ML20236N353
| ML20236N353 | |
| Person / Time | |
|---|---|
| Site: | Palisades, Arkansas Nuclear  |
| Issue date: | 06/30/1998 |
| From: | Battige C, Parkhill R NRC OFFICE OF NUCLEAR MATERIAL SAFETY & SAFEGUARDS (NMSS) |
| To: | Howe A NRC OFFICE OF NUCLEAR MATERIAL SAFETY & SAFEGUARDS (NMSS) |
| Shared Package | |
| ML20236J176 | List: |
| References | |
| FOIA-98-164 NUDOCS 9807150099 | |
| Download: ML20236N353 (3) | |
Text
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F.
MEMORANDUM TO:
Allen Howe, Welding Review Team Leader Spent Fuel Technical Review Section, SFPO l
FROM:'
Ronald Parkhill, Mechanical Engineer Spent Fuel Technical Review Section, SFPO Kenneth Battige, Materials Engineer
. Spent Fuel Technical Review Section, SFPO 1
SUBJECT:
FLAWTECH TRIP REPORT On January 22,1998, Messrs. Parkhill and Battige visited the FlawTech Division of PH Diversified, Inc., in Harrisburg, NC, to become more familiar with the methods for inserting i
flaws into metallic component specimens. FlawTech is currently under contract to Consumers Encrgy to implant flaws into the Palisades VSC-24 dry fuel storage mockup. Once the flaws are c implanted, the mockup is to be shipped to'ANO, where it will be used to evaluate the feasibility of performing UT on the structural lid closure weld. As a result of this visit, the following information was obtained:
a)
Flaw Insertion Process-i Flaws are inserted into the desired location by excavating the specimen at the appropriate
- location, welding a lever arm to the an:a of the desired flaw, and then using fatigue to break the
. base metal at the end of the lever ann. Either mechanical or thermal fatigue can be used to cause the breakage. Once the metal is removed from the end of the lever arm, this results in a small piece of metal that fits exactly into its corresponding area of the component specimen. The size -
of the crack is controlled by machining the small piece of metal to the desired shape, reinserting it in its matching component location, and then seal welding its perimeter to the component.
Once the seal welding of the flaw is completed, the excavated volume is welded to restore the component specimen to its original configuration. A UT examination of the excavated volume is performed to ensure that no other imperfections have been added during the welding process.
Other types of flaws, such as slag inclusions and lack of fusion, may also be introduced.
b)
Control of flaw size and location-l-
As described above the flaw size is controlled by measurement and machining of the small piece of fractured material prior to reattaching it to the component specimen via seal welding. The 1-accuracy of this process was demonstrated via destructive examination ofinserted flaws and documented in a report prepared for the Navy.
l cc: F. Sturz, E. Hackett, G. Homseth, C. Interrante, T. Kobetz, H. Lee, M. Vassilaros, D. Reid 9907150099 990630 PDR FOIA DUMS98-164 PDR
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c)
Records and Documentation -
Drawings are prepared by FlawTech working in concert with their client to determine the size, location, and type of flaw to be inserted. These drawings control the fabrication process.
Pictures are taken to provide a record of the flaw insertion process. A documentation package is provided to each client that includes the drawings and a pictorial record of the flaw insertion process. FlawTech also maintains a copy of the documentation package for their own records.
d)
Shipping Considerations-Due to the massiveness of the component specimens, FlawTech generally puts them on a flat bed truck, covered with a tarp. Since the flaws are well within the component specimen protected by the weld material of the excavated volume, no shipping damage is anticipated. For the Palisades mockup, Consumers Energy is planning to do a receipt inspection of the mockup at FlawTech's shop prior to shipping it to ANO.
e)
Impact on UT inspectability-I At the time of the shop visit many of the flaws had already been inserted and FlawTech provided a demonstration of UT's ability to detect some of the flaws. Using a small portable, battery powered UT equipment with a 5 MHZ straight beam transducer, flaws # 13,1,2,3 & 4 were readily identifiable when manually examined from the side of the mockup. It took only a couple of minutes to set up the UT equipment and perform an exammation for these flaws. The EPRI representative stated that thin transducers (i.e., less than a 1/16th of an inch) were available for tight spaces like the area between the inside wall of the transport cask and the outside diameter of the canister. The EPRI representative also stated that an automated UT process could produce more accurate and timely examinations than a manual UT process.
f)
Difference between the Palisades mockup flaws and those that would be produced for other calibration standards (ASME Section XI Appendices VII or VIII)-
i FlawTech stated there was no difference between the flaws implanted in the VSC-24 mockup and Section XI, Appendix VII or VIII, qualification flaws.
g)
Construction under FlawTech or Utility QA program-FlawTech implanted flaws on the Palisades mockup under the utility's QA program since Consumer's Energy has visited FlawTech and performed audits. As mentioned above, CE will perform a receipt inspection of the finished product prior to shipping to ANO. FlawTech has its own QA program modeled after 10 CFR 50 Appendix B developed with the assistance of a utility.
1
h)
Proprietary aspects-FlawTech considered the physical details of the process by which they break the flaw specimen proprietary and we did not see this operation as part of our visit.
I)
EPRI Involvernent-As identified in the Persons Contacted list, two representatives from EPRI's NDE center were present during our visit. They stated EPRI is assisting the SNC owners' group in the preparation of UT procedures for examination of the VSC-24 structural lid welds.-
PERSONS CONTACTED:
George Pherigo, President FlawTech Aaron Pherigo, Executive VP FlawTech and QA Manager Kim Kietzman, EPRI NDE Center -
Robert Zeh Bouck, EPRI NDE Center t.
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December 17,1997 SNC 97-125 P. h W
h Mr. Timothy Kobetz pg U.S. Nuclear Regulatory Commission B.M 3
11555 Rockville Pike NWt Rockville,MD 20852
)
Subject:
Transmittal of Revised Calculation Package CPC-06Q-301 Rev.1: Allowable Flaw Size Defmition for VSC-24 Dry Storage Cask Structural Lid to Shell Weld
Reference:
US NRC Request for Additional Information Conceming Confirmatory Action Letter 97-7-001 dated August 26,1997 US NRC Letter to J. Massey, Sierra Nuclear Corporation, dated December 9, 1997;
Subject:
Commitments Made to the Nuclear Regulatory Commission by Sierra Nuclear Corporation and the VSC-24 Owners Group i
Dear Mr. Kobetz
\\
As part of the response to Question 4 of the US NRC Request for Additional Information Conceming Confirmatory Action Letter 97-7-001 dated August 26,1997, and in response to Commitment 1 of the US NRC Letter to John Massey, Sierra Nuclear Corporation, dated December 9,1997; titled: Commitments Made to the Nuclear Regulatory Commission by Sierra Nuclear Corporation and the VSC-24 Owners Group, Sierra Nuclear Corporation (SNC) l and the VSC-24 Owners Group submit the updated and revised calculation package CPC-06Q-301 Kev. 4, titled: Allowable Flaw Size Dermition for VSC-24 Dry Storage Cask Structural Lid to Shell Weld.
The revised calculation has been updated to incorporate the comments made during the technical review meeting held in Washington D.C. on December 4,1997. In addition, the' calculation has been revised to include a discussion on the postulated mockup defects (Section 7.0) and includes a complete description of these flaws in Appendix C.
/
)
1 Victor Square Scotts Valley, California 95066. (408)438 6444
. Fax (408) 438-5206 f/
gg2&v.P/9 f
i
-a Should you or the Commission have any additional questions please contact me at Sierra Nuclear Corporation (SNC); 408 -438-6444.
Respectfully, Kay kel l
M er, Licensing l
4 cc: G.Dixon, J.Massey; LicRile; f:\\ admin \\ltrs\\sne I
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STRUCTURAL CALCULATION FILE No: CPC-06Q-301
~
INTEGRITY Associates, Inc.
PACKAGE PROJECT No: CPC-06Q l
PROJECT NAME: Analytical Support for Dry Spent Fuel Storage Activities l
CLIENT: Consumers Energy (Palisades Nuclear Plant)
CALCULATION TITLE:
Allowable Flaw Size Definition for VSC-24 Dry Storage Cask Structural Lid to Shell Weld 1
=
PROBLEM STATEMENT OR OBJECTIVE OF THE CALCULATION:
l Develop Weld Flaw Acceptance Criteria l
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Project Mgr.
Preparer (s) &
Document Affected Revision Description Approval Checker (s)
Revision Pages Signature &
Signatures &
Date Date 0
1 - 24 OriginalIssue f)-[1gx g ' jf/ 25/1 jt-l Appendix A ll/2f/9 9 14/25/9 7
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1 1 -28 Incorporated Comments
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1.0 INTRODUCTION
The purpose of this calculation is to develop acceptance criteria for flaws which may be detected in I
the structural lid to shell weld of spent fuel dry storage casks at Palisades, Point Beach, and ANO Nuclear Plants. The typical geometry of the structural lid to shell weldjoint is illustrated in Figure 1 l
[1].
l l
For the casks which are currently in service, nondestructive examination of these welds has included dye penetrant examination of the root and final welded layers. No volumetric examination of these l
welds has been performed in the past, but the plant owners are considering such examination as a result of discussions with the h'RC, l
l 2.0 CODE APPLICABILITY 1
In the present analysis, the methods of ASME Section XI, IWB-3600 and Appendix A [2] are used to determine allowable flaw sizes under the limiting loading conditions. IWB-3600 and Appendix A l
are directly applicable to Class 1 vessels (such as reactor vessels) and piping. Although the dry fuel storage casks are Class 2 (NC) vessels, Section IWC-3600 is still under development, and Section -
XI permits the use of IWB criteria for flaw evaluations.
Section XI flaw evaluation criteria are directly applicable for evaluation of flaw indications detected
' in the structural lid welds of casks which are already in service. Its applicability is less clear for l
examination results for new casks. However, for examinations of structural lid welds which are performed immediately upon completion prior to putting them in service, it is SI's opinion that the rules of Section XI should still be applied,in lieu of Section III rules. Although a loaded cask is not 1
formally considered to be "in operation" until it is successfully transferred to the storage pad, th-cask is performing its design function in a difficult to reverse manner once fuel is loaded and the shield lid and structural lid are in place.Section XI provides more extensive methods for the j
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evaluation of defects detected by volumetric examination, and volumerne examination of the structural lid weld immediately following completion forms a baseline for any subsequent inservice i
inspections by similar methods.
3.0 LOAD DEFINITION Table 1 [1] provides stress data for the structural lid weld under the horizontal drop accident. This event is considered to be an emergency / faulted class (service level C/D) event. Table 2 (1] presents stress data for normal operating events. By comparing the Tables, it can be seen that at the structural lid weld, the normal operating stresses are significantly lower than the stresses which are predicted to result from the horizontal drop event. Therefore, the horizontal drop accident is judged to govern the critical flaw size determination.
As shown on Table 1, the horizontal drop event produces the following stresses in the stmetural lid-to-shell weld:
i Pm = 7.2 ksi
\\
P. r P = 43.3 ksi t
B t
In the fracture mechanics analysis below, both of these stress corr.ponents were included. These were conservatively modeled as a tensile membrane stress, with a magnitude of 43.3 ksi. This magnitude is appropriate for use in the vicinity of the structural lid-to-shell weld. The highest stress in the shell reponed on Table 1 (73.0 ksi) occurs at a location which is approximately 12 inches from the bottom plate of the MSB [9), which is remote from this weld.
In addition to this applied stress, weld residual stress was included in the calculation. Because no measurements or calculations of weld residual stress were available, the weld residual stress was assumed to be represented by a distribution typical of a multipass groove weld such as is presented in Figure 7 which is taken from NUREG 031' Revision 2 (8].
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This typical distribution was scaled to reflect an assumed inside surface tensile stress of 40 ksi.
corresponding to a typical yield stress for the A-516 Grade 70 material. The scaled distribution is shown as a dashed line on Figure 7. Appendix A of Section XI {2] requires the use of residual stresses in determination of allowable flaw sizes.
For normal operating conditions, the limiting applied stress intensity Ki (applied) is:
K' K,(applied)< 5 where Kio calculated from the projected Charpy data is used as the critical stress intensity. The t
safety factor of 80 is as defined in Section IWB-3612. Kio is equivalent to Ka s discussed above.
a For this case, the total applied stress intensity K (applied) is determined from the membrane, i
bending, and residual stresses as K (applied) = Ki(membrane) + K (bending) i i
+ K (residual) i where the Ki(residual) reflects the residual stress case.
For the emergency / faulted case (horizontal drop), it is still appropriate (and conservative) to use the calculated Km as the criterion, because of the dynamic nature of the loading,instead of the Kic (which would be appropriate for static or slow loading rates). For this case (horizontal drop) the applied K is limited by i
K (applied: drop)< Ky i
s_
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The applied K using a safety factor of E on residual stresses as discussed above, is given by:
i
(
Ki(applied)
Ki (membrane) + Kr (bending) + Kr (residual)
=
For this case, residual stresses are also conservatively treated as primary membrane stresses, using the full code safety margin of E.
4.0 MATERIAL FRACTURE TOUGHNESS The certified material test reoorts (CMTRO II.5.61 for the structural lid weld material were provided by the plant owners. The procedure qualification records (PQRs) were also provided.
These documents contain Charpy V-Notch Impact data taken at -50*F (and some data at other temperatures). The PQRs also include Charpy results for base metal and heat affected zone (HAZ) as well as weld metal.
According to the " Certificate of Conformance for the VSC-24 System" [9] in Section 1.2.13. there are administrative limits which prevent moving of the storage casks when the temperature is less than 0 F. Consequently, a horizontal drop accident is judged not to be possible below this temperature.
1 Article A-4000 of Appendix A to Section XI [2] recommends that the material fracture toughness be
, determined from the actual material and product form in question. Therefore, to evaluate the l
fracture toughness of this matenal, use of the actual Charpy data at 0 F is appropriate. The Charpy data at 0 F is used to determine material fracture toughness (K e) using the following equation for i
carbon steel in the transition temperature region [3]:
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In this equation, E was assumed to be 29,000 ksi.
Judging from the % shear data, the material is in the transition region in the -50 F to 0 F temperature range, so use of this equation is appropriate [3). Also, the Charpy correlation is for K o i
(dynamic) fracture toughness as well as Kic (static), so it is applicable to a dynamic event like the drop accident.
As noted above, the material specifications for both base metal and weld metal require Charpy V-imida tea resuits at -juY, wnne me lowest temperature at wnien a honzontal atop could occur is 0 F, due to administrative limits [1]. All three plants (Palisades, Point Beach, ANO) provided CMTRs for weld material used (or proposed for use) in the structural lid welds [1,5,6] and these CMTRs included Charpy data at -50 F. All CMTRs include data for the as welded condition, which is applicable to all three plants. Results for base metal and HAZ from PQRs were also considered.
The PQRs include -50* Charpy data for weld metal, HAZ, and base metal. In order to determine the limiting material condition, all such data was evaluated for toughness at 0 F as described in the following. All available data is presented in Table 3. Based on the data in Table 3 the HAZ is not the limiting location.
In order to determine allowable flaw sizes for each plant, it is appropriate to use the limiting material toughness at the limiting temperature of 0 F. Since such data is not available in most cases, it is necessary to extrapolate toughness at 0 F from the available -50*F data.
The data from all CMTRs and PQRs shows that the material is in the transition region (reported per cent shear of 20-80%) and so linear projection is appropriate. Referring to Figure 5 from [7],the Revision 1
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slope of this curve is estimated as 0.55 ft-lb/ F for the high manganese curve, which describes a material similar to the A-516 Grade 70 base metal. This slope is more gradual than the Ic*c manganese curve, and therefore projection is more conservative using this slope. This slope was used to project all reported base metal, HAZ, and weld metal 50*F data [1,5,6] to 0 F. The results are shown in Table 3. Also, all available Charpy data from CMTRs [1,5.6] at 0 F is shewn in Table 3 for comparison. The predicted 0 F Charpy data for weld metal is conservative compared to all available actual weld metal 0*F data. That is, the predicted Charpy results at 0 F (based on extrapolation of-50 data) are consistently lower than actual data at 0 F for weld metal, which is the l
only material for which 0 F data is available.
l l
Cld Gf
- 4, p,,dkwd Cia py a'ususved esacagy scauita at OT wcte udeu tu calculate a material 1
toughness Kro for use in allowable flaw size calculations.
The resulting fracture toughness at 0 F is greater than 75 ksi-8nIfor all cases. This value is shown in Figure 2 in comparison to ASME Section XI fracture toughness curves for carbon and low alloy
~
steel reactor pressure vessel bounding materials. Figure 4 shows allowable flaw size (depth versus length) for a toughness of 78.4 ksi-,[id, which results from extrapolation of the minimum specified Charpy V-notch absorbed energy of 15 ft-lb at -50 F. (This is the minimum specified for both weld metal and base metal). Allowable flaw size curves for the limiting material for each plant are also shown.
5.0 APPLICATION OF ASME CODE MARGINS As discussed above, the limiting event for the structural lid weld is the horizontal drop accident, wh'ich is considered to be an emergency / faulted event. The stresses associated with this event are defined in Table 1 from [1].
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r Using the mies of IWB 3613(c) [2], the fracture toughness values determined above are reduced by a factor of d to define the limiting allowable K for flaws in the structural lid weld under i
emergency / faulted conditions. That is, K
Kwiow>ie<
l l
For example, a limiting Ko calculated from Charpy data of 78.8 bi-E produces an allowable Ki of 55.4 ksi-8. This value corresponds to the value obtained by extrapolating the minimum l
specified toughness (15 ft-lb at -50'F) to 0 F as discussed above.
6.0 ALLOWABLE FLAS' CALCULATIONS Using the above load definitions and fracture toughness, a series of allowable flaw size calculations were performed using the Structural Integrity Associates computer program pc CRACK
[4],
which has been developed and verified under the SI Quality Assurance program.
6.1 Surface Flaws The structural lid weld was modeled as a plate with an elliptical surface crack subject to both membrane and bending stresses. This model is illustrated in Figure 3. Use of this flat plate model for flaws in the stmetural lid to shell weld is appropriate for flaws originating in the vicinity of the weld root and propagating through the weld material or weld-base metal interface. This model is conservative compared to the actual weld geometry, because the actual weld experiences significant hoop constraint due to the stiffness of the stmetural lid and cask shell. Such constraint will limit 1
crack opening in the actual weld as compared to the model, and therefore a larger crack would be tolerable in the actual weld than is predicted by use of the flat plate model. These results are equally l
applicable to flaws originating on the outside surface and oriented inward.
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_-___m_.
The flaw aspect ratio (the ratio of Haw depth to length) was varied parametrically, to determine an allowable Gaw depth versus length curve. The conser ative fracture toughness including the emergency / faulted Code margins was used as the criterion for determining allowable Daw depth for each aspect ratio.
