNI GX -45
- 30. LOAD 2 LC 4,5,7 LOWER CHANNEL
- 31. JOINT LOAD 32, 3 rX 3.825 FY -6.1425 3 3, 6 FX -5 8. 4 8 ry - 6.14 2 5
- 34. MEMBER LOAD
- 35. 1 2 UNI GX 45,
- 36. 3 4 5 UNI GY -45, 37, 6 7 UNI GX -688.
- 30. LOAD 3 LC 4,5,7 CHANNEL AT EL. 703'-0"
- 39. JOINT LOAD 40, 3 FX 3.025 FY -6.1425
- 41. 6 TX -39.69 FY -6,1425
Calculation L-001337, Rev. O Project No. 10248-012 Attachment C Page C2 of 8 3X4.19 CHANNEL -- PAGE NO. 2
- 42. MEMBER LOAD
- 43. 1 2 UNI GX 45. ~~'
44, 3 4 5 UNI GY -45.
- 45. 6 7 UNI GX -467
- 46. LOAD 4 LC 4,$,7 PRESSURE LOAD = 197.03 PSI
- 47. JOINT LOAD 48, 3 FX 10.523 TY ~21.99 4 9. 6 FX -16.75 FY -21.99
- 50. MEMBER LOAD
$1. 1 2 UNI GX 123.0 $2. 3 4 $ UNI GY -161.13 $3. 6 7 UNI GX -197.03
- 54. LOAD $ THERMAL 5$. TEMP LOAD
- 56. 1 70 7 TEMP 76. *
- 57. LOAD COMB 6
$8. 1 1. 5 1. $9. LOAD COMB 7 60.21.51.
- 61. LOAD COMB B CHANNEL AT EL. 703'-0"
- 02. 3 1. $ 1
- 63. LOAD COMB 9 PRESSURE LOAD + THERMAL 64.41.51.0
- 65. LOAD LIST ALL
- 66. PERFORM ANALYSIS PR0BLEM STATISTICS NUMBER OF JOINTS / MEMBER + ELEMENTS / SUPPORTS = 8/ 7/ 2 ORIGINAL / FINAL BAND-WIDTH = 1/ 1 TOTAL PRIMARY LOAD CASES = 5, TOTAL DEGREES OF FREEDOM = 20 SIZE OF STIrrNESS MATRIX = 120 DOUBLE PREC. WORDS REQRD/ AVAIL. DISK SPACE a 12.01/ 1069.0 MB, EXMEM = 1.02 MB
++ PROCESSING ELEMENT STIFFNESS MATRIX. 13:371 4 ++ PROCESSING GLOBAL STIFFNESS MATRIX. 13:37: 4 ++ PROCESSING TRIANGULAR TACTORIZATION. 13:371 4 ++ CALCULATING JOINT DISPLACEMENTS. 13:37: 4 ++ CALCULATING MEMBER FORCES. 13:37: 4 67 PRINT JOINT DISP LIST 3 6
Calculation L 001337, Rev. O Project No. 10248-012 Attachment C Page C3 of 8 3X4.19 CHANNEL -- PAGE NO. 3
~~
JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN 2-ROTAN 3 1 0.00769 0.00001 0.00000 0.00000 0.00000 -0.00011 2 -0.01168 -0.00003 0.00000 0.00000 0.00000 0.01242 3 -0.00765 -0.00002 0.00000 0.00000 0.00000 0.00809 4 -0.00095 -0.00003 0.00000 0 00000 0.00000 0.000$0 5 -0.00083 0.00062 0.00000 0.00000 0.00000 0.00097 6 0.00687 0.00063 0.00000 0.00000 0.00000 -0.00714 7 -0.01250 0.00060 0.00000 0.00000 0.00000 0.01339 8 -0.00848 0.00060 0.00000 0.00000 0.00000 0.00905 9 -0.00177 0.00059 0.00000 0.00000 0.00000 0.00147 6 1 0.00760 -0.00003 0.00000 0.00000 0.00000 -0.00425 2 -0.01189 0.00002 0.00000 0.00000 0.00000 0.00594 3 -0.00100 0.00001 0.00000 0.00000 0.00000 0.00395 4 -0.00106 -0.00004 0.v0000 0.00000 0.00000 0.00111 5 0.00122 0.00100 0.00000 0.00000 0.00000 -0.00003 6 0.00802 0.00097 0.00000 0.00000 0.00000 -0.00508 7 -0.01067 0.00101 0.00000 0.00000 0.00000 0.00511 8 -0.00658 0.00100 0.00000 0.00000 0.00000 0.00312 9 0.00016 0.00096 0.00000 0.00000 0.00000 0.00028
* * * * * * * * * * * * *