The results are shown in Figure 4, and the supporting pc-CRACK analyses are attached in Appendix A. There is no known mechanism for continued crack propagation of defects in these l
welds, so no crack growth calculations have been performed for the assumed defects. Limiting allowable flaw depths for each heat of weld material at each plant are shown in Table 3.
6.2 Subsurface Flaws 4
The above discussion addressed the determination of allowable flaw sizes for Daws which are connected to the surface of the weld, under a conservative set of assumptions. The weld could also l
contain subsurface defects as a result of the welding process for example. In general, the allowable flaw size for a subsurface defect will be larger (usually twice or greater) than for a surface defect i
under the same conditions.
Evaluation of allowable subst rface defects was performed using the same linear clastic fracture mechanics techniques as were described above for surface defects. For these cases, a center cracked plate model (Figure 6) was used to evaluate the inf' mite length flaw. This model is conservative for the actual cases, since it treats applied stresses as pure tension, while for the subsurface flaw cases, the drop load case has a significant through-wall bending component. Consequently, for a subsurface flaw the stresses due to the drop event will be significantly lower than the 43.3 ksi surface stress for this event (see page 3). The calculated allowable Daw sizes for subsurface flaws corresponding to the same assumptions presented in Table 3 for surface flaws are shown in Table 4.
The allowable subsurface Haw results presented in Table 4 also require that the flaw be sufficiently embedded that treatment as a subsurface flaw is justified. ASME Section XI, Figures IWA-3310-1,-
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4 33201, and -3330-1 provide criteria for evaluating proximity of flaws to the surface and to each other (in the case of muitiple flaws). In general,if a flaw is closer to the surface than 0.4 of its half-depth, it must be considered to be a surface flaw.
7.0 RECOMMENDED MOCKUP DEFECTS The above analysis shows that a family of significant sized flaws (Figure 4 a, b. c, d) can be accepted in the stru:tural lid to shell weld, while maintaining Code rnargins, and under a conservative set of assumptions.
Ultrasonic examination of the final structural lid weld will be attempted using a mock-up which d"r"--*-- *% FrM :::.:ctr:1 !!d 'd' :::'!;=22.
3 In order to demonstrate the feasibility of the ultrasonic examination process, qualify the technique, and verify the capability for detecting and sizing any observed indications, the mockup will be implanted with flaws which represent the following conditions:
- Crack 0.05" to 0.25" deep and 0.5" long at the weld joint extremes to assure that the weld.
volume can be adequately examined -(Flaws 1-7,8-13,14-19 and 20-25).
Cracks 0.3",0.4", and 0.5" deep and 0.5" long at the weld centerline to provide confidence that large flaws can be detected and sized - (Flaws 28-30).
Welding defects which represent slag (0.1" deep x 0.5" long) and lack of fusion including lack of fusion resulting from weld starts and stops (0.1" to 0.3" deep x 0.375" long)-(Flaws 26,27 and 31-33).
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Appendix C describes the flaws which will be implanted in the mockup for use in demonstrating the feasibility and perfomung the process qualification for ultrasonic examination of the final stmetural lid weld.
Appendix C identifies the defects (size, orientation, and location) which the Owners Group intends to incorporate in the Palisades mockup, for use in volumetric examinations, feasibility demonstrations and process qualification. Multiple flaw configurations (e.g., paralle! Daws in either planar or laminar orientations) are not expressly included in the mock-up, because of the large number of such hypothetical combinations. For evaluation purposes, multiple flaws will be combined in accordance with Section XI proximity rules.
4 The allowable Gaw sizes contained in Tables 3 and 4 are presented as circumferentially oriented defects. The allowable flaw depth are also conservatively applicable to flaws oriented transverse to the weld direction. Circumferentially oriented Daws are more significant with regard to structural adequacy and are not inherently limited in length, as are transverse flaws due to the structural constraints of the geometry. Flaws oriented radially into the shell will not degrade the integrity of the weld, and are not considered here.
8.0 CONCLUSION
S This analysis has shown that flaws with depths greater than those which could have been missed during original weld examination can be accepted under the criteria of AShE Section XI, with a conservative set of assumptions. These results are generic and conservative in nature. Specific Daws exceeding the criteria developed in this calculation could potentially be accepted based upon more detailed analyses and less conservative materials properties on a case-by-case basis.
We recommend that the above results be used as the basis for establishing methods for qualifying volumetric examination techniques for these welds. and for mitial screening of results of field examinations.
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9.0 REFERENCES
1.
Letter from Emil A. Zernick (Consumers Energy) to Hal Gustin (SI), " Flaw Analysis Inputs," dated November 12,1997, transmitting design input information (letter attached as Appendix B). CPC-06Q-201 2.
ASME Boiler and Pressure Vessel Code,Section XI(with Appendix A),1989 Edition.
3.
Rolfe, Stanley T., and Barsom, John, M., Fracture and Faticue Control in Structures, Prentice-Hall,1977.
4 4.
StructuralIntegrity Associates, pc CRACK for Windows, Version 3.0, March 27,1997.
5.
Fax from Tom Burtard (Wisconsin Electric Power Company) to Hal Gustin (SI) dated 11/12/97 and i1/13/97 Charpy Test Results. CPC-06Q 203 6.
Fax from Darrell Williams (ANO) to Hal Gustin (SI) dated 11/11/97: Weld Material CMTRs. CPC-06Q-202 7.
ASM, The Metals Handbook, Vol 1,10th Edition,1990.
8.
NUREG-0313 " Technical Report on Material Selection and Processing Guidelines for BWR Coolant Pressure Boundary Piping," Revision 2.1988.
9.
Letter from Kay Moeckel (Sierra Nuclear) to Hal Gustin (SI) dated 12/12/97. CPC-06Q-204 Revision i
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4 Table 1 TABLE 11.21
SUMMARY
OF STRESSES (ksi) IN THE MSB RESULTING FROM lilE HYPOTHE11 CAL HORIZONTAL DROP e'
ASME Drop Dead Ws.'
Thermal Pressure Toul Albdile Bottom Plass P.
29.4 N/A N/A E06 29.5 490 is v r.
Ma s.i eaJ n.3 Shall P.
25.9 N/A N/A al 26.0 49.0 7 + P.
71J 1.2 73.0 715 6
$tructuraI P.
24 N/A N/A a0 2.6 49.o Ud P + P.
42.9 0.4 433 73.5 6
shield ud P.
2.4 N/A N/A 0.0 2.4 49.0 P + P.
2&6 to 20 6 73.5 6
Bosace Weld P.
219 N/A N/A a2 26I.
49.0 P + P.
444 1.7 4&3 73.5 6
Top Weld P.
7.1 N/A N/A a06 7.2 36 3 i
P + P.
42.9 a4 43.3 Sin 6
Shield Ud P.
9.1 N/A N/A a2 93 36R Wald P + P.
2a6 N/A N/A 02 21.4 51:
6 Dead wight is 3dM in the drop load.
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Table 2 TABLE J.4 !
\\tSB stulS11'51 STRESS EVu.t.% TION C ~ e e--
9 ene C 1LC':'.12 \\'1L':Y '.*Si*
- ta uut SECC P1U23t1t2
- WZ3. MAL ROCL2ic
- ':"*AL
.a t.--
P, 0.1 0.1 N/A 0.9 1.:
- 0J S!!B Shed Ps + P, 0.1 1.2 N/A 2.4 3.7
- 0.7 P+Q at 1.2 1.0 14 4.7 61J Bottom P.
0.02 0.06 N/A 1.0 1.1 20.5 Plate P + P, 0.02 1.7 N/A 1.5 3.2 30,7 6
P+Q 0.02 1.7 19.4 1.5 215 05 Top Ud P,
0.0 0.0 N/A 0.1 0.1
- 0J P + P, -
0.0 0.4 N/A 0.2 0.6 30.7 6P+0 0.0 0.4 0.2 0.2 0.8.
61.5 Bottem.co.
P, O.1 0.2 N/A 0.9 L
- 15 Shell P + P, 0.1 1.7 N/A 1.5 33 30.7 6
function P+Q 0.1 1.7 1.5 IJ 4.3 61.5 ap-to-shea P.
0.0 -
0.06
.N/A 0.2 0.3 15.4
. unction P + P, 0.0 0.4 N/A 0.2 0.6 23.1 6P+Q 0.0 0.4 0.4 0.2 LO 46.1 Sleeve P.
0.05 N/A -
N/A 1.8 1.9 20J Assembly P,. + P.
0.05 N/A N/A 2.1 12 30.7 P+Q 0.05 N/A 52.0 2.1 543 61.5 Shield Ud.
P, 03 0.2 N/A 03 OJ 15.4 to.Shell P + P.
03 0.3 N/A QL4 1.5
.3.1 t
6 Weld P+Q 43 02 1.3 0.4 2.5 46.1 SliNid Ud i
P.
14 N/A N/A Q.3 0.7 114 Support P + P.
14 N/A N/A 03 0.7 23.1 6
Ring Weld P + 0 '-
14 N/A a0 0J 17 46.1 Vamas dmou are maximums irrespee:ne of location Revision 1
Preparer /Date gq /j;.! -
?
Checker /Date gQ,ggy File No. CPC-06Q-301 i
Page 14 of 28
l Table 3 Projected Charpy Data and Allowable Surface Flaw Sizes Charpy Charpy Charpy @
Allowable Plant identifier Percent
@.50 F
@ 0#F O'F KID Depth Shear Average Predicted Actual
@ 0*F (360')
(If Surface Available)
WP 18P4(18 8)(GMAW)
Weld NA 28 55.4 NA 89.6 0.18 Base 18 8 NA 41 68.4 NA 99.6 Point Beach HAZ 18 8 NA 87 114.4 NA 128.8 PQR-W P-17 (SMAW)
Weld NA 84 111.4 NA 127.1 Base NA 40 67.4 NA 98.9 HAZ NA 137 I M.4 NA 154.4
,_m..
l Weld 58 55 82.4 NA 109.3 HAZ 70 80 107.4 NA 124.8 ANO Base 13 33 60.4 NA 93.6 0.20 PQR 398R1 (SMAW)
Weld 50 77 104.4 NA 123.0 HAZ 40 70 97.4 NA 118.8 Base 20 43 70.4 NA 101.0 Weldstar 467H NA 84 111.4 NA 127.1 ESAB 4I323 40 60 87.4 117 112.6 ESAB 37962 27 55 82.4 96 109.3 ANO ESAB 2A50$A02 50 94 121.4 NA 132.7 ESAB 2H408A03 43 96 123.4 NA 133.8 ESAB 2E426G02 63 103 130.4 NA 137.5 ESAB 2K407H03 70 122 149.4 NA 147.2 Revision 1
l l
Preparer /Date y;2/,.;/.gj j
I
( pygg l l
g Checker /Date File No. CPC-06Q-301 Page 15 of 28 l
l Table 3 (continuedi Charpy Charpy Charpy @
Allowable P! ant Identifier Percent
@-50*F
@ O'F 0~F KID Depth l
~
Shear Average Predicted Actual
@0F (360 )
(If Surface l
Available)
Allov Rods 32039 20 56 83.4 9I i10 0 0.24 ESAB 38380 56 99 126.4 135 135.4 ESAB 51122 60 82 109 4 115 125.9 POR-SM LID-D (SMAW) l Base NA 60 87.4 NA 112.6 Weld NA 130 157.4 NA 151.1 HAZ NA 123 150 4 NA I47.7 PQR SM-LID-C(SMAW)
Base NA 70 97.4 NA 118.8 q
Weld NA 92 119.4 NA 131.6 HAZ NA i12 139.4 NA 142 2 Palisades PQR-FC-LID (FCAW) dase NA 35 53.4 NA 111.3 Weld NA 69 96.4 NA 118.2 HAZ NA 141 168.4 NA 156.3 POR-FC-LID (FCAW)
Base NA 64 91.4 NA 115.1 Weld NA 91 118.4 NA 131.0 HAZ NA 158 185.4 NA 164.0 Min Specified Base and Weld NA 15 42.4 NA 78.4 0.15 (15 ft-lb @ -50*F)
Note:
1.
The line labeled " Min Specified" represents calculation results based on 15 ft-lb absorbed energy at -50 F.
2.
All Charpy data represents average results.
Revision 1
Preparer /Date g((it,/ g,/g
/
fg,Q,,,&
l CheckeliDate File No. CPC-06Q-301 Page 16 of 2S I
1 t
Table 4 Projected Charpy Data and Allowable Subsurface Flaw Sizes i
Charpy Charpy Charpy @
Allowable Plant identifier Percent
@ 50*F
@ 0*F 0"F KID Depth Shear Average Predicted Actual
@0F (360')
tlf Subsurface Available)
WP.18P4(18 8)(GMAW)
Weld NA 2;
55 4 NA 89.6 0.30 Base 18 8 NA 41 68 4 NA 99 6 Point Beach HAZ 18 8 NA 87 114.4 NA 128.8 PQR.WP 17 (SMAW)
Weld NA 84 111.4 NA 127.1 Base NA 40 67.4 NA 98.9 HAZ NA 137 164.4 NA 154.4,._, _,,
is.3;s Aam Weld 58 55 82.4 NA 109.3 HAZ 70 80 107.4 NA 124.8 AND Base 13 33 60.4 NA 93.6 0.30 PQR.398R 1 (SM AW)
Weld 50 77 104.4 NA 123.0 HAZ 40 70 97.4 NA 118.8 Base 20 43 70.4 NA 101.0 Weldstar 467H NA 84 I I 1.4 NA 127.I ESAB 41323 40 60 87.4 117 112.6 ESAB 37962 27 55 82.4 96 109.3 ANO ESAB 2A505A02 50 94 121.4 NA 132.7 ESAB 2H408A03 43 96 123.4 NA 133.8 ESAB 2E426G02 63 103 130 4 NA I37.5 ESAB 2K407H03 70 122 149.4 NA 147.2 Revision 1
l Preparer /Date p%i2/
/
/7 G l f/ 'Qg Checker /Date File No. CPC-U6D-301 '
l Page 17 of 28
a Table 4 teontinued) l Charpy Charpy Charpy @
Allowable l
Plant 3 era:6er Percent G.50*F
@ O'F O'F KID Depth Shear A$erage Predicted Actual
@ O'F (360*)
l (If Surface Available)
Allov Rods 32039 20 56 83 4 91 110.0 l'
ESAB 38380 56 99 126.4 135 135.4 ESAB SI122 60 82 109.4 125.9 PQR SM LID-D(SMAW)
Base NA 60 87.4 NA 112.6 WeH NA 130 157.4 NA 151.1 HAZ NA 123 150.4 NA 147.7 PQR SM-LID-C(SMAW)
Base NA 70 97.4 NA i18.8 Weld NA 92 119.4 NA 131.6 HAZ NA
- 12 139 4 NA 142.2 Palisades PQR-FC-LID (FCAW) e nn ao as.*
na
.3 Weld NA 69 96 4 NA i18.2 HAZ NA 141 168.4 NA 156.3 PQR-FC-LID (FCAW)
Base NA 64 91.4 NA-115.1 Weld NA 91 118.4 NA 131.0 HAZ NA 158 185.4 NA 164.0 Min Specified Base and Weld NA 15 42.4 NA 78.4 0.24 (15 ft-Ib @ -50'F)
Note: 1.
For subsurface defects at weld mid wall depth, the allowable through-wall dimension of the defect is generally twice the allowable surface flaw dimension for the corresponding case.
2.
The line labeled " Min Specified" represents calculation results based on 15 ft lb absorbed energy at -50 F.
3.
All Charpy data represents average results.
Revision 1
Preparer /Date
/lM_2// 7/G l
g[ggg Checker /Date File No. CPC-06Q-301 l
Page 18 of 28
l i
\\
w. 3 war,
, ~ t '/z - 1 '/ ', e ~ 1 { f
~-
t__
/
3/32," MAX CAf HClGHT l
As NEA31& RED FLOM MIGNE37 SIDC (LID CA M5B SMELL).
h j!
M j'
T 45' NCM.
4 n=
\\
_r.=
m 4
i
{
EE:ZlrJ :.3 L_.
Figure 1 l
Revision I
l l
l PrepareciDate g) tlq)lrl
.l g /g/f,l l
Checker /Date File No. CPC-060-30!
Page 19 of 28
i 33o 200
/
180 iso Lt
,.o
- ~
I J
Y.,
eass Y
- ioa i
X.
2.78 Ks 4 [n g
so so I
l no tu nruor i
o
,ico
.so o
eso
.im
.nso tr nr.o A **
FIG. A-4200-1 LOWER BOUND Y. AND t. V3 TEMPERATURE CURVE 5 FROM TESTS OF SA-533 GRADE 6 CLA$s 1, SA 508 CLA13 2. AND SA-508 CLASS 3 STEELS Figure 2 Revision 1
l l
Preparer /Date gA ty/,p p l
l g'Qgg j
Checker /Date i
l File No. CPC-060-301 l
Page 20 of 2S l
e h
N N c-Co+C X+C x2+C X3 1
2 3
a,, -..
b:
f f,, '~u i
.4'g; ggw:,,(
w;.
w j6fd5t@i$1 b 0:w*as,,,l $'
n.
s )?kg 2lL ',%?%.;.aik,.
M,s an svw, NS Cn: suricestress(24) i d
7-:g yW i
- s;n L':'Q ??d
' a.5lkh
, y@gw@g4 v...
., _e,
'.j ft.-
'4
,5 3
, UE[P+yg.%
- Chid
,N.V% !
n Mrf+%Q,.x;
~3.
j
%. N'$>$k[LT['35,2+g :408MWs l
-+ x
~
C" u)J REQUIRED NPUTS:
- "v t wallthickness a: maximuncrackdepth(a 50.81)
Figure 3: Single Edge Cracked Plate - LEFM Crack Model 1
4 Revision i
Preparer /Date j/J,ig/,7/9:.
f //.1 / )
Checker /Date
/ 4 fulh4 File No. CPC-06Q.301 '
Page 21 of 28 i
i l
i 1
l
\\
j A __OWABLE SURFACE FLAW S.ZE t
FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7 0.7 OF 15 FT-LB @ -50 DEG, EXTRAPOLATED TO O DEG u.o --
O.6
)
Eg 0.5
-- 0.5
( 0.4 FURTHER EVALUATION REQUIRED g
0.4 m
.2 0 15 2
~~L 0.1 -
ALLO'NABLE FLAW 0.1 0
1 5
,4 S
5 i
10 FLAW LENGTH, IN.
& GREATER Figure 4a l
Revision 1
l l
Preparer /Date //Q;7/j7 9:
l
/
Checker /Date
'Qgg7 l
r File No. CPC-060-301 i
Pace 22 ot' 28 l
u____----__---.----__-----------
i AL_OWABLE SUR= ACE FLAW SIZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7
7 FROM PALISADES DATA AT-50 DEG, EXTRAPOLATED TO O DEG 0.6 v.o FURTHER EVAL _tJAllON_BEQU1 BED
- 0.5 0.5 eg 0.4 0.4 f0.3 0.24 -- 0.3 u.
0.2 0.2 0.1 -
ALLOWABLE FLAW 0.1 0
1 N
4 S
b I
5 b
10 FLAW LENGTH, IN.
& GREATER Figure 4b Revision 1
l Preparer /Date
/)],7/g/ap j'
g Checker /Date File No. CPC-060-301 '
Page 23 of 28
ALLOWABLE SUR ACE LAW SIZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7
^'
FROM POINT BEACH DATA AT -50 DEG, EXTRAPOLATED TO O DEG 0.6
-)
0.6 0
k
.5
\\ FURTHER EVALUATION REQUIRED
- 0. 5 w 0.4-0 0.4 0.3 0.18 0.2 -
j
-0.2 ALLOWABLE FLAW 0.1 -
- 0.1 1
0 1
4 i
10 FLAW LENGTH, IN.
& GREATER Figure 4c Revision 1
l Preparer /Date jfM,3 g,1g9 l
/
Checker /Date gg/g/,7 l
File No. CPC-06Q-301 ' '
l Pace 24 of 28
O s
9 ALLOWABLE SURFACE FLAW SIZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 FROM ANO DATA AT-50 DEG, EXTRAPOLATED TO O DEG 0.6
- 0.6 2,
{-0.5 g
\\ FURTHER EVALUATION REQUIRED
- - - -0.5 1
w 0.4 0.4 1
0.3
- 0.3 0.2-0.2 0.1 0.1 0
1 4
i 10 1
FLAW LENGTH, IN.
Figure 4d Revision i
Preparer /Date /jpp/g/p
((ggg g
Checker /Date File No. CPC-06Q-301 Page 25 of 2S
\\
l Testing temperature. 7
- 100
- 50 0
50 100 150 00 150 i
4
/[
l Im
,"f"--..
1.55% Mn
~"
13 1.01% Mn
,,,,,/",..*
0.23% Mn
//
0.20% Mn
/
[
3g I
/I
/ A fi i
)
=
i a
a l/
l i
?
8 M *
.M l
5 Q
/
/
i 2
E
/
a l
f l
M3
~
g f
//
/
/
l/ *f
/
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/
/
- m
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,/
8 0
- 100
-3
- 5D
-5 0
3 50 M
100 Testing temperature.*C g gg Variation in Charpy V-notch impac energy with temperature for 0.30% C steels containing varying amounts of manganese. The specimens were austonitized at 900 *C (1650 T) and cr)oled at proximately 14 T/ min (25 7/ min). The microstructure of these steels were pearlitic. Source: Ref 6 Figure 5 Revision l
1 Preparer /Date ;]fl 33/p/;;
Checker /Date
'[f 7
File No. CPC-06Q-301 Page 26 of 28
~
o - c, n
b eb REQURED INPUTS:
b:' plate half width 4
- a. nwannun cracx aepta % s u.vo) e i.
1 Figure 6: Center Cracked Plate under Remote Tension Stress - LEFM Crack Model l
l i
I Revision 1
Preparer /Date g g/77/9z Checker /Date gff/g j
File No.. CPC-06Q 301 Page 27 of 28 1
I
INSIDE WALL OUTSIDE wt4L 50 1
I I
I I
1 1
1 1
o GE 26 40(
o GE 26 (4 azimuths)
K a ANL 26 (2 ozimulhs) 30 0 ANL 26 (IN-SERYlCE FROM XRB)
- ANL 20 20 g
a u
9 m_
na
.e.
d i
a av
- *g-M O O O
{
o M
o-O cr@--
f g1 0 -u--
3-- 8 o
- e
=
o a
o a
o e
o t
- -10 o
o q, y
a sfcc/
-20 O
a 4
o A
-30 as e
l I
I I
I I
I.
I I
i 0
0.2 0'.4 0.6 0.8 1.0 l
i c/t Figure 7 Axial Residual Stress Distribution for ?.ulti-Pass Weld frer. (B).
(Dashed line represents scaling of distribution to pr: duce inside surf ace tensile stress of 40 ksi. )
Revision 1
l Preparer /Date
$12/J7/c fl g'[/2f/7[f7l Checker /Date
~
File No. CPC-060-301 ' '
Pace 28 of 2S 1
l
\\
l
\\
l l
l s
I 1
- pocenry 4 pc CRACK Output i
(
Revision l
I Preparer /Date gj g,gg,jg f
Checker /Date File No. CPC-OdQ.~301 ' '
P3"e AJ of 33
4 tm pc-CRACK for Windcws t'er si:n 2. 0, Ma r.
2', ' 1997
,C, C:pyr;;nt '54 - '97 Structural Integrity Associates, Inc.
3315.Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info @structint.com Linear Elastic Fracture Mechanics Date: Tue Dec 16 10:49:01 1997 File: SURFANO.LFM
Title:
CPC-060: Allowable flaw size determination e
Loao cases:
Case: residual --- Stress Distribution Depth Stress 0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000 i
0.4500
-12.0000 l
0.6000
-2.0000 i
O.7500 10.0000 Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff l
residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. crack size:
0.5900
_________________---Stress Intensity Factor--------------------
Crack Case Case Case
(_PC-c40 1 a N/33
Size normal drop residual 0.0118 0.4155 9.06053 5.92216 s.-
0.0236 0.598275 12.9526 7.87386 0.0354 0.740604 16.0341 9.04405 0.0472 0.864264 18.7113 9.76808 0.0590 0.976436 21.1398 10.1856 0.0708 1.08076 23.3985 10.3735 0.0826 1.19487 25.8688 10.5748 0.0944 1.31592 28.4897 10.7542 0.1062 1.43664 31.1033 10.827 0.1160 1.55746 33.719 10.8063 0.1298 1.67869 36.3436 10.7022 0.1416 1.80055 38.982 10.5229 0.1534 1.92952 41.7741 10.3067 0.1652 2.07603 44.9461 10.0972 0.1770 2.22516 48.1746 9.81596 0.1888 2.37689 51.4597 9.46745 0.2006 2.53123 54.8011 9.05601
- 0.rize 2.6081d 3e.1v05 0.38394 0.2242 2.84764 61.6514 8.0615 0.2360 3.04756 65.9797 7.56107 0.2478 3.2547 70.4642 6.97506 0.2596 3.46627 75.0447 6.2977 0.2714 3.68219 79.7194 5.53033 0.2832 3.90237 84.4862 4.67451 0.2950 4.12673 89.3436 3.73199 0.3068 4.4086 95.4461 3.13246 O.3186 4.73656 102.546 2.78244 0.3304 6.07193 109.807 2.37727 0.3422 5.41456 117.225 1.92303 O.3540 5.76429 124.797 1.42617 0.3658 6.12101 132.52 0.893474 0.3776 6.51287 141.004 0.402307 0.3894
.7.0141 151.855 0.106159 0.4012 7.52584 162.934
-0.256648 0.4130 8.0479 174.237
-0.6781 0.4248 8.5801 185.759
-1.14987 0.4366 9.12225 197.497
-1.66333 O.4484 9.6742
-209.446
-2.20947 0.4602 10.5138 227.623
-2.826 7 0.4720 11.4141 247.114
-3.62191 0.4838 12.3317 266.982
-4.59183 0.4956 13.2665 287.219
-5.72798 0.5074 14.21S 307.821
-7.02199 0.5192 15.1862 328.761
-B.46527 0.5310 16.6666 360.831
-10.603 0.5428 15.65S7 403.961
-13.5771 0.5546 20.688 447.895
-16.8818 l
l
(_ ( C - C i:C-5: 1 h]f31
0.5664 22.7538 492.62
-20.4879 0.5782 24.8556 538.125
-24.3654 0.5900 26.993 584,397
-28.4845
' -Material fracture toughness:
Material'ID: ANO-min Depth K1c 0.0000 66.0000 0.3750 66.0000 0.7500 66.0000 Lead combination for critical crack size:
Load Case Scale Factor drop 1.0000 ledAQudi 1.JJVO' Crack Total Size K
Kic 0.0118-16.937 66 0.0236 23.4249 66 0.0354 28.0627 66 0.0472 31.7029 66 0.059 34.6867 66 0.0708 37.1953 66 0.0026 39.9333 66 0.0944 42.7928 66 0.1062 45.5032 66 0.118:
48.0913 66 0.1298 50.5775 66 0.1416 52.9774 66 0.1534 55.482 66 0.1652 58.3753 66
- 0.177 61.2298 66 0.1888 64.0514 66 i
l 0.2006 66.8456 66 0.2124 69.6178 66 0.2242 72.3732 66 l
0.236 76.0359 66 0.2478 79.741 66 0.2596 83.4207 66 0.2714 87.0747 66 C.2832 90.7033 66 l
0.295 94.3072 66 1
M4 '33 C PC-C6 C -30t
/
i
.._____________w
0.3068 99.6123 66 0.3186 106.247 66 0.3304 112.969 66 0.3422
'19.7E3 66 0.354 126.694 66 0.3658 133.708 66 0.3776 141.539 66 0.3894 151.996 66 0.4012 162.593 66 0.413 173.335 66 0.4248 184.23 66 0.4366 195.285 66 i
5 0.4484 206.508 66 0.4602 223.864 66 0.472 242.297 66 0.4838 260.874 66 0.4956 279.601 66 0.5074 298.481 66 0.5192 317.522 66 0.531 346.729 66 0.asiL S45.sv.
oo 0.5546 425.443 66 0.5664 465.371 66 0.5782 505.719 66 0.59 546.513 66 Critical crack size =
0.)969 i
l i
C E ( - 0 L-C - 3 C 1 Mi~f
I l
{
tm pc-CRACK for Windows j
Versitn 3.0, Mar. 27, 1997 1
.0 C:pyrign: 'E4 -
'9-Structural Integrity Associates, Inc.
3315 Almaden Expressway, suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 J
Fax:
408-978-8964 E-mail: info @structint.com l
)
Linear Elastic Fracture Mechanics 1
i Date: Tue Dec 16 10:50:55 1997 File: SURFPB.LEM
Title:
CPC-060: Allowable flaw size determir.ation uvaa vases:
Case: residual --- Stress Distribution Depth Stress 1
0.0000 30.0000 0.1500-0.0000 0.3000
-15.0000 0.4500
-12.0000 l
0.6000
-2.0000
)
0.7500 10.0000 i
Stress Coefficients Case ID C0 C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. ::ack size:
0.5900
Stress :n ens: 3 ractor--------------------
Crack
'ase Case Case i
l l
1 b
b'0bk '3 Cl Al s,[>
/ -~
1 A
1 Size normal drop residual 0.0118 0.4155 9.06153 5.92216 0.0236 0.598275 12.9526 7.87386 0.0354 0.740604 16.0341 9.04405 0.0472 0.864264 18.7113 9.76808 0.0590 0.976436 21.1398 10.1856 0.0708 1.08076 23.3985 10.3735 0.0826 1.19487 25.8688 10.5748 0.0944 1.31592 28.4897 10.7542 0.1062 1.43664 31.1033 10.827 0.1180 1.55746 33.719 10.8063 0.1298 1.67869 36.3436 10.7022 0.1416 1.80055 38.982 10.5229 0.1534 1.92952 41.7741 10.3067 0.1652 2.07603 44.9461 10.0972 0.1770 2.22516 48.1746 9.81596 0.1888 2.37689 51.4597 9 46745 0.2006 2.53123 54.8011 9.05601 U.2129 4.bd513 30.1903 d.3db94 0.2242 2.84764 61.6514 8.0615 0.2360 3.04756 65.9797 7.56107 0.2478 3.2547 70.4642 6.97506 0.2596 3.46627 75.0447 6.2977 0.2714 3.68219 79.7194 5.53033 0.2832 3.90237 84.4862 4.67451 0.2950 4.12673 89.3436 3.73199 0.3068 4.4086 95.4461 3.13246 0.3186 4.73656 102.546 2.78244 0.3304 5.07193 109.807 2.37727 O.3422 5.41456 117.225 1.92303 0.3540 5.76429 124.797 1.42617 0.3658 6.12101 132.52 0.893474 0.3776 6.51287 141.004 0.402307 0.3894 7.0141-151.855 0.106159 0.4012 7.52584 162.934
-0.256648 0.4130 8.0479 174.237
-0.6781 0.4246 8.5801 185.759
-1.14987 0.4366 9.12225 197.497
-1.66333
.0.4484 9.6742 209.446
-2.20947 0.4602 10.5138 227.623
-2.82647 0.4720 11.4141 247.114
-3.62191 0.4838 12.3317 266.982
-4.59183 0.4956 13.2665 287.219
-5.72798 0.5074 14.218 307.821
-7.02199 0.5192 15.1862 328.781
-8.46527 0.5310 16.6666 360.831
-10.603 l
0.542S 1B.6587 403.961
-13.5771 0.5546 20.688 447.895
-16.8818 l
( FC - C 6 G - 3 '01 47 g l
'O.5664 22.7538 492.62
-20.4679 0.5762 24.8556 53e.;25
-24.3654 0.5900 26.993 EB4,397
-29.4545 Material fracture. toughness:
Material :D: PB-man Deptn Kic 0.0000 63.0000 0.3750 63.0000 0.7500 63.0000 Load combination for critical crack s :e:
Load Case Scale Factor drop 1.0000
- s..wwa.
- 4. aiv 7 Crack Total-Size K
K1c 0.0118 16.937 63 0.0236 23.4249 63 0.0354 28.0627 63 0.0472 31.7029 63 0.059 34.6867 63 0.0708 37.1953 63 0.0826 39.9333 63 0.0944 42.7928 63 0.1062 45 5032 63 0.118 48.0913 63 0.1298-50.5775 63 0.1416 52.9774 63 0.1534 55.482 63 0.1652 58.3753 63 0.177 61.2298 63 0.1888 64.0514 63 0.2006 66.8456 63 0.2124 69.6178 63 0.2242 72 3732 63 0.236 76.0359 63 0/2479 79.741 63 0.2596 83.4207 63 0.2714 87.0747 63 0.2932 90.7033 63 0.295 94.3072 63
( hl-bk-Ni 3 33
0.3068 99.6127 63 0.3186 106.247 63 0.3304 112.969 63 0.3422 119.783 63 0.354 126.694 63 O.3658 133.708 63 0.3776 141.539 63 0.3894 151.996 63 0.4012 162.593 63 0.413 173.335 63 0.4248 184.23 63 0.4366 195.285 63 0.4484 206.508 63 0.4602 223.864 63 0.472 242.297 63 0.4838 260.874 63 0.4956 279.601 63 0.5074 298.481 63 0.5192 317.522 63 O.531 346.729 63 0.5428 385.904 63 0.5546 425.443 63 0.5664 465.371 63 0.5782 505.719 63 0.59 546.513 63 Critical crack size =
0.1843 s
6 se
~..'
C PC-C6Q - 3cl g cfl/.
1
l 1
tm-pc-CRACK for Windcws Version 3.0, Mar. 27, 1997 (C) Copyright '94 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-979-8964 E-mail: info @structtnt.com Linear Elastic Fracture Mechanics Dato: Tue Dec 16 10:52:09 1997 File: SURFSPEC.LFM
Title:
CPC-060: Allowable flaw size determination i
Load Cases:
Case: residual --- Stress Distribution Depth Stress 0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000 0.4500
-12.0000 0.6000
-2.0000 0.7500 10.0000 Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. crack size:
0.5900
Stress Intensity Factor--------------------
Crack Case Case Case C f' L - C c a ' 3 -.jvi
/
r i e
-Alc ;,3
~
Size normal d:cp residual 0.0113 0.4185 9.06053 5.92216 0.0236 0.598275 12.9526 7.87386 0.0354 0.740604 16.0341 9.04405 0.0472 0.864264 18.7113 9.76808 0.0590 0.976436 21.1398 10.1856 0.0708 1.08076 23.3985 10.3735 0.0826 1.19487 25.8688 10.5748 0.0944 1.31592 28.4897 10.7542 0.1062 1.43664 31.1033 10.827 0.1180 1.55746 33.719 10.8063 0.1298 1 67869 36.3436 10.7022 0.1416 1.80055 38.982 10.5229 0.1534 1.92952 41.7711 10.3067 0.1652 2.07603 44.9461 10.0972 0.1770 2.22516 48.1746 9.81596 0.1888 2.37689 51.4597 9.46745 0.2006 2.53123 54.8011 9.05601 0.41e4 e.ousis 3d.1983
- n. des 94 0.2242 2.84764 61.6514 8.0615 0.2360 3.04756 65.9797 7.56107 0.2478 3.2547 70.4642 6.97506 0.2596 3.46627 75.0447 6.2977 0.2714 3.68219 79.7194 5.53033 0.2832 3.90237-84.4862 4.67451 0.2950 4.12673 89.3436 3.73199 0.3068 4.4086 95.4461 3.13246 0.3186 4.73656 102.546 2.78244 0.3304 5.07193 100.807 2.37727 0.3422 5.41456' 117.225 1.92303 0.3540 5.76429 124.797 1.42617 0.3658 6.12101 132.52 0.893474 0.3776 6.51287 141.)04 0.402307 0.3894 7.0141 151.855 0.106159 0.4012 7.52584 162.934
-0.256648 0.4130 8.0479 174.237
-0.6781 0.4248 8.5801 185.759
-1.14987 0.4366 9.12225 197.497
-1.66333 0.4484 9.6742 209.446
-2.20947 0.4602 10.5138 227.623
-2.82647 0.4720 11.4141 247.114
-3.62191 0.4838 12.3317 266.982
-4.59183 0.4956 13.2665 287.219
-5.72798 0.5074 14.218 307.821
-7.02199 0.5192 15.1862 328.781
-8.46527 0.5310 16.6666 360.831
-10.603 0.5428 18.6587 403.961
-13.5771 0.5546 20.688 447.895
-16.8818 l
C PC-Cb0*301 l
q e
0.5664 22.7538 492.62
-20.48 9 0.5782 24.8556 538,125
-24.3654 0.5900 26.993 524.397
-25.4645
~ Material fracture toughness:
Material ID: SPEC-min Depth K1c 0.0000 55.0000 0.3750 55.0000 0.7500 55.0000 Load combination for critical crack size:
Load Case Scale Factor drop 1.0000, LealuddA A.JJUU' Crack Total Size K
Kic 0.0118 16.937 55 0.0236 23.4249 55 0.0354 28.0627 55 0.0472 31.7029 55 0.059 34.6867 55 0.0708 37.1953 55
..s 0.0826 39.9333 55 0.0944 42.7928 55 0.1062 45.5032 55 0.116 48.0913 55 0.1298 50.5775 55 0.1416 52.9774 55 0.1534 55.482 55 0.1652 58.3753 55 0.177 61.2298 55 0.1888 64.0514 55 0.2006 66.8456 55 0.2124 69.6178 55 0.2242 72.3732 55 0.236 76.0359 55 0.2478 79.741 55 0.2596 83.4207 55 0.2714 87.0747 55 0.2832 90.7033 55 0.295 94.3072 55 1
l
~$
b j{
}
=
0.3068 99.6123 55 0.3186 106.247 55 0.3304 112.969 55 0.3422 119.783 55 0.354' 126.694 55 0.3658 133.708 55 0.3776 141.539 55 0.3894 151.996 55 0.4012 162.593 55 0.413 173.335 55 I
0.4248 184.23 55 0.4366 195.285 55 0.4484-206.508 55 0.4602 223.864 55
)
0.472 242.297 55 0.4838 260.874 55 0.4956 279.601 55 0.5074 298.481 55 0.5192 317.522 55 0.531 346.729 55 U.042b Jdd.904 b3-0.5546 425.443 55 0.5664 465.371 55 0.5782 505.719 55 0.59 546.513 55 Critical crack size =
0.1515
- ~
kN#
1 i
M4
.c
/t, r\\ s, > 3:
l l
i l
l tm pc-CEACM fcr Windows l
Version 3.0, Mar. 27, 1997 (0 Ccpyr;;nt '94 - '97 Structural Integrity Associates, Inc.