- END OF LATEST ANALYSI S RESULT * * * * * * * * * * * * * *
- 68. FRINT MEMBER FORCES LIST 1 4 7
Calculation L 001337 Rev. O Project No. 10248 012 Attachment C Page C4 of 8 3X4.19 CRANNEL -- PAGE NO. 4
~~
MEMBER END FORCES STRUCTURE TYPE = PLANE ALL UNITS ARE -- POUN INCH MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y. MOM-Z 1 1 1 -49.40 463.69 0.00 0.00 0.00 0.00 2 49.48 -275.18 0.00 0.00 0.00 101.22 2 1 241.35 -336.75 0.00 0.00 0.00 0.00 2 -241.35 349.00 0.00 0.00 0.00 -93.96 3 1 181.49 -225.46 0.00 0.00 0.00 0.00 2 -101.49 237.79 0.00 0.00 0.00 -63.46 4 1 257.07 -92.13 0.00 0.00 0.00 0.00 2 -257.07 126.06 0.00 0.00 0.00 -29.89 5 1 -1.34 -7.29 0.00 0.00 0.00 0.00 2 1.34 7.29 0.00 0.00 0.00 -2.00 6 1 -50.82 456.40 0.00 0.00 0.00 0.00 2 50.82 -267.89 0.00 0.00 0.00 99.23 7 1 240.02 -344.03 0.00 0.00 0.00 0.00 2 -240.02 356.36 0.00 0.00 0.00 -95.95 8 1 180.16 -232.74 0.00 0.00 0.00 0.00 2 -100.16 245.07 0.00 0.00 0.00 -65.46 9 1 255.74 -99.42 0.00 0.00 0.00 0.00 2 -255.74 133.34 0.00 0.00 0.00 -31.89 4 1 4 162.39 -80.42 0.00 0.00 0.00 -110.93 5 -162.39 153.54 0.00 0.00 0.00 -79.17 2 4 377.70 210.42 0.00 0.00 0.00 170.36 5 -377.70 -137.29 0.00 0.00 0.00 112.15 3 4 266.41 150.55 0.00 0.00 0.00 111.53 5 -266.41 -77.43 0.00 0.00 0.00 73.71 4 4 204.79 146.30 0.00 0.00 0.00 13.07 5 -204.79 115.54 0.00 0.00 0.00 11.92 5 4 7.29 -1.34 0.00 0.00 0.00 6.75 5 -7.29 1.34 0.00 0.00 0.00 -0.92 6 4 169.68 -81.75 0.00 0.00 0.00 -104.18 5 -169.68 154.88 0.00 0.00 0.00 -88.08 7 4 384.99 209.08 0.00 0,00 0.00 177.11 5 -384,99 -135.96 0.00 0.00 0.00 103.24 0 4 273.69 149.22 0.00 0.00 0.00 118.28 5 -273.69 -76.09 0.00 0.00 0.00 64.79 0 4 212.08 144.96 0.00 0.00 0.00 19.02 5 -212.08 116.87 0.00 0.00 0.00 3.00 7 1 7 184.48 133.77 0.00 0.00 0.00 90.06 8 -184.48 -98.94 0.00 0.00 0.00 0.00 2 7 -106.35 -59.87 0.00 0.00 0.00 -252.42 8 106.35 592.38 0.00 0.00 0.00 0.00 3 7 -46.49 -30.60 0.00 0.00 0.00 -163.57 8 46.49 392.06 0.00 0.00 0.00 0.00
Calculation L 001337 Rev. O Project No. 10248 012 Attachment C Page C5 of 8 3X4.19 CHANNEL -- PAGE NO. 5
~~
MEMBER END FORCES STRUCTURE TYPE = PLANE ALL UNITS ARE -- POUll INCH MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-2 TORSION MOM-Y MOM-Z 4 7 226.31 79.40 0.00 0.00 0.00 2.50 0 -226.31 73.02 0.00 0.00 0.00 0.00 5 7 1.34 7.29 0.00 0.00 0.00 5.64 0 -1.34 -7.29 0.00 0.00 0.00 0.00 6 7 185.82 141.06 0.00 0.00 0.00 95.70 8 -105.82 -106.23 0.00 0.00 0.00 0.00 7 7 -105.02 -52.58 0.00 0.00 0.00 -246.78 8 105.02 505.10 0.00 0.00 0.00 0.00 0 7 -45.16 -23.32 0.00 0.00 0.00 -157.93 0 45.16 304.77 0.00 0.00 0.00 0.00 9 7 227.65 06.76 0.00 0.00 0.00 0.14 0 -227.65 65.74 0.00 0.00 0.00 0.00
............s. END OF LATEST ANALYSIS RESULT **************