~
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 i
Voice:
408-978-8200 l
Fax:
408-978-8964 l
E-mail: info 9structint.ccm Linear Elastic Fracture Mechanics Date: Tue Dec 16 10:52:56 1997 File: SURFPAL.LEM
Title:
CPC-060: Allowable flaw size determination Loac cases:
1 Case: residual --- Stress Distribution Depth Stress 0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000 0.4500
-12.0000 0.6000
-2.0000 0.7500 10.0000 s..
Stress Coefficients Case ID CO
-C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. crack size:
0.5900
Stress Intensity Factor--------------------
Crack Case Case Case C PC-obo -30 (
4,14/33
L_
Size normal drop residual 0.0118 0.4185 9.06:53 5.92216 0,0236 0.598275 12.9526 7.87386
~
0.0354 0.740604 16.0341 9.04405 0.0472 0.864264 18.7113 9.76808 0.0590 0.976436 21.1398 10.1856 0.0708 1.08076 23.3985 10.3735 0,0826 1.19487 25.8688 10.5748 0.0944 1.31592 28.4897 10.7542 0.1062 1.43664 31.1033 10.827 0.1180 1.55746 33.719 10.8063 0.1298 1.67869 36.3436 10.7022 0.1416 1.80055 38.982 10.5229 0.1534 1.92952 41.7741 10.3067 0.1652 2.07603 44.9461 10.0972 0.1770
'2.22516 48.1746 9.81596 0.1888 2.37689 51.4597 9.46745 0.2006 2.53123 54.8011 9 05601 v.eiew-e.eeeAs so.tses o.cosse 0.2242 2.84764 61.6514 8'.0615 0.2360 3.04756 65.9797 7.56107 0.2478 3.2547 70.4642 6.97506 0.2596 3.46627 75.0447 6.2977 0.2714 3.68219 79.7194 5.53033 0.2832 3.90237 84.4862 4.67451 0.2950 4.12673 89.3436 3.73199 0.3068 4.4086 95.4461 3.13246 0.3186 4.73656 102.546 2.78244 0.3304 5.07193 109.807
.2.37727
..s 0.3422 5.41456 117.225 1.92303 0.3540 5.76429 124.797 1.42617 0.3658 6.12101 132.52 0.893474 0.3776 6.51287 141.004 0.402307 0.3894 7.0141 151.855 0.106159 0.4012 7.52584 162.934
-0.256648 0.4130 8.0479 174.237
-0.6781 0.4248 8.5801 185.759
-1.14987 0.4366 9.12225 197.497
-1.66333 0.4484 9.6742 209.446
-2.20947 0.4602 10.5138 227.623
-2.82647 0.4720 11.4141 247.114
-3.62191 0.4838 12.3317 266.982
-4.59183 0.4956 13.2665 287.219
-5.72798 0.5074 14.218 307.821
-7.02199 0.5192 15.1862 328.781
-8.46527 0.5310 16.6666 360.831
-10.603 0.5428 18.6587 403.961
-13.5771 0.5546 20.688 447.895
-16.8818
)
0.5664 22.7532 492.62
-20.4879 0.5782 24.8556 538.125
-24.3654
.0.5900 26.993 584.397
-28.4845
'~
Material fracture toughness:
Material ID: PAL-min Depth Kic 0.0000 78.0000 0.3750 78.0000 0.7500 78.0000 Load combination for critical crack size.
Load Case Scale Factor drop 1.0000 1.~1 5....
..ss w
Crack Total Size-K K1c 0.0118 16.937 78 0.0236 23.4249 78 0.0354 28.0627 78 0.0472 31.7029 78 0.059 34.6867 78
.0.0708 37.1953 78 0.0826 39.9333 78 0.0944 42.7928 78-0.1062-45.5032 78 0.118 48.0913 78 0.1298 50.5775 78 l
0.1416 52.9774 78-0.1534 55.482 78
.0.1652 58.3753 78 i
0.177 61.2298 78 O.1888 64.0514 78 0.2006 66.8456 78 0.2124 69.6178 78 0.2242 72.3732 78 l
0.236 76.0359 78 l
0.2478 79.741 78 0.2596 83.4207 78 0.2714 87.0747 78 0.2832
-90.7033 78 j
0.295 94.3072 78 1
c PC-06G -3cI Al6 /n
\\
4 0.3068 99.6123 78 l
0.3186 106.247 78 l
0.3304 112.969 78 l
0.3422 119.783 76 l
0.354 126.694 78
)
0.3658 133.708 78 O.3776 141.539 78 0.3894 151.996 78 0.4012 162.593 78 0.413 173.335 78 0.4248 184.23 78 0.4366 195.285 78 0.4484 206.508 78 0.4602 223.864 78 0.472 242.297 78 0.4838 260.874 78 0.4956 279.601 78 0.5074 298.481 78 0.5192 317.522 78 0.531 346.729 78 0.0940 a03.904 18 0.5546 425.443 78 0.5664 465.371 78 0.5782 505.719
/8 0.59 546.513 70 Critical crack size =
0.2423 i.
y.
%W
-i -
~.
f tl
I 1
1 t:
I t
pc-CRACK for Windows Version 3.0. Mar. 27, 1997 (C) C:pyrign: 'S4 - '97 Structural Integrity Associates, :nc.
3315 Almaden Expressway. Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: Info @structint.com l
l i
i Linear Elastic Fracture Mechanics i
Date: Tue Dec 16 14:00:51 1997 File: SUBPAL.LEM
Title:
CPC-060: Allowable flaw size determination Load Cases:
l.
Case: residual --- Stress Distribution Depth Stress C.C000 30.0000 0.1500 0.0000 0.3000
-15.0000 O.4500
-12.0000 0.6000
-2.0000 0.7500 10.0000 i
Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff i
drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Center Cracked Plate Under Remote Tensien Stress l
Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3375 l
l
--- ----------------- s t r e s s In t e n s i t y Fa c t o r ---------- ----------
Crack Case Case Case t
{
( PC-C (: G-3Cl ip a
t E________.__________________.___._
Site normal drop residual 0.0067 C.29;3 6.30664 4.4227 0.0135 0.412197 8.92407 6.25825 0.0202 0.505322 10.9402 7.67213 0.0270 0.584283 12.6497 P.87096 0.0337 0.654384 14.1674 9.93529 0.0405 0.718372 15.5527 10.9068 0.0472 0.777895 16.8414 11.8105 0.0540 0.834048 18.0571 12.6631 0.0607 0.887603 19.2166 13.4762 0.0675 0.93914 20.3324 14.2586 0.0742 0.989108 21.4142 15.0173 0.0810 1.03787 22.4699 15.7576 0.0877 1.08573 23.5061 16.4843 0.0945 1.13295 24.5284 17.2012 0.1012 1.17976 25.5418 17.9119 0.1080 1.22636 26.5506 18.6194 0.1147 1.27294 27.5591 19.3266 0.1215 1.31968 28.571 20.0362
'0.1282 1.36675 29.59 20.7508 0.1350 1.41431 30.6199 21.473 0.1417 1.46255 31.6642 22.2054 0.1485 1.51162 32.7265 22.9503 0.1552 1.56169 33.8106 23.7106 0.1620 1.61296 34.9206 24.489 0.1687 1.66561 36.0604 25.2883 0.1755 1.71984 37.2345 26.1117 0.1822 1.77587 38.4477 26.9625 0.1890 1.83395 39.7051 27.8443 0.1957 1.89434 41.0125 28.7611 0.2025 1.95732 42.3761 29.7174 0.2092 2.02323 43.803 30.7181 0.2160 2.09244 45.3013 31.7687 0.2227 2.16535 46.8798 32.8757 0.2295 2.24245 48.5491 34.0464 0.2362 2.32429 50.321 35.289 0.2430 2.41152 52.2095 36.6133 0.2497 2.5049 54.231 38.031 0.2565 2.60531 56.405 39.5556 0.2632 2.71385 58.7549 41.2035 0.2700 2.83183 61.309 42.9946 0.2767 2.96084 64.1022 44.9534 1
0.2835 3.10291 67.1781 47.1105 0.2902 3.26058 70.5916 49.5043 0.2970 3.43714 74.4141 52.1849 0.3037 3.63692 78.7393 55.2181 0.3105 3.86578 83.6942 58.6928 0.3172 4.13189 89.4555 62.7331 l
1 f
~$ $ U n
~
0.3240 4.44704 96.2784 67.5179 C.3307 4.82904 104.549 73.3176 0.3375 5.306?9
'14.993 20.565*.
Material fracture toughness:
Material ID: PAL-min Depth K1c 0.0000 78.0000 0.3750 78.0000 0.7500 78.0000 Load combination for critical crack size:
Load Case Scale factor dron 1.0000..
residual 1.3300' Crack Total Size K
Kic 0.00675 12.1888 78 0.0135 17.2475 78 0.02025 21.1441 78 0.027 24.4481 78
^'
O.03375 27.3814 78 0.0405 30.0588 78 0.04725 32.5494 78 0.054 34.899 78 0.06075 37.1399 78 0.0675 39.2964 78 0.07425 41.3872 78 0.081 43.4276 78 0.08775 15.4303 78 0.0945 47.4061 78 0.10125 49.3646 78 0.108 51.3144 78 0.11475 53.2634 78 0.1215 55.2191 78 0.12825 57.1886 78 0.135 59.179 78 0.14175 61.1973 78 0.1485 63.2504 78 0.15525 65.3458 78 0.162 67.491 7S 0.16875 69.6939 78
e I
0.1755 71.9631 79 0.18225 74.3078 75 0.189 76.738 78
(
.0.19575 79.2647 7B 0.2025 81.9002 78 0.20925 84.6581 78 0.216 87.5537 78 0.22275 90.6046 78 0.2295 93.8307 78 0.23625 97.2553 78 l
0.243' 100,905 78 0.24975 104.812 78
.0.2565 109.014 78 0.26325 113.556 78 l
0.27 118.492 78 0.27675 123.89 78 0.2835 129.835 78 l
0.29025 136.432 78 0.297 143.82 78 0.30375 152.179 78 0.3105 161.756 78 0.31725 172.891 78 0.324 186.077 78 0.33075 202.061 78 0.3375 222.035 78 Critical crack size =
0.1925 l
1 l
i C PC-cl-G.-3 c l R 3 I /_:.
tm pc-CRACE for Windows l
Version 3.0, Mar. 27, 1997 (0: C0pyright '94 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118 '.557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info @structint.com Linear Elastic Fracture Mechanics Date: Tue Dec 16 14: 01:43 1997 File: SUBANO.LFM j
l
Title:
CPC-060: Allowable flaw size determination I
Loac cases:
Case: residual --- Stress Distribution Depth _
Stress j
0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000 0.4500
-12.0000 0.6000
-2.0000 0.7500 10.0000 s.
Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3375
Stress Intensity Factor--------------------
j Crack Case Case Case i
( k( ~ Cb 5 - 3C l S2z 33
Size normal drep residual 0.0067 0.2913 6.30664 4.4227 0.0135 0.412197 8.92407 6.25825 0.0202 0.505322 10.9402 7.67213 0.0270 0.584283 12.6497 8.87096 0.0337 0.654384 14.1674 9.93529 0.0405 0.718372 15.5527 10.9068 0.0472 0.777895 16.8414 11.8105 0.0540 0.834048 18.0571 12.6631 0.0607 0.887603 19.2166 13.4762 0.0675 0.93914 20.3324 14.2586 0.0742 0.989108 21.4142 15.0173 0.0810 1.03787 22.4699 15.7576 0.0877 1.08573 23.5061 16.4843 0.0945 1,13295 24.5284 17.2012 0.1012 1.??976 25.5418 17.9119 0.1080 1.22636 26,5506 18.6194 0.1147 1.27294 27.5591 19.3266 v.1413 1.41968 20.3/1 2U.0Je2 0.1281 1.36675 29.59 20.7508 0.1350 1.41431 30.6199 21.473 0.1417 1.46255 31.6642 22.2054 0.1485 1.51162 32.7265 22.9503 0.1552 1.56169 33.8106 23.7106 0.1620 1.61296 34.9206 24.489 0.1687 1.66561 36.0604 25.2883 0.1755 1.71984 37.2345 26.1117 0.1822 1.77587 38.4477 26.9625 0.1890 1.03395 39.7051 27.8443 0.1957 1.89434 41.0125 28.7611 0.2025 1.95732 42.3761 29.7174 0.2092 2.02323 43.803 30.7181 0.2160 2.09244 45.3013 31.7687 0.2227 2.16535 46.8798 32.8757 0.2295 2.24245 48.5491 34.0464 0.2362 2.32429 50.321 35.289 0.2430 2.41152 52.2095 36.6133 0.2497 2.5049 54.231 38.031 0.2565 2.60531 56.405 39.5556 0.2632 2.71385 58.7549 41.2035 0.2700 2.83183 61.309 42.9946 0.2767 2.96084 64.1022 44.9534 0.2835 3.10291 67.1781 47.1105 0.2902 3.26058 70.5916 49.5043 0.2970 3.43714 74.4141 52.1849 0.3037 3.63692 78.7393 55.2181 0.3105 3.86578 83.6942 58.6928 0.3172 4.13189 89.4555 62.7331 CPC-ObQ-3Gi j
h!/: 3 / 3 3
7 l
e i
0.3240 4.44704 96.2784 67.5179 0.3307 4.82904 104.549 73.3176 0.3375 5.30629
_14.953 e0.5651
.. Material fracture toughness:
Material ID: ANO-min Depth K1c 0.0000 66.0000 0.3750 66.0000 0.7500 66.0000 l
l Load combination for critical crack size:
Load Case Scale Factor dron 1.0000 residual 1.3300' Crack Total Size K
K1c 0.00675 12.1888 66 0.0135 17.2475 66 0.02025 21.1441 66 0.027 24.4481 66 O.03375' 27.3814 66
~~'
0.0405 30.0588 66 0.04725 32.5494 66 0.054 34.899 66 0.06075 37.1399 66 0.0675 39.2964 66 0.07425 41.3872 66 0.081 43.4276 66 0.08775 45.4303 66 0.0945 47.4061 66 0.10125 49.3646 66 0.108 51.3144 66 0.11475 53.2634 66 0.1215 55.2191 66 0.12825 57.1886 66 0.135 59.179 66 0.14175 61.1973 66 0.1485 63.2504 66 0.15525 65.3458 66 0.162 67.491 66 0.16875 69.6939 66
( fC -CGC - 3 ci Al9 33
0 4
0.1755 71.9631 66 0.18225 74.3078 66 0.189 76.738 66 0.19575 79.2647 66 0.2025-81.9002 66 1
0.20925 84.6581 66 0.216 87.5537 66 0.22275 90.6046 66 0.2295 93.8307 66 0.23625 97.2553 66 0.243 100.905 66 0.24975 104.812 66 0.2565 109.014 66 0.26325 113.556 66 0.27 118.492 66 0.27675 123.89 66 0.2835 129.835 66 0.29025 136.432 66 0.297 143.82 66 n.,o3,s is, 2,a c6 0.3105 161.756 66 0.31725 172.891 66 0.324 186.077 66 0.33075 202.061 66 0.3375 222.035 66 Critical crack size =
0.1574 (PL-C&G -3cl l
Slf 33 N _--____ _ __ --- - _ _ ___ -.__ _ _.- - _._____ _ ___ _ _ _ -__
pc-CRACK for Windows Version 3.0, Mar. 27, 199~
(C) Copyr:ght '84 -
'9-Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info @structint.c m 1
Linear Elastic Fracture Mechanics Date: Tue Dec 16 14:02:59 1997 File: SUBPB.LEM l
Title:
CPC-060: Allowable flaw size determination Load Cases:
Case: residual --- Stress Distribution Depth Stress 0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000 O.4500
-12.0000 0.6000
-2.0000 O.7500 10.0000 Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress
' Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3375
Stress Intensity Facto:--------------------
Crack Case Case Case C PC - G6G - 3 01 rh 2 <o >-,>
s Size normal drop residual 0.0067 0.2913 6.2:664 4.422~
0.0135 0.412197 8.92407 6.25825 0.0202 0.505322 10.9402 7.67213 0.0270 0.584283 12.6497 8.87096 0.0337 0.654384 14.1674 9.93529 0.0405 0.718372 15.5527 10.9068 0.0472 0.777895 16.8414 11.8105 0.0540 0.834048 18.0571 12.6631 0.0607 0.887603 19.2166 13.4762 0.0675 0.93914 20.3324 14.2586 0.0742 0.989108 21.4142 15.0173 0.0810 1.03787 22.4699 15.7576 0.0877 1.08573 23.5061 16.4843 0.0945 1.13295 24.5284 17.2012 D.1012 1.17976 25.5418 17.9119 0.1080 1.22636 26.5506 18.6194 0.1147 1.27294 27.5591 19.3266 0.1215 1.31968 28.571 20.0362 0.1282 1.36675 29.59 20.7508 0.1350 1.41431 30.6199 2'. 473 0.1417 1.46255 31.6642 22.2054 0.1485 1.51162 32.7265 22.9503 0.1552 1.56169 33.8106 23.7106 0.1620 1.61296 34.9206 24.489 0.1687 2.66561 36.0604 25.2883 0.1755 1.71984 37.2345 26.1117 0.1822 1.77587 38.4477 26.9625 0.1890 1.83395 39.7051 27.8443 0.1957 1.89434 41.0125 28.7611
~-
0.2025 1.95732 42.3761 29.7174 0.2092
- 2. (l 3 32 3 43.803 30.7181 0.2160 2.
Cti 15.3013 31.7687 0.2227 2.16535 46.8798 32.8757 0.2295 2.24245 48.5491 34.0464 0.2362 2.32429 50.321 35.289 0.2430 2.41152 52.2095 36.6133 0.2497 2.5049 54.231 38.031 0.2565 2.60531 56.405 39.5556 0.2632 2.71385 58.7549 41.2035 0.2700 2.83183 61.309 42.9946 0.2767 2.96084 64.1022 44.9534 0.2835 3.10291 67.1781 47.1105 0.2902 3.26058 70.5916 49,5043 0.2970 3.43714 74.4141 52.1849 C.3037 3.63692 78.7393 55.2181 C.3105 3.86578 83.6?42 58.6929 C.3172 4.'3189 89.4555 62.7331
( h -C/[-k
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0.3240 4,44704 96.2784 67.5179 0.3307 4.82904 104.549 73.3176 0.3375 5.?O639
'14.E63 93.5651 Material fracture toughness:
Material ID: PB-min Depth K1c 0.0000 63.0000 0.3750 63.0000 0.7500 63.0000 Load combination for critical crack size:
Load Case Scale Factor droo 1.000Q.
residual 1.3300' Crack Total Size K
K1c 0.00675 12.1888 63 0.0135 17.2475 63 0.02025 21.1441 63 0.027 24.4481 63
~
0.03375 27.3814 63 0.0405 30.0588 63 0.04725 32.5494 63 0.054 34.899 63 0.06075' 37.1399 63 0.0675 39.2964 63 0.07425 41.3872 63 0.081 43.4276 63 0.08775 45.4303 63 0.0945 47.4061 63 0.10125 49.3646 63 0.108 51.3144 63 0.11475 53.2634 63 0.1215 55.2191 63 0.12825 57.1886 63 0.135 59.179 63 0.14175 61.1973 63 0.1485 63.2504 63 0.15525 65.3458 63 0.162 67.491 63 0.16875 69.6939 63 C PC - Ob6 ~ 30i o p. l y n
O.1755 71.9631 63 0.18225 74.3078 63 0.189 76.738 63 0.19575 79.2647 63 0.2025 81.9002 63 0.20925 84.6581 63 0.216 87.5537 63 0.22275 90.6046 63 0.2295 93.8307 63 0.23625 97.2553 63 0.243 100.905 63 0.24975 104.812 63 O.2565 109.014 63 0.26325 113.556 63 0.27 118.492 63 0.27675 123.89 63 0.2835 129.835 63 0.29025 136.432 63 0.297 143.82 63 0.30375 152.179 63 U.J103 161./$6 63 0.31725 172.891 63 0.324 186.077 63 0.33075 202.061 63 0.3375 222.035 63 Critical crack size =
0.1478 d*
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to pc-CRACK for Windows Version 3.0, Mar. 27, 1997 (C: Copyrignt '64 -
'9' Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: Info @structint.com Linear Elastic Fracture Mechanics Date: Tue Dec 16 14:03:52 1997 File: SUBSPEC.LEM
Title:
CPC-060: Allowable flaw size determination Loaa Cases:
Case: residual --- Stress Distribution Depth Stress 0.0000 30.0000 0.1500 0.0000 0.3000
-15.0000
~
0.4500
-12.0000 0.6000
-2.0000 0.7500 10.0000 Stress Coefficients Case ID CO C1 C2 C3 Type normal 2
0 0
0 Coeff drop 43.3 0
0 0
Coeff residual 30.3653
-287.02 548.501
-268.861 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3375
Stress Intens;ty Fac:cr--------------------
Crack Case Case Case
( fl-C6G -M '
1 ?% i
}
Size normal drop residual 0.0;67 0.29'3 6.30664 4.4227 0.0135 0.412197 8.92407 6.25825 0.0202 0.505322 10.9402 7.67213 0.0270 0.584283 12.6497 8.87096 0.0337.
0.654384 14.1674 9.93529 0.0405 0.718372 15.5527 10.9068 0.0472 0.777895 16.8414 11.8105 0.0540 0.834048 18.0571 12.6631 0.0607 0.8876d3 19.2166 13.4762 0.0675 0.93914 20.3324 14.2586 0.0742 0.989108 21.4142 15.0173 0.0810 1.03787 22.4699 15.7576 0.0877 1.08573 23.5061 16.4843 0.0945 1.13295 24.5284 17.2012 0.1012 1.17976 25.5418 17.9119 0.1080 1.22636 26.5506 18.6194 0.1147 1.27294 27.5591 19.3266 v.141s 1.J19o0 20.3/1 20.03ez 0.1282 1.36675 29.59 20.7508 0.1350 1.41431 30.6199 21.473 0.1417 1.46255-31.6642 22.2054 0.1485 1.51162 32.7265 22.9503 0.1552 1.56169 33.8106 23.7106 0.1620 1.61296 34.9206 24.489 0.1687 1.66561 36.0604
'25.2883 0.1755 1.71984 37.2345 26.1117 O.1822 1.77587 38.4477 26.9625 0.1890 1.83395 39.7051 27.8443 0.1957 1.89434 41.0125 28.7611 0.2025 1.95732 42.3761 29.7174 0.2092 2.02323 43.803 30.7181 0.2160 2.09244 45.3013 31.7687 0.2227 2.16535 46.8798 32.8757 0.2295 2.24245 48.5491 34.0464 0.2362 2.32429 50.321 35.289 0.2430 2.41152 52.2095 36.6133 0.2497 2.5049 54.231 38.031 0.2565 2.60531 56.405 39.5556 0.2632 2.71385 58.7549 41.2035 0.2700 2.83183 61.309 42.9946 0.2767 2.96084 64.1022 44.9534 i
0.2835 3.10291 67.1781 47.1105 0.2902 3.26058 70.5916 49.5043 0.2970 3.43714 74.4141 52.1849 0.3037 3.63692 79.7393 55.2181 0.3105 3.86578 83.6942 58.6929 0.3172 4.13189 89.4555 62.7331 L.Q -o b G - 3 0!
A 31 l3 3
/
t__z______
_______._ _ ___j
0.3240 4.44704 96.2784 67.5179 0.3307 4.92904 104.549 73.3176 0.3375 5.?S6?9
'.14.993
!:.565*.
Material fracture toughness:
Material ID: SPEC-min Depth Kle 0.0000 55.0000 0.3750 55.0000 0.7500 55.0000 Load combination for critical crack size:
Load Case Scale Factor drop 1.000Q, resicual 1.3300 Crack Total Size K
K1c 0.00675 12.1888 55 0.0135 17.2475 55 0.02025 21.1441 55 0.027 24.4481 55 O.03375 27.3814 55 0 0405 30.0588 55 0.04725 32.5494 55 0.054 34.899 55 0.06075 37.1399 55 0.0675 39.2964 55 0.07425 41.3872 55 0.081 43.4276 55 0.08775 45.4303 55 0.0945 47.4061 55 0.10125 49.3646 55 0.108 51.3144 55 0.11475 53.2634 55 0.1215 55.2191 55 0.12825 57.1886 55 0.135 59.179 55 0.14175 61.1973 55 0.1485 63.2504 55 0.15525 65.3458 55 0.162 67.491 55 0l16875 69.6939 55 A32/33
i I
0.1755 71.9631 55 l
0.18225 74.3078 55 L
0.189 76.738 55 I
0.19575 79.2647 55 0.2025 81.9002 55 l.
0.20925 84.6581 55
{
l 0.216 87.5537 55 1
0.22275 90.6046 55 l
0.2295 93.8307 55 1
0.23625 97.2553 55 l
0.243
'100.905 55 b256 109.
55 0.26325 113.556 55 0.27 118.492 55 0.27675 123.89 55 0.2835 129.835 55 0.29025 136.432 55 0.297 143.82 55
'O.30375 152.179 55 0.3105 161.756 55 0.31725 172.891 55 0.324 186.077 55 0.33075 202.061 55 0.3375 222.035 55 Critical crack size =
0.1208 l
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t APPENDIX B Design Input from Consumers Energy 8%ee*
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Revision I
PrepareuDate l;j[f Q-l :
CheckenDate lp'/4 l
~~
l File No. CPC-060-301 Page B1 of Il
l^
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Hm:es !.ac. ear p:an:
2'?!)Ese S:ar Memor.sa rsa-Cove!. Mt 49 43 November 12,1997 Mr. Hal Gustin Structural Integrity Associates. Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557
SUBJECT:
Flaw Analysis inputs Deer Hat-m This letter transmits design inputs for use in the flaw analysis being provided under purchase order C0025456. The specific design inputs shown below are enclosed.
Safety Analysis Report for the Ventilated Storage System, PSN-91-001, Rev 0, dated October 1991, Table 11.21, Summary of Stresses (ksi) in the MSB Resulting from the Hypothetical Horizontal Drop. The limiting event for the structurallid weld is the horizontal drop accident, which is considered to be an emergency / faulted event.
Safety Analysis Report for the Ventilated Storage System, PSN 91-001, Rev 0, dated
~
October 1991, Table 3.4-5, MSB Maximum Stress Evaluation.
Certificate of Compliance ( C of C) for Dry Spent Fuel Storage Casks (No.1007),
effective May 7,1993, Section 1.2.13, Minimum Temperature for Moving the MSB.
Certificate of Compliance ( C of C) for Dry Spent Fuel Storage Casks (No.1007),
I e
effective May 7,1993, Section 1.2.14, Minimum Temperature for Lifting the MTC.
Certified Material Test Reports (Lot No. 32039 and 38380) for the weld material used on the structurallid welds in MSB's 1 13 are enclosed. The CMTR (Lot No. 51122) for the weld material to be used on future structurallid welds is also enclosed. The cask structural lid welds will remain in the as welded condition following welding.
Please give me a callif you have any questions.
l I
Sincerely, -
Emil A.
ernick p7 Engineering Lead -Dry Fuel Storage dN
'~
RECE!VED
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StSB StAXINIDI STRESS EVALUATION r
C - ~'re.t St-sses CALCULATED V ALUE. KSI' OE.C qug M cMT PRES 3tlR.E
- hTAMA1.
HASDI*NG
?O~Af.
. :. t.--
P.
0.1 0.1 N/A 0.9 1.1 20.5 htSB Shell P + P, 0.1 1.2 N/A 2.4 3.7 30.7 tP+Q 0.1 1.2 1.0 2.4 4.7 61.5
. Bottom P.
0.02 0.06 N/A 1.0 1.1 20.5 Plate P + P.
0.02 1.7 N/A 1.5 3.2 30.7 t
. a...
,., 4 c,
r,v w.m Top Lid P.
0.0 0.0 N/A 0.1 0.1 20.5 P + P, 0.0 0.4 N/A 0.2 0.6 30.7 t
l P+Q 0.0 0.4 0.2 0.2 0.8 61.5 Bottom-to-P.
0.1 0.2 N/A 0.9 1.2 20.5 Shell Po + P.
0.1 1.7 N/A 1.5 3.3 30.7 function P+Q 0.1 1.7 1.5 1.5 4.8 61.5 e
- - ap-to shell P.
0.0 0.06 N/A 0.2 03 15.4
. unction P + P.
0.0 0.4 N/A 0.2 0.6 23.1 t
P+Q 0.0 0.4 0.4 0.2 1.0 46.1 Sleeve P.
0.05 N/A N/A 1.8 1.9 20.5 P. + P.
0.05 N/A N/A 2.1 2.2 30.7 Assembly tP+Q 0.05 N/A 52.0 2.1 54.2 61.5 l_
Shield Lid-P.
03 0.2 N/A 03 0.8 15.4 to-Shell Po + P.
03 0.8 N/A 0.4 1.5 23.1 Weld P+Q 03 0.8 13 0.4 2.8 46.1 Sliield Lid P,
0.4 N/A N/A 03 0.7 15.4 Support P + P, 0.4 N/A N/A 0.3 0.7 23.1 Ring Weld P+Q-0.4 N/A 0.0 03 0.7 46.1 6
1 l
Values shown are maximums irrespective of location s:
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1.2.13 Minimum Tem 0erature for Moving the MSB Limit / Specification:
Movement of the MSB inside the VCC.,ill :ni f te al':,,ec a.
ambient temperatures of O' F or above.
Objective:
To avoid the potential for brittle failure.
Action:
Confirm that the ambient temperature is above 03 F immediately before moving the MSB, while inside the VCC.
Surveillance:
The ambient temperatures shall be measured before movement of the MSB.
Basis:
Each MSB shell material will have shown, during fabrication, by Charpy test (per ASTM A370) that it has 15 ft-lb of absorbed energy at -50' F; and, therefore, movement of the MSB 8
at temperatures above 0 F will avoid the potential for brittle fracture.
Calculations show that the MSB shell minimum temperature will be substantially above the ambient 8
temperature (e.g., 20 F for 25-year-old fuel). However, for conservatism and simplicity, it is recomended that the ambient be selected as the minimum MSB movement temperature.
It is highly unlikely that any MSB movement activity would l
take place at temperatures below zero.
Nevertheless, if movement at a temperature below that specified is necessary, calculations (similar to those presented in Chapter 4 of the SAR) may be used to estimate the minimum MSB shell temperature for any particular ambient condition.
O l
m.
A-28 di'l-CG(I-3f'
[j5
I
'.2.14 Minimum Temperature for L f ting the MTC Limit / Specification:
l The MTC shall be allowed to be used to move the MSB if ne 8
ambient temperature is 40 F or above.
j Objective:
To avoid the potential for brittle failure.
Action:
Confirm that the ambient temperature is above 408 F before l
moving the MSB inside the MTC.
Surveillance:
The MTC ambient temperature shall be determined before movement of the MSB in the MTC.
i Basis:
The MTC material will have shown, during fabrication, that it 8
has 15 ft-lb of absorbed energy at 0 F.
Having Charpy test 8
results, at 0 F, which show ductilit) (or other appropriate test to show that the Nil Ductility Ter:perature is lower than 80 F), will avoid the potential for brittle failure when the cask is moved at 40' F or higher. The MTC shell will have a temperature higher than ambient due to the heat source from the irradiated fuel.
- However, for conservatism and simplicity, it is recomended that the ambient temperature be used as the minimum shell temperature.
If movement at lower l
temperatures is ever required, additional specific analysis or other actions that meet the approval of the NRC must be provided.
l-1 1
1 A-29
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O HANOVER, PA 17331 CERTITIE b b b 7EST REPORT WELDSTAR COMPANY Customer Order No.: 2244A-A
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. AURORA, IL 60304._ -
This Material Conforms to Specification:
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Years PHONE (630) 859-3100 AURORA.(L 6050? 1150 P.O BOX 1150
+
CERTDICATE OF COMPLIANCE ISSUED August 22,1997 CUSTOMER: Consumers Energy CUSTOMER PO#: G0238240 SHIP TICKET P.
N917295 DESCRIPTION: 495 lbs. spooled de (33# spoob) ESAB e.c. p.,r,3.,.r e im. vim <run i
la #51122 h mw+M ChflWsk one mpy per item, covers the matmal shrpped a6amst the abon referenced pun:hase order r.:nber h above raatmal will med code requzrernents of ASME Sectro II, Part C and Secoon III 1986 Edideo through 1988 Adderria NB2400 fcr Clas 1 matmal, with special impact propertaes of15 ft/lla mzazmum absorbed energy at-50' F, and the requrmur:ts ofASME Boiler and Pressure Vessel Code current edroco and addenda for Section II, C, SFA 5.20, and is in ec:::pliance with the above referenced purchase order number We certi.fy that the matmal shrpped has been handled in compliance with our i<6hrW and ven5 canon program.
All vendors on Weldstar's approved vendor 1:st have been audited by Weldstar.
Weldstar's Quahty Assurance Program Revision K, da.ted November 12,1996 meets the requ:re:nents of ASME Section III, NCA-3800,1995 hna.
The provisions ofNRC 100R Part 21 apply to this order.
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1750 MITCHELL RCAD. AURORA. IL 6C5%9594 PHONE 630) 25-3100 1000 E. MAIN STREET, LOGANSPORT. ;ND. 46947 5011 PHONE (219) 7221177 2E50 BCND STREET. UNIVERSITY PARK. 'l 60466 3181 PPCNE PC8) 5%5f 61
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lif W h kb November 26,1997 Stua2.
SNC 97-121 4%
Q Mr. Timothy Kobetz Nw U.S. Nuclear Regulatory Commission Qg%@
l1555 Rockville Pike beg-Rockville,MD 20852
Subject:
Hardcopy Transmittal of Calculation Package CPC-06Q-30); Attaclunent to Response to Question 4 of Request for Additional Information Concerning CAL 97-7-001 Dear Mr. Kobetz Sierra Nuclear Corporation (SNC) submits the attached hardcopy of calculation package CPC-06Q-301; as part of the response to Question 4 of Request for Additional Information concerning CAL 97-7-001. Should you or the Commission have any additional questions please contact me et Sierra Nuclear Corporation (SNC); 408 - 438 - 6444.
Respectfully, M
Kay occkel y
M er, Licensing cc: G.Dixon, J.Massey; LicRile; c:\\ltr\\nrcrai4 k
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STRUCTURAL CALCULATION FILE No: CPC-06Q 301 l
INTEGRITY PACKAGE PROJECT No: CPC-06Q Associates, Inc.
PROJECT NAME: Analytical Support for Dry Spent Fuel Storage Activities CLIENT: Consumers Energy (Palisades Nuclear Plant)
CALCULATION TITLE:
Allowable Flaw Size Definition for VSC-24 Dry Storage Cask Structural Lid to Shell Weld i
l PROBLEM STATEMENT OR OBJECTIVE OF THE CALCULATION:
l Develop Weld Flaw Acceptance Criteria i
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l Project Mgr.
Preparer (s) &
Document Affected Revision Description Approval Checker (s)
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0 1 - 24 OriginalIsr t Appendix A Hf?
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SIC-97-039 Page 1 of 24 E
e
I.0 INTRODUCTION The purpose of this calculation is to develop acceptance criteria for flaws which may be detected in the structural lid to shell welds of spent fuel dry storage casks at Palisades, Point Beach, and ANO Nuclear Plants. The geometry of the structural lid to shelljoint is illustrated in Figure 1 {1].