- 69. SECTION 0. 5 1. MEMB 4
- 70. PRINT SUPPORT REACTIONS
Calculation L-001337, Rev. O Project No. 10248 012 Attachment C Page C6 of 8 3X4.19 CHANNEL -- PAGE NO. 6
~~
SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE JOINT LOAD FORCE-X FORCE-Y TORCE-Z MOM-X MOM-Y MOM Z l 1 -463.69 -49.48 0.00 0.00 0.00 0.00 2 336.75 241.35 0.00 0.00 0.00 0.00 3 225.46 181.49 0.00 0.00 0.00 0.00 4 92.13 257.07 0.00 0.00 0.00 0.00 5 7.29 -1,34 0.00 0.00 0.00 0.00 6 -456.40 -50.82 0.00 0.00 0.00 0.00 7 344.03 240.02 0.00 0.00 0.00 0.00 0 232.74 180.16 0.00 0.00 0.00 0.00 9 99.42 25$.74 0.00 0.00 0.00 0.00 8 1 -98.94 184.48 0.00 0.00 0.00 0.00 2 592.38 -106.35 0.00 0.00 0.00 0.00 3 392.06 -46.49 0.00 0.00 0.00 0.00 4 73.02 226.31 0.00 0.00 0.00 0.00 5 -7.29 1.34 0.00 0.00 0.00 0.00 6 -106.23 105.82 0.00 0.00 0.00 0.00 7 585.10 -105.02 0.00 0.00 0.00 0.00 0 384.77 -45.16 0.00 0.00 0.00 0.00 9 65.74 227.65 0.00 0.00 0.00 0.00
************** END OF LATEST ANALYSIS EESULT ************ *
- 71. PRINT MEMBER STRESSES LIST 1 4 7
Calculation L 001337, Rev. O Project No. 10248 012 Attachment C Page C7 of 8 3X4.19 CHANNEL -- PAGE NO. 7
~ '-
MEMBER STRESSES ALL UNITS ARE PoVH/SQ 1H0H MEMB LD SECT AX1AL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z 1 1 .0 181.2 T 0.0 0.0 181.3 1698.5 0.0 1.00 181.2 T 0.0 8149.3 8330.5 1000.0 0.0 2 .0 884 1 C 0.0 0.0 884.1 1233.5 0.0 1.00 884.4 C 0.0 7564.3 8448.4 1278.7 0.0 3 .0 664.8 C 0.0 0.0 664.8 825.8 0.0 1.00 664.0 C 0.0 $109.3 5774.1 871.0 0.0 4 .0 941.7 C 0.0 0.0 941.7 337.5 0.0 1.00 941.7 C 0.0 2406.5 3348.2 461.7 0.0
$ .0 4.9 7 0.0 0.0 4.9 26.7 0.0 1.00 4.9 T 0.0 160.7 165.6 26.7 0.0 6 .0 186.1 T 0.0 0.0 186.2 1671.8 0.0 1.00 186.1 T 0.0 7988.6 8174.7 981.3 0.0 7 .0 879.2 C 0.0 0.0 879.2 1260.2 0.0 1.00 879.2 C 0.0 7725.0 8604.2 1305.4 0.0 8 .0 659.9 C 0.0 0.0 659.9 852.5 0.0 1.00 659.9 C 0.0 $270.0 5929.9 897.7 0.0 9 .0 936.8 C 0.0 0.0 936.8 364.2 0.0 1.00 936.8 C 0.0 2567.2 3504.0 488.4 0.0 4 1 .0 955.3 C 0.0 23030.8 23906.0 473.1 0.0 0.50 955.3 C 0.0 6300.9 7336.1 688.1 0.0 1.00 955.3 C 0.0 16436.0 17392.1 903.2 0.0 2 .0 2221.8 C 0.0 35370.3 37592.1 1237.7 0.0 0.50 2221.8 C 0.0 2958.5 5180.3 1022.7 0.0 1.00 2221.0 C 0.0 23285.5 25507.3 807.6 0.0 3 .0 1567.1 C 0.0 23155.8 24722.8 885.6 0.0 0.50 1567.1 C 0.0 842.4 2409.5 670.5 0.0 1.00 1567.1 C 0.0 15303.2 16870.2 455.5 0.0 4 .0 1204.7 C 0.0 2713.9 3918.6 860.6 0.0 0.50 1204.7 C 0.0 10923.0 12127.6 90.5 0.0 1.00 1204.7 C 0.0 2475.0 3679.7 679.6 0.0 5 .0 42.9 C 0.0 1400.6 1443.5 7.9 0.0 0.50 42.9 C 0.0 1626.0 1668.8 7.9 0.0 1.00 42.9 C 0.0 1851.3 1894.2 7.9 0.0 6 .0 998.1 C 0.0 21630.1 22628.3 480.9 0.0 0.50 998.1 C 0.0 4754.9 5753.0 696.0 0.0 