For the casks which are currently in service, nondestructive examination of these welds has included dye penetrant examination of the root and final welded layers. No volumetric examination of these welds has been perforTned in the past, but the plant owners are considering such examination as a result of discussions with the NRC.
2.0 CODE APPLICABILITY In the present analysis, the methods of ASME Section XI,IWB-3600 and Appendix A [2] are used to determine allowable flaw sizes under the limiting loading conditions. IWB-3600 and Appendix A are directly applicable to Class 1 vessels (such as reactor vessels) and piping. Although the dry fuel storage casks are Class 2 (NC) vessels, Section IWC-3600 is still under development, and Section XI permits the use of IWB criteria for flaw evaluations.
Section XI flaw evaluation criteria are directly applicable for evaluation of flaw indications detected in the structural lid welds of casks which are already in service. Its applicability is less clear for examination results for new casks. However, for examinations of structural lid welds which are performed immediately upon completion prior to putting them in service, it is SI's opinion that the rules of Section XI should still be applied, in lieu of Section III rules. Although a loaded cask is not formally considered to be "in operation" until it is successfully transferred to the storage pad, the cask is performing its design function in a difficult to reverse manner once fuel is loaded and the 1
shield lid and structural lid are in place.Section XI provides more extensive methods for the Revision 0
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,a evaluation of defects' detected by volumetric examination, and volumetric examination of the structural lid weld immediately following completion forms a baseline for any subsequent inservice inspections by similar methods.
3.0 LOAD DEFINITION Table 1 [1] provides stress data for the structural lid weld under the horizontal drop accident. This i
event is considered to be an emergency / faulted class (service level C/D) event. Table 2 [1] presents stress data for normal operating events. By comparing the Tables, it can be seen that at the own'ral lid wald the norm =1 o,watine ctreues are civnificantiv lower than the stresses which are predicted to result from the horizontal drop event. Therefore, the horizontal drop accident is judged to govern the critical flaw size determination.
As shown on Table 1, the horizontal drop event produces the following stresses in the structurallid-to-shell weld:
Pm = 7.2 ksi P.+ Pa = 43.3 ksi t
~
In the fracture mechanics analysis below, boJi of these stress components were included. The second (bending) component was modeled as linear through weld bending, with the 43.3 ksi applied as tension on the inside surface (root) of the weld, which is assumed to be the origin of any observed cracks.
In addition to these two load components, weld residual stress was included in the calculation.
Because no measurements or calculations of weld residual stress were available, the weld residual i
stress was assumed to be represented by a constant tensile stress through the weld thickness.
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Appendix A of Section XI [2] requires the use of residual stresses in determination of allowable flaw sizes. However,it is overly conservative to treat such steady state secondary stresses equally with primary stresses resulting from normal operation (e.g. prcrsure) or accidents (such as the horizontal drop event). Appendix H of Section XI defines treatment of residual stresses in a manner which is judged to be appropriate for evaluation of flaws in the structural lid weld. This appendi).
requires that residual stresses be included, but with a safety factor of 1, rather than the Section }3 specified factors for code-limited types of stress.
i For normal operating conditions, the limiting applied stress intensity Ki (applied) is:
l.
K (applied )< dI5 i
where Ko calculated from the projected Charpy data is used as the critical stress intensity. The safety factor of 86 is as defined in Section IWB-3612. Ko is equivalent to Ku as discussed above. For this case, the total applied stress intensity Ki (applied) is determined from the 1
membrane, bending, and residual stresses as i
Ki(applied) = Ki(membrane) + Ki(bending)
+ K ( residual) i
((
Kg(residual) where the reflects the safety factor of I for the residual stress case.
SIN
' For the emergency / faulted case (horizontal drop), it is still appropriate (and conservative) to use the calculated Km as the criterion, because of the dynamic nature of the loading,instead of the Kic (which would be appropriate for static or slow loading rates). For this case (horizontal drop) the applied Kiis limited by Revision 0
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.f Kp applied -drop > < F' E 42 The applied K using a safety factor of 1.0 on residual stresses as discussed above, would be given i
by:
l l
Kr(membrane) + Kr(bending) + Kg(residual) '
Ki(applied)
=
- =m, h== e.e.c.-w.e ecp =- 5:. c--s+ m: em ~m ; m:W,: --
(impact), residual stresses may not be able to redistribute during the horizontal drop case as they would during slower or static cases. In fact. for the initial horizontal drop impact. residual stresses may in fact behave more like primary stresses over the shon interval of the drop impact.
Consequently, for this case, residual stresses are conservatively treated as primary membrane stresses, using the full code safety margin of E.
I The magnitude of the residual stress is assumed to be a constant 30 ksi tensile value through the l
weld thickness. This value was selected based upon consideration of the base material yield stress, i
1 with consideration of anticipated reduction of residual stresses in the inner (near root) layers of the weld due to application of subsequent welded layers.
i 4.0 MATERIAL FRACTURE TOUGHNESS The certified material test repons (CMTRs) [1,5,6] for the structurallid weld material were provided by the plant owners. These documents contain Charpy V-Notch Impact data taken at -
50 F (and some data at other temperatures). According to the "Cenificate of Conformance for the Revision 0
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VSC-24 System" [9] in Section 1.2.13. there are administrative linuts which prevent moving of the storage casks when the temperature is less than 0*F. Consequently. a horizontal drop accident is judged not to be possible below this temperature.
Article A-4000 of Appendix A to Section XI [2] recommends that the material fracture toughness be determined from the actual material and product form in question. Therefore, to evaluate the i
fracture toughness of this material, use of the actual Charpy data at 0 F is appropriate. The Charpy data at O'F is used to determine material fracture toughness (Kic) using the following equation for carbon steel in the transition temperature region [3):
Ko= 3/5C,E In this equation, E was assumed to be 29,000 ksi.
Judging from the % shear data, the material is in the transition region in the -50 F to 0*F temperature range, so use of this equation is appropriate [3]. Also, the Charpy correlation is for Ko (dynamic) fracture toughness as well as Kic (static), so it is applicable to a dynamic event like the drop accident.
As noted above, the material specifications require Charpy V-notch test results at -50 F, while the lowest temperature at which a horizontal drop could occur is 0 F, due to administrative limits [1].
All three plants (Palisades, Point Beach, ANO) provided CMTRs for weld material used (or proposed for use) in the structural lid welds [1,5,6) and these CMTRs included Charpy data at -
50*F. Although all CMTRs include data for both as-welded and stress relieved conditions, the as-welded condition is applicable to all three plants, so that data will be used.
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In order to determine allowable flaw sizes for each plant it is appropriate to use material toughness j
at the limiting temperature of 0*F. Since such data is not available in most cases, it is necessary to extrapolate toughness at O'F from the available -50 F data.
The data from all CMTRs shows that the material is in the transition region (reported per cent shear of 20 80%) and so linear projection is appropriate. Referring to Figure 5 from [7),the slope of this curve is estimated as 0.55 ft-lb/ F for the high manganese curve, which describes a material sirrilar to the 516 Grade 70 base metal. This slope was used to project all reponed weld metal -50*F data
[1,5,6] to 0 F. The results are shown in Table 3. Also, all available Charpy data from CMTRs
[1,5,6] at 0 F is shown in Table 3 for compariwn. The predicted 0 F Charpy data for weld metal is conservative compared to all available actual 0*F data. Inat is, tne predicted Cnarpy results at ut (based on extrapolation of-50 data) are consistently lower than actual data at O'F.
Each of predicted Charpy absorbed energy results at 0*F were used to calculate a material toughness Kro for use in allowable flaw size calculations.
The resulting fracture toughness 0*F is generally greater than 75 ksi-d. This is shown in Figure 2 in comparison to ASME Section XI fracture toughness curves for carbon and low nloy steel reactor pressure vessel bounding materials. Figure 4 shows allowable flaw size (depth versus length) for a toughness of 78.4 ksi-En', which results from extrapolation of the minimum specified Charpy V-notch absorbed energy of 15 ft-lb at -50*F.
5.0 APPLICATION OF ASME CODE MARGINS As discussed above, the limiting event for the structural lid weld is the horizontal drop accident.
l which is considered to be an emergency / faulted event. The stresses associated with this event are defined in Table 1 from [1].
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._-_________._.-.,n
o Using the rules of IWB-3613(c) [2], the fracture toughness values determined above are reduced by a factor of v5 to define the limiting allowable Ki for flaws in the stmetural lid weld under emergency / faulted conditions. That is.
l K so.e< K i
For example, a limiting Kro calculated from Chagy data of 78.8 ksi-E produces an allowable Kr of 55.4 ksi-M. This value corresponds to the value obtained by extrapolating the minimum specified toughness (15 ft-lb at -50 F) to O'F as discussed above.
6.0 ALLOWABLE FLAW CALCULATIONS Using the above load definitions and fracture toughness, a series of allowable flaw size calculations were performed using the Structural Integrity Associates computer program pc CRACK * [4],
which has been developed and verified under the SI Quality Assurance program.
6.1 Surface Flaws The structural lid weld was modeled as a plate with an elliptical surface crack subject to both membrane and bending stresses. This model is illustrated in Figure 3. Use of this flat plate model for flaws in the stmetural lid to shell weld is appropriate for flaws originating in the vicinity of the weld root and propagating through the weld material or weld base metal interface. This model is conservative compared to the actual weld geometry, because the actual weld experiences significant hoop constraint due to the stiffness of the structural lid and cask shell. Such constraint will limit crack opening in the actual weld as compared to the model, and therefore a larger crack would be l Revision 0
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l tolerable in the actual weld than is predicted bv use of the flat plate model. These results are equally applicable to flaws originating on the outside surface and onented inward.
The flaw aspect ratio (the ratio of flaw depth to length) was varied parametrically, to determine an allowable flaw depth versus length curve. The conservative fracture toughness including the emergency / faulted Code margins was used as the criterion for determining allowable flaw depth for each aspect ratio.
The results are shown in Figure 4, and the supporting pc CRACK analyses are attached in Appendix A. There is no known mechanism for continued crack propagation of defects in these 7:d:, :c :: :rxh r: d :d2*.i:nr 5~ e b-r "^~-d
'~ '"- =""m d d-fe" I imi'%
allowable flaw depths for each heat of weld material at each plant are shown in Table 3.
6.2 Subsurface Flaws The above discussion addressed the determination of allowable flaw sizes for flaws which are connected to the surface of the weld, under a conservative set of assumptions. The weld could also contain subsurface defects as a result of the welding process for example. In general, the allowable flaw size for a subsurface defect will be larger (usually twice or greater) than for a surface defect under the same conditions.
Evaluation of allowable subsurface defects was performed using the same linear elastic fracture mechanics techniques as were described above for surface defects. For these cases, a center cracked plate model (Figure 6) was used to evaluate the infinite length flaw. This model is conservative for the actual cases, since it treats applied stresses as pure tension, while for the subsurface flaw cases, the drop load case has a significant through-wall bending component. Consequently, for a subsurface flaw the stresses due to the drop event will be significantly lower than the 43.3 ksi surface stress for this event (see page 3). The calculated allowable flaw sizes for subsurface flaws Revision l
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corresponding to the same assumptions presented in Table 3 for surface flaws are shown in Table 4.
The allowable subsurface flaw results presented in Table 4 also require that the Daw be sufficiently i
embedded that treatment as a subsurface flaw is justified. ASME Section XI, Figures IWA-3310-1,
-3320-1. and -3330-1 provide criteria for evaluating proximity of flaws to the surface and to each other (in the case of multiple flaws). In general, if a flaw is closer to the surface than 0.4 ofits half-depth, it must be considered to be a surface flaw.
j 7.0 RECOMMENDED MOCKUP DEFECTS The above analysis shows that a family of significant sized flaws (Figure 4) can be accepted in the structural lid to shell weld, while maintaining Code margins, and under a conservative set of assumptions.
For the existing operating casks. the nondestructive examination performed as a part of accepting these welds included dye penetrant examination of the root pass. Such an examination would have detected defects which had penetrated the root pass surface. Consequently, it is concluded that the most likely defects in these welds are limited in size to less than the root pass thickness. The root pass is assumed to be about 0.1 inch in thickness. Therefore, we recommend that a mockup to be used for qualification of volumetric examination techniques include indications in the root of the weld which are equal to the root pass thickness (e.g.,0.1 inch deep), to test detection capability. To test defect sizing capability, we suggest that a range of flaws with depths from 0.05 inch to perhaps j
0.25 inch be included, witn orientations along and normal to the weld direction, and directed through the weld metal, along the lid to weld interface. and along the shell to weld interface.
Indications of various aspect ratios in the range of 0.1 to 0.5 should be considered. Implanted flaws will give results which are most representative of those to be expected in actual casks.
With regard to embedded defects representative of welding defects. the most likely defects are interbead lack of fusion and lack of penetration at both weld metal-base metal interfaces. Where the Revision 0
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l weld was made with a flux shielded process (such as is the case at Palisades and ANO), slag inclusions could also occur Representative defects of these types should also be included in the mockups, with sizes in the same range as the above root defects.
8.0 CONCLUSION
S l
This analysis has shown that flaws with depths greater than those which could have been missed during original weld examination can be accepted under the criteria of ASME Section XI, with a conservative set of assumptions. These results re generic and conservative in nature. Specific flaws exceeding the criteria developed in this calculation could potentially be accepted based upon more detailed analyses and less conservative materials properties on a case-by-case basis.
We recommend that the above results be used as the basis for establishing methods for qualifying volumetric examination techniques for these welds, and for initial screening of results of field b
examinations.
9.0 REFERENCES
dated November 12,1997, transmitting design mput information (letter attached as Appendix B).
- 2. ASME Boiler and Pressure Vessel Code,Section XI(with Appendix A),1989 Edition.
' 3. Rolfe, Stanley T., and Barsom, John, M., Fracture and Faticue Control in Struerures, Prentice-Hall,1977.
- 4. Structural Integrity Associates, pc CRACK
- for Windows, Version 3.0, March 27,1997.
S. Fax from Tom Burtard (Wisconsin Electric Power Company) to Hal Gustin (SI) dated 11/12/97 and 11/13/97 Charpy Test Results.
- 7. ASM, The Metals Handbook. Vol 1,10th Edition,1990.
Revision l
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Checker /Date [.yg
..,. m l l
File No. CPC-06Q 301 I
Pace 11 of 24
Table 1 TABLE 11.21
SUMMARY
OF STRESSES (kai) IN THE MSB RESULTING FROM THE HYPonlEnCAL HORIZOffTAL DROP ASME i
ts-,-.
nm.,
t w wte n-.i
- Nwn, To,e 4
,,..gic Bassos Plass P.
29.4 N/A N/A a06 29.5 49 0 P + P.
444 L7 463 73.5 6
Shall P.
219 N/A N/A a1 26.0 49.0 P + P.
71J 1.2 73 0 73.5 6
Structural P.
24 N/A N/A Q.0 2.6 49D 1.id P + P.
42.9 a4 43J 73.5 l
6 Shield Lid P.
2.4 N/A N/A no 2.4 492 P + P.
W 40 204 73.5 6
Botaan Weid P.
219 N/A N/A Q2 26.1 49.0 P + P.
4(6 1.7 463 73.5 6
Top Wald P.
7.1 N/A N/A GD6 7.2 363 P + P.
42.9 R4 433 55.1 6
Shield Ud P.
9.1 N/A N/A R2 93 36.M Wekt P + P.
M N/A N/A a8 21.4 55.1 6
Dead weight is included in the drop load.
l Revision 0
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Checker /Date /r c /. - l l
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1 File No. CPC-060-301 l
Page 12 of 2a i
i
+
I Table 2 l
l TABLE 3.4 J
%!SB 3Ltml131 STRESS D'u.1:ATION Cr reae-t C e ses C ALCL*LA'~~D V Al'.T K5f' t
cr.xo ows 5'.*4C PRZ.1lst1LK "HDL%A!.
HANCLNG
"'"~ A.:.
.?.t--
P.
0.1 -
0.1 N/A 0.9 1.1 00J MSB Shed P, + P, 0.1 12 N/A
- .4 3.i 303 P+Q 0.1 1.2 1.0 2.4 43 6;J Bottom P.
0.02 0A5 N/A 1.0 1.1 20J j
Place P + P.
a02 1.7 N/A 1.5 3.2 30J 6I,C
- i"
.7
- 7, *
".J Top Lid P.
0.0 0.0 N/A 0.1 0.1 P + P.
0.0 0.4 N/A 00 0.6 303 6P+Q Q.0 0.4 02 0.2 03 61.5 Bottom to-P.
0.1 00 N/A 0.9 10 00J l
Shell P + P.
0.1 1.7 N/A 1.5 3.3 30J i
6 funcnon P+Q 0.1 1.7 1.5 1.5 42 61J
.tp-to.shnu P.
0.0 0.06 N/A 0.2 0.3 -
15.4
. unction P + P.
0.0 E4 N/A 0.2 0.6 23.1 6P+Q 0.0 0.4 0.4 02 1.0 4&1 Sleeve P.
- 0.05 N/A N/A 1.8 1.9 20J Anembly P + P.
Q.05 -
N/A N/A 2.1 2.2 303 6P+Q 0.05 N/A 52.0 2.1 54.2 61.5 Shield Ud.
P.
03 0.2 N/A 0.3 0.8 15.4 to-Shell P + P.
a3 QA N/A E4 1.5
- 3.1 6
Wald P+Q 43 QA 1.3 0.4 2.5 46.1 Sliiald Ud P.
a4 N/A N/A 03 03 15.4 Support P + P, a4 N/A N/A Q3 0.7 23.1 6
Ring Weld P + Q".
a4 N/A 0.0 03 0.7 46.1 Values shown are maximums imspee:rve of location Revision l
0 l
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Preparer /Date ljjj ;:/;i '<:-l j
l Checker /Date Q l
l File No. CPC.060 301 Pace :3 of 21 I
1 L___________._________.______.._
l Table 3 Projected Charpy Data and Allowable Flaw Sizes Charpy Charpy Charpy @
Allowable Plar.!
Idenufier Percent
@ -50'F
@ O'F O'F KID Depth Shear Average Predicted Actual
@ O'F (360')
(or Min)
(If Surface Available)
WP 18P4(IS-8)
NA 28 55.4 NA 89.6 0.14 Weld Point Beach Base 18-S NA 41 68 4 NA 99.6 0.17 Haz 18-8 NA 87 114.4 NA 128.8 0.22 Weld Zone Min 40 17 44 4 NA 80.2 0.13 ANO PQR AS-030 Weld Zone Ave 58 55 82.4 NA 109.3 0.17 HAZ Avc 70 l
80 107.4 ~
NA 124.8 0.20 Base Lone Ave 13,,,,_j _
33 60.4 NA 93.6 0.14 I
I i
Weldstar 467H Av I
NA 84 l 111.4 l
NA 127.1 0.20 Min Spec 467H NA I
20 47.4 l
NA I 82.9 0.13 40 60 87.4 1
!!7 I !!2.6 0.17 1
ESAB 41323 ANO ESAB 37962 l
27 55 82 4 96 l 109.3 0.17 ESAB 2A505A02 1
50 94 121.4 NA i 132.7 0.22 ESAB 2H408A03 43 96 123.4 NA 133.8 0.22 ESAB 2E426G02 63 103 130.4 NA 137.5 0.22 ESAB 2K407H03 70 122 149.4 NA 147.2 0.25 Allov Rods 32039 20 56 83.4 91 110.0 0.17 Palisades ESAB 38380 56 99 126.4 135 i
135.4 0.22 ES AB 51122 60 82 109.4 115 125.9 0.20 Min Specified NA NA 15 42.4 NA 78.4 0.13 Note: For subsurface defects at weld mid wall depth, the allowable through-wall dimension of the defect is generally twice the allowable surface flaw dimension for the corresponding case.
I Revision 0
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.l l
Checker /Date
.'7
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File No. CPC-060 301 i
Page 14 of 24
\\
d 4
t I
I.
i Table 4 l
Projected Charpy Data and Allowable Flaw Sizes l
Charpy Charpy Charpy @
Allowable l
Plant Idenufier Percent
@ 50*F
@ O'F O'F KID Depth l
Shear Average Predicted Actual
@ 0*F (360')
(or Min)
(If Subsurface Available)
WP-18P4(18-8)
NA 28 55.4 NA 89.6 0.32 Weld Point Beach Base 18-8 NA 41 68.4 NA 99.6 0.38 Haz 18-8 NA 87 114.4 NA 128.8 0 48 I
i Weld Zone Min 40 17 44.4 NA 80.2 0.28 l
ANO PQR AS-030 Weld Zone Avg 58 55 82.4 NA 109.3 0.38 l
HAZ Avg 70 80 107.4
.NA 124.8 0.44 l
Base Lone Avg 13 33 60.4 NA 93.6 0.32 Weldstar 467H Av NA 84 111.4 NA 127.1 0.44
{
l Min Spec 467H NA 20 47.4 NA 82.9 0.28 ESAB 41323 40 60 87.4 117 112.6 0.38
)
(
ANO ESAB 37962 27 55 82.4 96 109.3 0.38 ESAB 2A505A02 50 94 121.4 NA 132.7 0.48 l
ESAB 2H408A03 43 96 123.4 NA 133.8 0.48 ESAB 2E426G02 63 103 130.4 NA 137.5 0.48 ESAB 2K407H03 70 122 149.4 NA 147.2 0.52 Allov Rods 32039 20 56 83.4 91 110.0 0.38 Palisades ESAB 38380 56 99 126.4 135 135.4 0.48 ESAB 51122 60 82 109.4 -
115 125.9 0.44 Min Specified NA NA 15 42.4 NA 78.4 0.28 l
Note: For subsurface defects at weld mid wall depth, the allowable through-wall dimension of the defect is generally twice the allowable surface flaw dimension for the corresponding case.
1 l
i Revision l
0 l
Preparer /Date j) A p!2 Thy l
l Checker /Date g;'..;f.);j l
File No. CPC-060-301 l
Pace 15 of N l
l
I a
i,
,..,v.,,
, - t'/ -i /'e s/g J 5 '
~
t t_
3/32. MAX CAP HEIGHT l
AS NEASERE3 F LOM MIGHE57 v.
I (LID CA M55 3MELL).
MBE I
--- w h
l 45' NCR.
'R' l
3 l
l I
ms ssc:,
i f
acz:s :s 1
i Figure 1 l
Revision l
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,,l l
l l
I File No. CPC.060-301 l
Pace 16 of 24 l
l
220 m
iso
/
iso l
Li k
- eso u
a l
"u
.. iso
[
{ 100 1,
8
,o gy ::.75 ks t 77n s;
60 so 3r.
- TNDr o
.s.
or - a r,o p.
- FIG. A 42001 LOWER BOUND K. AND K.VS TEMPERATURE CURVES FROM TESTS OF SA 533 GRADE B CLASS 1. 5A 508 CLASS 2, AND SA 508 CLAS$ 3 STEELS Figure 2 i
l Revision 1
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l PreparenDate j fjg,# lj7 9_ j l
l 9
l CheckenDate
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.. !.- l l
l i File No. CPC-060-301 I
Pace 17 of 21 l
l l
l l
_______.____._____m
l a = 0, - C.x
. C. '
i 1
x i
4 i
I l
l I
~I A
A l
\\J t-
- 1 1
N-t
/.I I
~~
r-
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a i
See-ion A-A
.I c = Ce + C (t/s)(membrane stress) i
= -C (i\\:) (been st:e:s) c3 i
c, - c + as Ci = -2sd\\t i
6 l
,I 9 1 r!
RIQUIRED DiPUTS:
t:
wa!! thicizers a:
esci depth (1.nz ! 0.5t) material yield stress
- 1. c c-.c.c s.sper. :st10 Ep: :-!:
".I7M C:::2 M: del A. Pyt 2 - I'lipt:::1 Sc:6:e C:sd ?!::e ut.de:
- 'e=:::=e n.: Se:i:z i::212ei
- - =
Figure 3 l
Revision 0
l l
Preparer /Date j jjj,;/2 s! - l l
l Checker /Date pp/,,+
/,, - l l
l l
l i File No. CPC-060-301 i
Page IS of 4 l
I ALLOWABLE FLAW SIZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7 0.7 OF 15 FT-LB @ -50 DEG, EXTRAPOLATED TO O DEG c,c 06 Eg 0.5 0.5 g
FURTHER EVALUATION REQUIRED
'g 0.4 0.4 h 0.3 0.3 0.2 0.2 0.1 0.1 ALLOWABLE FLAW 0
1 2
4 i
10 FLAW LENGTH, IN.
& GREATER i
Figure 4a l
Revision l
0 l
l l
Preparer /Date l jjQ,, /g's y-j Checker /Date py.
l File No. CPC-060-301 p2ce ;9 or 3 l
A _LOWAB _E F _AW SIZ E FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7
^7 FROM pal..lRADFS DATA AT.sn DFG F'tTRAPol. ATPn TO n npr.,
I I
l 0.6 0.6 2
__- 0.5 FURTHER EVALUATION REQUIRED 0.5 n.tu 0.4 0,4 O
{
(
1.3 0.3 i
y
_u.
0.2 0.2
~
0.17 0.1 ALLOWABLE FLAW
- 0.1 O
O i
0 1
2 3
4 5
6 7
8 9
10 i
FLAW LENGTH, IN.
i
& GREATER i
Figure 4b Revision l
0 l
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l Preprer/Date lJJg n/>5!%
l l
Checker /Date p/'j';. /.,./.. ;
l l
File No. CPC-060-301 I
Pa;e 20 of 24
l I
I i
ALLOWAB _E FLAW SIZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUM MATERIAL TOUGHNESS 0.8 0.7
^'
FROM POINT BEACH DATA AT-50 DEG, EXTRAPOLATED TO 0 DEG 0.6 0.6
-d l
g 0.5 0.5 l
g FURTHER EVALUATION REQUIRED w 0.4 0.4 l
C k 0.3 0.3 L
(
0.14 l
0.1 0.1 ALLOWABLE FLAW 0
.0 0
1 2
3 4
5 6
7 8
9 10 FLAW LENGTH, IN.
& GREATER Figure 4c l
i i
Revision 0
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)
l File No. CPC-06Q-301 i
Page 21 of 22 l
i
1 l
ALLOWABL.E FLAW S.ZE FLAW DEPTH VERSUS LENGTH 0.8 BASED ON MINIMUIA MATERIAL TOUGHNESS 0.8 FROM ANO DATA AT-50 DEG, EXTRAPOLATED TO O DEG 0.6 g 0.5 0.5 g
FURTHER EVALUATION REQUIRED w 0.4 O
0.4 b 0.3 0.3 0.2 0.2 0.13 0.1 0.1 ALLOWABLE FLAW 0
0 0
1 2
3 4
5 6
7 8
9 10 FLAW LENGTH, IN.
& GREATER l
Figure 4d
{ Revision 0
l Preparer /Date lf) Mj/75/?:-l l
l l Checker /DateQ'y' /.,-/,,- l l
l
' File No. CPC-060-301 1
Page 22 of 2 t
a l
i
..a Tesung temperature. *F
-13
- 50 0
50 100 150 30 150 I
100 1.55% Mn
[
g [_----
--- 1.01% Mn l
l[
l p,6,.**' l
~
I
//
l/
0.39% Mn
/
,L.
g j
/p
), _........* 0.30% Mn
- y
/
i
/
/
=
l/
/
s e
R ?
e e 75 i
I
/
1 l j/
l 2s
/
r e5 f
/ /
/
/
f
/
,/
?.
- x
/
/
//,s
/
0 0
-le
- 75
- 5D
-3 0
3 5D 75 le Testing temperature *C E
Won in Nrpy V notch impac energy with temperature for 0.30% C steels containing varying Y jg amounts of manganese. The specimens were austenitized at 900 *C (1650 *F) and cooled at ipprommately 14 *C/ min (25 *F/ min).The microstructure of these steels were pearistic. Source: Ref 6 Ficure 5
)
Revision 0
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l
- l Che ker/Date /yg.
.lg l
l i File No. CPC-060 301 l
pace 23 of 24
I e :o A
A 4
l I
b I
i a I f
i T
1 REQUIRED DiPUTS:
b: platewidth a: crack depth (a.u i 0.9b)
Fip:re 3-20.
LEFM Cr2:k Mode! C, Pye 2 - Ce:::er Crzer Plate ::: der Remote Tension Stress Figure 6 Revision 0
l l
l Preparer /Date l % n j-s l
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Checker /Date I. f.',
.. - l l
l i, e i File No. CPC-060-301 Page 24 of 24 1
{
i 4.PPENOD' a pc CRACK Output i
l l
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_..__..__._._s
1 l
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- 1 tm pc-CRACK for Windows Version 3.0, Mar. 27, 1997 (C; C:pyr_ght '54 - 'c7 Structural Integrity Associates, Inc.
j 3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557
)
Voice:
406-975-8200 Fax:
406-978-8964 E-mail: info @structint.com i
i Linear Elastic Tracture Mechanics g
Date: Thu Nov 20 10:56:27 1997 File: 55.LFM
Title:
CPC-06Q:' LIMITING ZERO DEGREE FLAWS L
Load Cases:
rese: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 L
0.3750 7.2000 O.7500
-28.9000 Stress Coefficients CaseEID-CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0.
Coeff DROP 2' 43.3001
-96.2668 0
0 StressDist Crack Model: Single Edge-Cracked Plate s
Crack Parameters:
t-Plate width:
0.7500 l
. Max.. crack size:
0.3750
Stress Intensity Tacter--------------------
Crack =
Case-Case Case Size RESIDUAL MEMSRANE DROP 2 q
i l
t t
9
l 0.0075 4.98488 1.19637 7.12042 1
0.0150 7.09853 1.70365 10.034 0.0225 8.75371 2 10089 12.2441 0.0300 10.177 2.4424E 14.0649 0.0375 11.4554 2.74931 15.6861 0.0450.
12.6334 3.03202 17.1144 l
0.0525 13.737 3.29688 18.4094 l
0.0600' 14.7832 3.54796 19.5969 i
0.0675 15.7835 3.78805 20.695 0.0750 16.7465 4.01917 21.7166 0.0825 17.9075 4.29781 22.9894 l
0.0900 19.0627 4.57506 24.2291 O.0975 20.2147 4.85153 25.4397 l
-0.1050 21.3655 5.12771 26.6243 0.1125
- 22.5167 5.404-27.7854 0.1200 23.6695 5.68069 28,9252 j
0.1275 24.8252 5.95805-30.0451 L
'O.1350 25.9845 6.23629 31.1465 0.1425 27.1482
.6.51557 32.2305 v.isuu 2e.31te o.isbu4 JJ.2se-0.1575 29.7019 7.12847 34.5864 0.1650 31.1029 7.46469 35.8642 0.1725 32.5197 7.80472 37.1309 l.
0.1800 33.9523 8.14855 38.3864 l
0.1875 35.4007 8.49617 39.63 0.1950 36.8649' 8.84758 40.8616 0.2025 38.3448 9.20276 42.0805 j
0.2100 39.8404 9.56169 43.2863 l
0.2175 41.3515 9.92437 44.4787 l
0.2250 42.8782-10.2908 45.0571 l
0.2325 44.8048 10.7532 47.2543 l
O.2400 46.7591 11.2222 48.8424 0.2475 48.7407 11.6978 50.4204 l
0.2550 50.7491 12.1798 51.9869 0.2625 52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775 56.9322 13.6637 56.607 0.2850 59.0448 14.1708
.58.117 0.2925 61.1827 14.6838 59.6102 0.3000 63.3455 15.2029 61.0856 1
0.3075 66.4177 15.9402 63.5413 i
'O.3150 69.5356 16.6886 65.9877 I
0.3225 72.6988-17.4477-68.423 0.3300 75.9066 18.2176 70.8454 6
0.3375 79.1584 18.998 73.2532 I
O.3450 82.4536
,19.7889 75.6445 1
0.3525 85.7917 20.59 78.0178 l
L
- 0,3600 89.1722 21.4013 80.3714 J
0.3675 92.5944 22.2227 82.7036 0.3750-96.0581 23.0539 85.0129 i
A3
~
c
l t
I Material fracture toughness:
erial ID: A516 55 Depth K1c 0.0000 55.4000 0.3750 55.4000 0.7500 55.4000 Load combination for critical crack size:
Load Case Scale Factor RESIDUAL 1.0000 DROP 2 1.0000 1
Crack Tota]-
Size K
Kic i
0.0075 12.1053 55.4 0.015 17.1326 55.4 0.0225 20.9976 55.4 0.03 24.2618 55.4 0.0375 27.1415 55.4 0.045 29.7478 55.4 I
0.0525 32.1464 55.4 0.06 34.3801 55.4 0.0675 36.4785 55.4 0.075 38.4631 55.4 0.0825 40.897 55.4 -
0.09 43.2918 55.4 0.0975 45.6544 55.4 0.105 47.9897 55.4 0.1125 50.3021 55.4 0.12 52.5947 55.4 0.1275 54.8703 55.4 0.135 57.131 55.4 0.1425 59.3787 55.4 0.15 61.6148 55.4 0.1575 64.2884 55.4 0.165 66.9671 55.4 0.1725 69.6506 55.4 0.18 72.3386 55.4
'O.1875 75.0308 55.4 0.195 77.7265 55.4 0.2025 80.4253 55.4 0.21 83.1267 55.4 i
t
}
o
)
o 0.2175 85.8302 55.4 0.225 88.5352 55.4 0.2325 92.2591 55.4 0.24 95.6;*5 55.4 O.2475 99.161 55.4 0.255 102.736 55.4 0.2625-106.325 55.4 i
0.27 109.926 55.4 0.2775 113.539 55.4 0.285 117.162 55.4 l
0.2925 120.793 55.4 0.3 124.431 55.4 j
0.3075 129.959 55.4 0.315 135.523 55.4 0.3225 141.122 55.4 0.33 146.752 55.4 0.3375 152.412 55.4 0.345 158.098 55.4 0.3525 163.81 55.4 0.36 169.544 55.4 0.3675 175.298 55.4 0.375 181.071 55.4 Critical crack size =
0.1292 1
~~
1 As~
l
__ ____ __________ -_-__ a
e i
tm pc-CRACK for Windows Version 3.0, Mar. 27, 1997 (C) Copyright '84 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info 0structint.com Linear Elastic Fracture Mechanics Date: Thu Nov 20 10:58:23 1997 File: 60.LEN
Title:
CPC-060: LIMITING ZERO DEGREE FLAWS Load Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients
.. se ID CD C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE
'I. 2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist j
1 Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 j
Max. crack size:
0.3750
^
i
Stress Intensity Factor--------------------
Crack Case Case Case Size RESIDUAL MEMBPANE DROP 2 l
AG
l 0.0075 4.98488 1.19637 7.12042 0.0150 7.09853 1.70365 10.034 0.0225 8.75371 2.10089 12.2441 0.0300 10.177 2.44248 14.0849 1
0.0375 11.4554 2.74931 15.6861 0.0450 12.6334 3.03202 17.1144 0.0525 13.737 3.29688 18.4094 0.0600 14.7832 3.54796 19.5969 0.0675 15.7835 3.78805 20.695 0.0750 16.7465 4.01917 21.7166
'O.0825 17.9075 4.29781 22.9894 0.0900 19.0627 t.57506 24.2291 0.0975 20.2147 4.85153 25.4397 0.1050 21.3655 5.12771 26.6243 0.1125 22.5167 5.404 27.7854 0.1200 23.6695 5.68069 28.9252 0.1275 24.8252 5.95805 30.0451 0.1350 25.9845 6.23629 31.1465 0.1425 27.1482 6.51557 32.2305 0.1;;;
20.3100 0.7;;;4
- .130
)
0.1575 29.7019 7.12847 34.5864 i
0.1650 31.1029 7.46469 35.8642 0.1725 32.5197 7.80472 37.1309 0.1800 33.9523 8.14855 38.3864 0.1375 35.4007 8.49617 39.63 0.1950 36.8649 8.84758 40.8616 0.2025 38.3448 9.20276 42.0805 0.2100 39.8404 9.56169 43.2863 0.2175 41.3515 9.92437 44.4787
~
0.2250 42.8782 10.2908 45.6571 0.2325 44.8048 10.7532 47.2543 0.2400 46.7591 11.2222 48.8424 0.2475 48.7407 11.6978 50.4204 0.2550 50.7491 12.1798 51.9869 0.2625 52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775 56.9322 13.6637 56.607 0.2850 59.0448 14.1708 58.117 0.2925 61.1827 14.6838 59.6102 0.3000 63.3455 15.2029 61.0856 0.3075 66.4177 15.9402 63.5413 0.3150 69.5356 16.6886 65.9877 0.3225 72.6988 17.4477 68.423
-0.3300 75.9066 18.2176 70.8454 0.3375 79.1584 18.998 73.2532 0.3450 82.4536 19.7889 75.6445 0.3525 85.7917 20.59 78.0178 0.3600 89.1722 21.4013 80.3714 0.3675 92.5944 22.2227 82.7C36 0.3750 96.0581 23.0539 85.0129 l
l "sterial fracture toughness:
..terial ID: A516_60 Depth K1c O.0000 60.0000 0.3750 60.0000 0.7500 60.0000 Load combination for critical crack size:
J Load Case Scale Factor RESIDUAL 1.0000 DROP 2 1.0000 2.u.k
- . 1 Size E
Kic 0.0075 12.1053 60-0.015 17.1326 60 0.0225 20.9978 60 0.03 24.2618 60 0.0375 27.1415 60 0.045 29.7478 60 0.0525 32.1464 60 0.06 34.3801 60 0.0675 36.4785 60 0.075 38.4631 60 0.0825 40.897 60 0.09 43.2918 60 0.0975 45.6544 60
-0.105 47.9897 60 0.1125 50.3021 60 0.12 52.5947 60 0.1275 54.8703 60 0.135 57.131 60 0.1425 59.3787 60 0.15 61.6148 60 0.1575 64.2884 60 0.165 66.9671 60 0.1725 69.6506 60 0.18 72.3386 60 0.1875 75.0308 60 0.195 77.7265 60 0.2025 80.4253 60 0.21' 83.1267 60 l
l n C' i
__-_____________--___._.__--O
=
l C.2175 85.8302 60 0.225 88.5352 60 0.2325 92.0591 60 0.24
'95.6015 60 0.2475 99.161 60 0.255 102.736 60 0.2625 106.325 60 0.27 109.926 60 0.2775 113.539 60 0.285 117.162 60 0.2925 120.793 60 0.3 124.431 60 0.3075 129.959 60 0.315 135.523 60 0.3225 141.122 60 0.33 146.752 60 0.3375 152.412 60 0.345 158.098 60 0.3525 163.81 60 v.se Aoy.s*4 ou 0.3675 175.298 60 0.375 181.071 60 Critical crack size =
0.1446 i
I
.7._..