1.00 998.1 0 0.0 18288.1 19286.2 911.1 0.0 7 .0 2264.6 C 0.0 36771.0 39035.6 1229.9 0.0 0.50 2264.6 C 0.0 4584.5 6849.1 1014.8 0.0 1.00 2264.6 C 0.0 21434.2 23698.9 799.7 0.0 8 .0 1609.9 C 0.0 24556.4 26166.3 877.8 0.0 0.50 1609.9 C 0.0 2468.4 4078,3 662.7 0.0 1.00 1609.9 C 0.0 13451.9 15061.8 447.6 0.0 9 .0 1247.5 C 0.0 4114.6 $362.1 852.7 0.0 0.50 1247.5 C 0.0 9297.0 10544.5 82.6 0.0 1.00 1247.5 C 0.0 623.7 1871.2 687.5 0.0 7 1 .0 675.8 C 0.0 7250.6 7926.3 490.0 0.0 1.00- 675.8 C 0.0 0.0 675.0 362.4 0.0
Calculation L-001337, Rev. O Project No. 10248-012 Attachment C Page C8 of 8 3X4.19 CHANNEL -- FAGE NO. 8/# /?/ J A (--
~~
MEMBER STRESSES ALL UNITS ARE POUN/SQ INCH MEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z 2 .0 389.6 T 0.0 20321.7 20711.3 219.3 0.0 1.00 389.6 7 0.0 0.0 389.6 2169.0 0.0 3 .0 170.3 7 0.0 13168.5 13338.8 112.1 0.0 1.00 170.3 7 0.0 0.0 170.3 1436.1 0.0 4 .0 829.0 C 0.0 201.1 1030.1 291.1 0.0 1.00 829.0 C 0.0 0.0 829.0 267.5 0.0
$ .0 4.9 C 0.0 454.0 458.8 26.7 -
0.0 1.00 4.9 C 0.0 0.0 4.9 26.7 0.0 6 .0 680.6 C 0.0 7704.5 8385.2 516.7 0.0 1.00 600.6 C 0.0 0.0 680.7 309.1 0.0 7 .0 384.7 T 0.0 19867.8 20252.5 192.6 0.0 1.00 384.7 T 0.0 0.0 384.7 2143.2 0.0 8 .0 165.4 7 0.0 12714.6 12880.0 85.4 0.0 1.00 165.4 7 0.0 0.0 165.4 1409.4 0.0 9 .0 833.9 C 0.0 655.1 1489.0 317.8 0.0 1.00 833.9 C 0.0 0.0 833.9 240.8 0.0
.........*..** END OF LATEST ANALYSIS RESULT **************
- 72. FINISH
. . . . . . . . . . . . * *
- E N D O F S T AA D * ! ! ! * * * * * * * * * * * * * * *
" *
- DATE- OCT 28,1997 TIME- 13:37: $ ****
For questions on STAAD-III, contact
- Research Engineers, Inc at Ph: (714) 974-2500 Fax: (714) 921-2543
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Page 3 Of)9 R/o ; l (~- e l r Contractor Nano CB(T* . t l 4 Document Li,stingt s
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Calculation L.001337 Project No. 10248 012 ATTACllMENT D S,,, Page 4 Of 39 8th REYNOLDS ALUMINUM SUPPLY COMPANY METALS AND BUILDING PRODUCTS ~-< 4MX) t il TH AVLNUL, $. . P. O. 00X 1378b . DI AMINGHAM, AL ABAMA 35702 205/$912341 . September 31, 1974 Chicago Bridge P. O. Box 774 Kankakee, Illinois 60901 Attention: Art Johnson Picase use this letter as nothorization to mark material on P.O.
# C73-6336-12A as follows:
6 pes. lit. # F30188 22 pes. lit. # 23755 39 pes. lit . # 17797 7 pcs. Ht. # 42379 Very truly yours, REYNOLDS ALUMINUM SUPPLY CO.
///
Bob Littleton BL rf cc F13e Il In business since 1914 _1
ORYNCLC ALOMINUM SCPPLY DMPANY $$I$, [$2.$ AT1 ACilMl:N1 D Page $ Of 39 R/C CERTIFICATE OF TEST STAINLESS STEEL
. Doie d'-/ MM Customer blCO y L Customer Order No. 2.314:3dfo -/td Add:ess Consignee Consignee Order No.
Addses: Invotee No. __ O 7" O 7d 7 9 __ Date of Shipment A"A " Speelflection MoThl- A A /40 crode do# M ATERI AL , et t u PJE AT NUMDER NUMBER OF PIECES' SIZE ,, CONDITION l'30 ISO f,e A A I h '3// t. X I A 0 * *> ' \ 8
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CHEMICAL ANALYSES sit M C MN P S Si CR No Cu Ts Co Mo
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(, , 0 5' I.47 .DI9 < 0 ll 51 /S.24 S'.60 PHYSICAL PROPERTIL ' TENSILE STRENGTH YlCLD STRENGTH % ELONG ATION HARDNESS REMARKS
. ITs w I. d'9, 2 00 39,000 6~0 66L A. 80 !00 i
A 9,700 69.I gg g,e 3, 60 800 39,700 59 I Rf f p 4, 85, .t 00 31,400 &A 6 7 f 'I 9 ('. y s,100 36,100 6~4 b_ & A J'h l We certify that the chemical onelyses and physical test results applying on the above ordet nut M cre corteet and true to the best of our knowledge and belief. Sworn and subseilbed to before me Reynolds Aluminum Supply Company 7 l
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. A dd i t i on 7 18474 ITT Harper Inc. G.J. caicubcon t Oni m Pudect No.10NS Ol; I 8200 Lehigh Avenon . Morton Orove ill b0053
. Q121906-8000 ATTACllMENT D Pase 6 Of 39 R/c CLRTirl[0 TC$T PLPORT [ Dates 6/14/74 ,
C us t ve r : ' METAL GOOD $ $lRVICE CENTER DIV ALCAN ALUM lika0 W. AD0l$0N $TREET llMh Drowing No.' W NKLIN PARK, ILL. 60131 Addtcu: HMH Vork Osder No. Purchase Orde r No. 26 -)l0$5 , bescrlptiunof i t eer We19ht and i.e n'j t h Haterial Pieces $hape Site ,
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2, i.38 7/tsh Mechanical Propertles Heat Number Tentile $t rength Yield $trength (longation R of A Hardness 30844 88.300 50.000 byt 69 M O We be rci , ce r t i f y that the above figures are correct as contained in the records of this
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CERTiritD TEST REP 0AT Datet 6/4/74 CHAllGED ITtit H.8H Register No.005090 t cuv r t METAL. GOODS $EriVICE
' DIY ALCA?1 AI.t!!! HMH Drawing No.
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HMH vork Order Ho. chase Order No. 24-90007 Description of item Ight and -
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.24 1.43
.31 .34 10.69 10.03
- 064 023 30706 . 021 023 26 .28 10.60 9.90 .34 1.46 30013 049 018
- Hechanical Properties PCS LOS fensile Strength Yield Strength 1Elon00 tion R of A Hardness Hut Number 60 57 3050 90,000 51,700 50 30599 30706 91,000
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50,000 40 67 hh4020 70 2 135 30013 .. 89,200 49,300 51 , We hereby certify hat the above figures are correct as contained In the records of this *
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MATERIAL HE AT . 1. Welded Assembliis NUMBER SHCF.T 2. Non. Welded Code Matl.
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Mark 3E A8' 3 Y/#* 8#00 0 Cakulation L.001337 3A,3 // fte . 3 (24 A O l'roject No. 10248 012 38 * ( __ ONS 1#0 # a'r Of3 0 _as -s n . sco Sc4-/f y I'cc, .E e & & O I I I L Dv \ \ caisheso (( oate //J/[/r $ esxof f i A _ DATEl __ a Reviewed (for rnatorial covered by code): jj
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Calculation L 001337 V p, p fgg g , Jg4g Project No.1004S.012 - -
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Chemical Analysis LDS PC5: Heat Number C S ; P CU 1 M0 CR Nl Si NH
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ATTACllMENT D
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i Calculation L 001337 Project No. 10248 012 s ATTACHMENT D SUPPLEMENTAL
SUMMARY
SHEET Page 18 Of 39 R/c 1 FOR MATERI AL VERIFICATION O C' f 4 3 CHICAGO BRIDGE & IRON COMPANY
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. Calculation L 001337 Project N;. 10218 012 6
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SHEET ATTACllMENT D
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- 3. Non Code Matt.
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MJ.SITY ASSURANCI DOCUMENT 'NDEL - Specification #m 5 M . 21l. Page ' of. ' File Number- 6. A Docuc.ont Title _ d M T A 's Calculation L.001337
' Project No. 10248 012
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Contractor Name CBff
- ATTACHMENT D Pai;e 22 0T39 - (t/o Document Li,stingt ,
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34 C/JI3};13121966-8000 . ATTACllMENT D Pasc 23 0f 39 Me . JR NUMBER $N b l0 '
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164V ERTIFIEbTESTREPORT Date: 10/21/74
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HMH Register No.005743
'ECIFICATIONS A (Tm A A~/ ip _.
{y [ 3 6 , fiMHDrawingNo. { Y![N hM0 i HHH Work Order No.
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, Descript lon of item Pieces Shape Sire Length Naterial 3,320 LDS -
25 PCS CHANNEL 3xl 3/8x3/16" R/L 304 STAINLESS STEEL SPEC: ASTN A 276
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. r 40489 89,200 51,600 50.0 68.0 r,,
4 W3 hereby certify that the above figures are correct as contained in the records of this company. .
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D i'.', f LC A N .',LUP. lNUH Project No. 10248-012 h-g.- [*
'lli.uo V. ADDi$0tl ST8tElf ATTACHMENT D HMH Drawing No.
Address: IUN$lINPAFF. Il L I,1'0 I S 6'3 I .'I Page 24 Of 39 Plc *
. HMN Work Order No.
Purchase Order No. 7.W675 ,
- Descript ion of item
- We i ght and -- - - - - -
Pleces Shape Size Le ngt h Material 33fD L*5 s ' )
.sl PCs tu rn.r t 2 x 1 .* ?/16 19' !/L 3nl4 STtlNLE55 STELL r .
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MATERI AL HEAT NUMBER SHEET Q 1. Welded Assemblies
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- 3. Non Code Matt.
piece. Piece- 3 g g Mark E Material Heat No, fg Mark jz Material Heat No, eg ir J2 g Z pg y ffgr ffss/ Calculation L 001337 V 32- 7 2 A*- 40489 ProjectWo. 10248-012 _
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'11400 W. /.0Di$0tl $T8tELT MMH Drawing No.
Page 30 0f 39 &# Address: IFAN$.L l!1 P/M., ILLI,t:Ol$ Solf t -
- HMH Vork. Order No.
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- Description of item
. . ye l g h t and -- .-- - -- - - - - -- - - Pleces Shape Size length Material 3315 S .
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Chemical Analysis s LBS Heat Number C S P CU M0 CR NI SI MH
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Heat Number Tensile Strength YieldJtrength Elonpition R oJ/3 Hardness 71 30660 90.850
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,Ve hereby certify that the above figures are correct as contai.ned in the record f h
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Date: 10/21/74
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HMH Register No.005743
'ECIFICATIONS A (Tm A -9.Y p c,,,,,,,;,, t,gg ,3 y .U [ 36 L Ad 13]
Project No. 10248-012 ATTACHMENT D iiMH Drawing-No. y f3 g b }7) Page 310f 39 R./c . HHH Work Order No.
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, Descript ion of item Pieces Shape size Length Material 3,320 LBS 25 PCS CHANNEL 3xl 3/8x3/16" R/L 304 STAMLESS STEEL SPEC: ASTM A 276 i .- .
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SU8sCR18ED AND SWORN 10 8EFORE M2 iHis ISI!It ._DAI '
*l' WE CERilFY THE ABOVE INFORMATION IS AN EXACT COPY OF CERTIFIED TEST CERilFICATES FURNISHED BY THE ABOVE MANUFACTUPERS AND KEPT IN OUR PERMANENT RECORD Fi1ES.
OF SGPCREbtF,19 1 a, 4 \' ,/
- JONES & LAUGHLIN STEEL SERVICE CENTER DsVISION
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Calculation L-001337, Rev. 2 - Project No. 10364-004 Attachment E -Page Ei of 6
-PAGE NO. 'l-1
- S T A A D - III- *
- Revision 20.2
- Proprietary Program of
- Research Engineers, Inc. *
- JAN 16, 1998
- Date=
Time = 9:59:40 USER ID: SARGENT & LUNDY ENGRS t
- 1. STAAD PLANE DETAIL C-C, CBI DWG. 129'R3
- 2. INPUT WIDTH 72
- 3. UNIT INCHES POUND 4 JOINT COORDINATES
- 5. 1 0, 5.1875: 2 1. 5.1875; 3 9.3125 5.1875; 4 9.3125 O.
6.-MEMBER INCIDENCES
- 7. 1 1 2; 2 2 3; 3 3 4
- 8. MEMBER PROPERTY AMERICAN
- 9. 1 TO 3 PRI IX .02 IY .00439 IZ .004395 AY .375 AZ .4 YD .375 ZD 1
- 10. CONSTANTS
- 11. E STEEL ALL
- 12. POISSON STEEL ALL
- 13. DENSITY STEEL ALL
- 14. BETA 0. ALL
- 15.
- STAINLESS STEEL
- 16. ALPHA 99E-7 ALL-l 17. SUPPORTS
- 18. 1 4 PINNED 19, 2 FIXED BUT FX MZ .
- 20. LOAD-1 PRESSURE LOAD = 295 PSI ON MEMB 3, 45 PSI ON 1&2
- 21. MEMBER LOAD 22.~ 1 2 UNI GY -45.
- 23. 3 UNI GX -295.
- 24. LOAD 2 THERMAL
- 25. TEMP LOAD-
- 26. 1 TO 3 TEMP 76,
- 27. LOAD COMB 3
- 28. 1 1. 2 1.
- 29. LOAD LIST 1-3
- 30._ PERFORM ANALYSIS P R O B L E-M S T A T I-S T-I C S NUMBER'0F JOINTS / MEMBER + ELEMENTS / SUPPORTS .
4/ 3/ 3-ORIGINAL / FINAL BAND-WIDTH = 1/ -1 TOTAL PRIMARY LOAD. CASES = 2, TOTAL DEGREES OF FREEDOM = 7 SIZE OF STIFFNESS MATRIX = 35 DOUBLE.PREC. WORDS REORD/ AVAIL. DISK SPACE =' 12.01/ 1059.6 MB, EXMEM = 1.02 MB \ L
Calculation L-001337, Rev. 2 : Project No. 10364-004 Attachment E Page E2 of 6 DETAIL C-C, CBI CWG 129 R3 -- PAGE NO. 2 . ++ PROCESSING ELEMENT STIFTNESS MATRIX. 9:59:41'-
++ PROCESSING GLOBAL STIFFNESS MATRIX.- 9:59:41 , , _ _ ,
++ PROCESSING TRIANGULAR TACTORIZATION - 9:59:41-
++ CALCULATING JOINT DISPLACEMENTS. 9:59:41
-++ CALCULATING MEMBER. FORCES. 9:59:42
- 31. PRINT JOINT DISP LIST 3 4
i
~
i s 4 i k f u ..
T Calculation L-001337, Rev. 2 _ Project No. 10364-004 Attachment E - Page E3 of 6
-DETAIL C-C, CBI DWG. 129 R3- --
PAGE No.- -3
" ~ ~~
JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE JOINT LOAD X-TRANS Y-TRANS Z-TRANS- X-ROTAN= -Y-ROTAN Z-ROTAN 3 1 -0.00075 -0.00012 0.00000 0.00000 0'.00000 -0.00530 ! -3 0.00624 0.00378 0.00000 0.00000 0.00000 -0.00575
" " * ' * " " ' END OF LATEST ANALYSIS RESULT ""* *" *"*' ,
a
- 32. PRINT MEMBER FORCES LIST 2 3 !
s j .!- T
~
,m- .n. . ,m .. ~ w -,. >wn ,,. -
d Calculation L-001337, Rev. 2-- Project No. 10364-004: .- Attachment E Page E4 of 8 :
)
DETAIL C-C, CBI DWG. 129 R3
- PAGE NO..- e4
' ' '~~
MEMBER END TORCES STRUCTURE TYPE = PLANE i ALL_ UNITS ARE -- POUN INCH-MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z~ 2 'l 2 878.65 126.45 0.00 0.00 0.00 85.13 3 -878.65 247.61 0.00 0.00 =0.00 -588.73' 3 2 -891.39- 112.70 0.00 0.00 0.00 36.96 3- -891.39 261.36 0.00 0.00 0.00 --654.85 z j 3 1 3 247.61- 878.65 0.00 0.00 0.00 588.73' 4 -247.61 651.67 0.00 0.00 0.00 0.00 I
, 3 3 261.36 891.39 0.00 0.00 0.00 654.85 4' -261.36 638.92 0.00 0.00 0.00 0.00
"" * " * * ' * " END OF LATEST ANALYSIS RESULT * " * * * ' * * * * "
- 33. SECTION 0. .30129 .33805 1. MEMB 2
-34. SECTION 0. 57416 .58249 1. MEMB 3
- 35. PRINT SUPPORT nEACTIONS-4
. t e . - s-,,- ,-%. - - , . --- j- e ,-.e- ,, ,r .,y, er.,v-r 9 y
Calculation L 001337, Rev. 2 _ Project No.10364-00( Attachment E Page E5 of 6-I DETAIL C-C, CBI OWG. 129-R3 -- PAGE No.-- 5-I
^~~~'
-SUPPORT REACTIONS--UNIT TOUN JNCH STRUCTURE TYPE = PLANE i JOINT LOAD TORCE-X TORCE-Y TORCE-Z .. MOM-X - MOM-Y MOM' "
1 . 1' 878.65 -62.f3 0.00 0.00 0.00 0.00 3 -891.39 -14.48 0.00 0.00 0.00 0.00 4 1 651.67 247.61 0.00 0.00 0.00 0.00 3 638.92 261.36- 0.00 0.00 0.00 0.00 2 1 0.00- 234.08 0.00 0.00 0.00 0.00 3 0.00 172.18 0.00 0.00 0.00- 0.00
* " * "" * ' * *
- END OF LATEST ANALYSIS RESULT "" * * "' * " * ,
- 36. PRINT MEMBER STRESSES LIST 2 3 -
Y
-v- rt , e t v ,.,er,-v- -
Calculation L-001337, Rev. 2- Project N'o, 10364-004. Attachment E Page E6 of 3 DETAIL C-C,"CBI DWG. 129 R3
-- PAGE NO. 6/ FINAL i
"' ' ~
MEMBER STRESSES
............... 1 ALL UNITS =ARE POUN/SQ INCH MEMB LD -SECT- AXIAL ~ BEND-Y BEND-Z COMBINED M4 EAR-Y SHEAR-Z
- 2 1 .0 2343.1 C 0.0 3631.8 5974.8 337.2 0,0 0.30 2343.1 C 0.0 3857.8 6200.9 36.7 0.0 0.34 2343.1 C 0.0 3947.4 6290.5 0.0 0.0
1.00 2343.1 C Q.0- 25116.5 27459.5 660.3 0.0 c- 3 .0 2377.0 C 0.0 1577.7 3954.7 300.5- 0.0
- 0.30 2377.0 C 0.0 4443.2 6820.2 0.0 +
0.0 .! ' O.34 2377.0 C 0.0 4353.6 6730.6 36.7 0.0 1.00 2377.0 C 0.0 -27937.2 30314.2 697.0- 0.0
-3 1 .0 660.3 C 0.0 25116.5 25776.8 2343.1 0.0 O.57 660.3 C 0.0 30707.2 31367.5 0.0 0.0 0.58 660.3 C 0.0 30695.5 31355.8 34.0 0.0 1.00 660.3 C 0.0 0.0 660.3 1737.8 0.0 3- .0 697.0 C 0.0 27937.2 28634.1 2377.0 0.0
, 0.57 697.0 C 0.0 29506.1 30203.0 34.0 0.0 0.58 697.0 C 0.0 29517.8 30214.8 0.0 0.0
'1 00
. 697.0 C 0.0 0.0 697.0 1703.8 0.0 r .
************** END OF LATEST ANALYSIS RESULT **************
! 37. FINISH
.. . . . . . . . . * * *
- EN D O F ST AAD-I I I * * * * * * * * * * * * * * *
* * *
- DATF= JAN 16,1998 TIMF= 9:59:42 ****
For questions on STAAD-III, contact:
- 4 Research Engineers, Inc at
- Ph: (714) 974-2500 Fax: (714) 921-2543
- i 1
k
- - - - - -= w-- ,ee
- s w- n r r--,-- , - - - A w4w,,- , .-s v- -- -m---w.- +-,ry t
A a --- -- -..------a -- - , --,,. .- --- == m -- -9 .n- - - --Ge-*-4 -. J -- - *--- - - - * *s- em-4-- m= + ---- -^" -=- -- - - - -- A-~-- Attachment F References
,., w- -,
)
i References l
- 1. llnited States Nuclear Regulatory Commis* ion (NRC) Inspection Report 50-373/78 33, dated January 19,1979
- 2. l., O. DelGeorge (Conunonwealth lidision Company (Comlid)] letter to A.
Schwencer (NRC), "LaSalle County Station, lJnits 1 and 2, Containment Leak Chase Channels," dated August 10,1981
- 3. l.. O. DelGeorge (Comlid) letter to A. Schwencer (NRC), "LaSalle County Station, (Jnits I and 2, Supplemer'11 Information Concerning Containment 1.cak Chase Channels," dated S(plemts - 1,1981
- 4. l. O. DelGeorge (Coml!d) letter to A. Schwencer (NRC), "1.aSalle County Station, (Jnits I and 2, Containment 1.cak Chase Channels," dated October 1, 1981
- 5. NRC Inspection Report 50 373/81 28, dated November 6,1981
- 6. S. V. Athavale (NRC) letter to Donald F. Schnell (Union lilectric Company),
" Containment 1.iner 1.cak Chase Channel Venting Callaway Plant lJnit No.1 (TAC No. 72750)," dated March 14,1990
- 7. Stephen P. Sands (NRC) letter to Thomas J. Kovach (Comtid), " Safety !! valuation of Containment 1.cak Chase Channels Ilyron, (Jnit Nos. I and 2, liraidwood, lJn.; Nos. I and 2 (TAC Nos. 72569,73570,66476, and 66477)," dated May 17, 1990
- 8. 1.icensee !! vent Report (l.IIR) 50 373/97 030 00, dated September 17,1997 9 W. T. Subalusky (Comlid) letter to the NRC Document Control Desk,
" Containment 1.cak Chase Channels," dated November 26,1997 F-1
. _-}}