1 i
tm pc-CRACK for Windows version 3.0, Mar. 27, 1997 (C) Copyright '84 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info 8strucrint.com Linear Elastic Fracture Mechanics
)
Date: Thu Nov 20 10:59:25 1997 File. : 70.LD!
Title:
CPC-060: LIMITING ZERO DEGREE FLAWS Load Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients wase ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist i
Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Mzx. crack size:
0.3750
Stress Intensity Factor--------------------
Crack Case Case Case Size RESIDUAL MEMBRANE DROP 2 fb
,e 0.0075 4.98488 1.19637 7.12042 0.0150 7.09853 1.70365 10.034 0.0225 8.75371 2.10089 12.2441 0.0300 10.177 2.44248 14.0849 0.0375 11.4554 2.74931 15.6861 0.0450 12.6334 3.03202 17.1144
[
0.0525 13.737 3.29688 18.4094 O.0600 14.7832 3.54796 19.5969 0.0675 15.7835 3.78805 20.695 0.0750 16.7465 4.01917
-21.7166 0.0825
-17.9075 4.29781
'22.9894 0.0900 19.0627 4.57506 24.2291 l
0.0975 20.2147 4.85153 25.4397 0.1050 21'.3655 5.12771 26.6243 0.1125 22.5167 5.404 27.7854 0.1200 23.6695 5.68069 28.9252 0.1275 24.8252 5.95805 30.0451 0.1350 25.9845 6.23629 31.1465 0.1425 27.1482 6.51557 32.2305 6 lann-7o 32co-c 7osna is 9en 0.1575 29.7019 7.12847 34.5864 0.1650 31.1029 7.46469 35.8642 0.1725 32.5197 7.80472 37.1309 0.1800 33.9523 8.14855 38.3864 0.1875 35.4007 8.49617 39.63 0.1950
-36.8649 8.84758 40.8616 0.202.5 38.3448 9.20276 42.0005 0.2100 39.8404 9.56169 43.2863 0.2175 41.3515' 9.92437 44.4787 0.2250 42.8782
-10.2908 45.6571 0.2325 44.8048' 10.7532 47.2543 i
0.2400 46.7591 11.2222-48.8424 0.2475 48.7407 11.6978 50.4204 0.2550 50.7491 12.1798 51.9869 0.2625 52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775 56.9322 13.6637 56.607 j
0.~2850 59.0448 14.1708=
58.117 i
0.2925 61.1827 14.6838 59.6102 0.3000 63.3455-15.2029 61.0856 0.3075 66.4177 15.9402, 63.5413 0.3150.
69.5356-16.6886 65.9877 0.3225 72.6988 17.4477 68.423 0.3300 75.9066 18.2176
-70.8454 0.3375 79.1584 18.998.
73.2532 0.3450 82.4536 19.7889 75.6445 0.3525 85.7917 20.59, 78.0178 0.3600 89.1722 21.4013 80.3714
.0.3675 92.5944 22.2227 82.7036
-0.3750 96.0521-23.0539 85.0129 l
l-
l '
s....,
1 i
r aMateria1' fracture toughness:
.dterial'ID: A516_70 Depth Kic 0.0000 70.0000-0.3750'
-70.0000' O.7500-70.0000-
' Load combination for critical crack size:
. Load' Case Scale Factor RESIDUAL 1.0000 DROP 2
-1.0000 J..k Twi.i Size K
- K1c 0.0075 12.1053
- 70-0.015 17.1326 70 0.0225' 20.9978
'70 0.03 24.2618 70.
0.0375 27.1415' 70
'O.045 29.7478 70 t
0.0525 32.1464 70-
-0.06 34.3801 70 0.0675-36.4785 70-0.075' 38.4631 70
~
0.0825 40.897 70 0.09 43.2918, 70 0;0975 45.6544 70
-0.105 47.9897 70 0.1125~
50.3021' 70 0.12 52.5947 70-1 1275 54.8703' 70-0 0.135 57.131 70 0;1425 59.3787 70 0.15 61=. 614 8 70 1
0.1575 64.2884 70 0.165 66.9671
. 70-0.1725 69.6506 70 0.18 72.3386 70 O.1875-75.0308 70 0.195 77.7265
-70
-0.2025
~80.4253-70
.0.21 83.1267 70 l-I l
a
__m_____
l
'4 r
l l
0.174 62.585 90 l
0.18 64.3934 90 0.186 66.2586 90 0.192 68.1871 90 0.198 70.186 90 0.204 72.2631 90 l
0.21 74.4272 90 0.216 76.6879 90 0.222 79.056 90 0.228 81.5437 90 0.234 84.1649 90 0.24 86.9355 90 0.246 89.8738 90 0.252 93.0009 90 0.258 96.3416 90 0.264 99.9252 90 0.27 103.787 90 1
0.276 107.968 90 O.282 112.519 90 n van 1,7,gne on 0.294 123.001 90 0.3 129.109 90-l l
Critical crack site =
0.2463 l
l l
l I
l 4
tu pc-CRACK fer Windows version 3.0, Mar. 27, 1997 (C) Copyright '84 - '97 I
Structural Integ: ty Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-nail: info @structant.com Linear Elastic Fracture Mechanics i
Date: Mon Nov 24 12:18:54 1997 File: CCP100.LEM
Title:
CPC-060: SUBSURFACE DEFECT, KID =100 Load Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 l
Stress Coefficients wase ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3000 1
Stress Intensity Factor--------------------
Crack Case Case Case Sire RESIDUAL MEMBRANE DROP 2 l
l l
l l
A41 l
4 0.0060 4.11943 0.988664 5.94573 0.0120 5.82841 1.39882 8.41235 0.0180 7.14374 1.7145 10.3108 0.0240 8.25766 1.98;84 11.9186 0.0300 9.24501 2.2?.88 13.3437 0.0360 10.1444 2.43466 14.6418 0.0420 10.9791 2.63498 15.8465 0.0480 11.7643 2.82342 16.9798 0.0540 12.5107 3.00257 18.0572 0.0600 13.2264 3.17434 19.0902 0.0660 13.9176 3.34022 20.0877 0.0720 14.589 3.50137 21.0569 0.0780 15.2449 3.65878 22.0035 0.0840 15.8886 3.81326 22.9326 0.0900 16.523 3.96552 23.8482 0.0960 17.1508 4.11618 24.7543 0.1020 17.7742 4.2658 25.6541 0.1080 18.3954 4.41489 26.5507 0.1140 19.0164 4.56392 27.447 0.1200 19.A39 e,71'1s
?a 14;7 0.1260 20.2651 4.86363 29.2494 0.1320 20.8965 5.01516 30.1607 0.1380 21.5349 5.16837 31.0821 0.1440 22.182 5.32369 32.0161 0.1500 22.8398 5.48154 32.9655 0.1560 23.5099 5.64238 33.9327 0.1620 24.1944 5.80665 34.9206 0.1680 24.8952 5.97486 35.9322 0.1740 25.6146 6.1475 36.9705 0.1800 26.3547 6.32513 38.0387 0.1860 27.1181 6.50834 39.3405 0.1920 27.9074 6.69777 40.2797 0.1980 28.7255 6.89411 41.4605 0.2040 29.5756 7.09814 42.6875 0.2100 30.4613 7.31071 43.9659 0.2160 31.3866 7.53277 45.3013 0.2220 32.3558 7.76538 46.7002 0.2280 33.3739 8.00974 48.1698 0.2340 34.4467 8.26722 49.7182 0.2400 35.5807 8.53936 51.3549 0.2460 36.7832 8.82798 53.0906 0.2520 38.0631 9.13514 54.9378 0.2580 39.4304 9.46328 56.9112 0.2640 40.897 9.81529 59.0282 0.2700 42.4774 10.1946 61.3092 0.2760 44.1886 10.6053 63.7789 0.2820 46.0514 11.0523 66.4677 0.2880 48.0916 11.542 69.4124 0.2940 50.3414 12.0819 72.6595 0.3000 52.8414 12.6819 76.2679 J
~
AG
(
l Material fracture toughness:
.ateria' ID: a516-100 Depth Kic 0.0000 100.0000 0.3750 100.0000 0.7500 100.0000 Load combination for critical crack size:
Load Case Scale Factor l
RESIDUAL 1.0000 l
DROP 2 1.0000 Crack Tota 3 Size K
K1c 0.006 10.0652 100 0.012 14.2408 100 0.018 17.4545 100 0.024 20.1762 100 0.03 22.5887 100 0.036 24.7863 100 0.042 26.8256 100 0.048 28.7441 100 0.054 30.5679 100
~
0.06 32.3166 100 0.066 34.0053 100 0.072 35.6459 100 0.078
'37.2484 100 0.084 38.8211 100 0.09 40.3712 100 0.096 41.905 100 0.102 43.4283 100 0.108 44.9461 100 0.114 46.4633 100 0.12 47.9847 100 0.126 49.5145 100 0.132 51.0572 100 0.138 52.617 100 0.144 54.1982 100 0.15-55.8052 100 0.156 57.4426 100 0.162' 59.115 100
.0.168 60.8274 100 l
i i
l l
l
) *. C I
1
l l
2 1
0.174 62.585 100 0.18 64.3934 100 0.186 66.2586 100 0.192 68.1871 100 i
l 0.198 70.186 100 l
0.204 72.2631 100
{
0.21 74.4272 100 O.216 76.6879 100 0.222 79.056 100 i
0.228 81.5437 100 0.234 84.1649 100 0.24 86.9355 100
)
0.246 89.8738 100 0.252 93.0009 100 0.258 96.3416 100 0.264 99.9252 100 0.27 103.787 100 0.276 107.968 100 0.282 112.519 100 0.288 117.504 100 0.294 123.001 100 0.3 129.109 100 Critical crack size =
0.2641 O
e m#
40b
l APPENDIX B Design input from Consumers Energy l
Revision 0
1 Preparer /Date pfgij/pg/9p
/g,,/ j. 3 j
~
Checker /Date File No. CPC-06Q-301 l
Page BI of G tl l
l l
Panaces kxer pam m,,,,com m 27780 Bw Star Memonat netwar covert. MI 49043 November 12,1997 Mr. Hal Gustin Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118 1557
SUBJECT:
Flaw Analysis inputs Daar Hal:
This letter transmits design inputs for use in the flaw analysis being provided under purchase order C0025456. The specific design inputs shown below are enclosed.
Safety Analysis Report for the Ventilated Storage System, PSN 91-001, Rev O, dated October 1991, Table 11.21, Summary of Stresses (ksil in the MSB Resulting from the Hypothetical Herizontal Drop. The limiting event for the structural lid weld is the j
horizontal drop accident, which is considered to be an emergency / faulted event.
{
Safety Analysis Report for the Ventilated Storage System, PSN-91-001, Rev 0, dated October 1991, Table 3.4-5, MSB Maximum Stress Evaluation.
Certificate of Compliance ( C of C) for Dry Spent Fuel Storage Casks (No.1007),
effective May 7,1993, Section 1.2.13, Minimum Temperature for Moving the MSB.
Certificate of Compliance ( C of C) for Dry Spent Fuel Storage Casks (No.1007),
effective May 7,1993, Section 1.2.14, Minimum Temperature for Lifting the MTC.
Certified Material Test Reports (Lot No. 32039 and 38380) for the weld material used on the structural lid welds in MSB's 1 13 are enclosed. The CMTR (Lot No. 51122) for the weld material to be used on iuture structurallid welds is also enclosed. The cask structural lid welds will remain in the as welded condition following welding.
Please give me a callif you have any questions.
Sincerely, Emil A.
ernick g
Engineering Lead Dry Fuel Storage O
RECEIVED NOV 141997 STRUCTURAL INTEGRITY
o e
T.GLE 3.4 5
>!SB SIAXI5tC51 STRESS EVALUATION Cc--enent Stresses CALCl*LMD VAltJE K51' DEAD gyg STJOHT PPI33'JRE TFRMAL.
KAN0llNO TCCAL
- .N -
P.
0.1 0.1 N/A 0.9 1.1
- 0.5 SiSB Shell P + P, 0.1 1.2 N/A 2.4 3.7
.t0.7 tP+Q 0.1 1.2 1.0 2.4 4.7 61.5 i
Bottom P.
0.02 0.06 N/A 1.0 1.1 20.5
.P: ate P + P, 0.02 1.7 N/A 1.5 3.2 30.7 t
P+Q u.u4 4.i 13..;
1.;
aa '
1 Top Lid P.
0.0 0.0 N/A 0.1 0.1 20.5 P + P, 0.0 0.4 N/A 0.2 0.6 30.7 tP+0 0.0 0.4 0.2 0.2 0.8 61.5 Bottom.to-P.
0.1 0.2 N/A 0.9 1.2 20.5 Shell P + P, 0.1 1.7 N/A 1.5 33 30.7 t
^'iction P+Q 0.1 1.7 1.5 1.5 4.8 61.5
' ap.to.shell P.
0.0 0.06 N/A 0.2 03 15.4
. unction P + P, 0.0 0.4 N/A 0.2 0.6 23.1 tP+Q 0.0 0.4 0.4 0.2 1.0 46.1 Sleeve P.
0.05 N/A N/A 1.8 1.9 20.5 Assembly P + P, 0.05 N/A N/A 2.1 2.2 30.7 l
tP+Q 0.05 N/A 52.0 2.1 54.2 61.5 Shield Ud-P.
03 0.2 N/A 03 0.8 15.4 to Shell P + P, 03 0.8 N/A 0.4 1.5 23.1 6
Weld P+Q 03 0.8 13 0.4 2.8 46.1 Shield Ud P.
.0.4 N/A N/A 03 0.7 15.4 Support Pc + P, 0.4 N/A N/A 03 0.7 23.1 Ring Weld P+Q-0.4 N/A 0.0 03 0.7 46.1
)
Values shown are maximums irrespectne of location s
.e 1
e l
iib t
t 5
05
- o. 5
- 0. 5
- n. 5 l
t.
I.
a I
t Mw i
93 9 3 91 9 3 93 65 5
r S o l
4 7 4 7 47 4 7 4 7 3 5 35 Al A
l 63 4 6 I. 3 23
- 3. I 3
4 a
53 00 t
0 66 7
9 3
o 96 63 2
2 T
24 27 4
2 24 4
2 M
OR F
e G
r 6
4 u
6 1
7 1 2 04 00 27 0 4 28 1 F s
f e
oI 0I 00 C0 0 f 0(
( (
TO r
L R P
l MO m
A A
A A
A A
AA r
/
/
/
/
/
/
//
Z EI e
N N
N N
N N
NN I
R h
I 2
T DO I
I I
l NI E
L I
L iA
)
B sC A
k t
I T
(T W
A A
A A
A A
/
/
/
/
/
/
//
El d
N N
N N
N N
NN a
SiST e
EO D
I a
F E o
OI l
p 46
- 9. A
- 6. 9
- 4. 6
- 9. 6 1 9 8
6 1
L p
o r
94 51 2
2 i 54 7
9 0 o
Y1 2
2 I
24 4
2 R
D 24 27 4
r d
A e
M h
t M
n U
i S
d e
P P.
P P
P P
P d
7' u
P. +
P+
P+
P+
P+
P+
P+
l i
i.
i c
n P
P P
P P
P P.
i s
i t
h l
t d
ig e
e ke U
w a
t t
n a
r n
P u
k W
l i
t e
k d
L e
a t
op e
c n
W d
n eD i
u k
o l t m
o t
l e
p ek l
t e
e rd t
i o
t i
t h
o o
hW o
h B
S SU S
B T
C S
Wl. o gh G c.
l
1.2.13 Minimum Temperature for Moving the uSB Limit / Specification:
Movement of the MSB inside the VCC wtil only De alic ec ;;
ambient temperatures of O' F or above.
Objective:
To avoid the potential for brittle failure.
Action:
Confirm that the ambient temperature is above 0 F immediately 8
before moving the MSB, while inside the VCC.
Svi..;l;..6.:
Tii.
uivisi iv. g...iu. 4 ei..*i U.
nured before movement or the MSB.
Basis:
Each MSB shell material will have shown, during fabrication, by Charpy test (per ASTM A370) that it has 15 ft-lb of absorbed energy at -50' F; and, therefore, movement of the MSB 8
at temperatures above 0 F will avoid the potential for brittle fracture.
Calculations show that the MSB shell ainimum temperature will be substantially above the ambient 8
temperature (e.g., 20 F for 25-year-old fuel). However, for conservatism and simplicity, it is recommended that the ambient be selected as the minimum MSB movement temperature.
It is highly unlikely that any MSB movement activity would take place at temperatures below zero.
Nevertheless, if movement at a temperature below that specified is necessary, calculations (similar to those presented in Chapter 4 of the SAR) any be used to estimate the minimum MSB shell temperature for any particular ambient condition.
A-28
[$5
I~
j
(
l l
l 1.2,14 Minimum Temperature for Lifting the MTC 1
Limit / Specification:
l The MTC shall be allowed to be used to move :ne MSS if ;,e ambient temperature is 40' F or above.
i Objective:
To avoid the potential for brittle failure.
l Action:
Confirm that the ambient temperature is above 40' F before moving the MS8 inside the MTC.
l L,. ;11.r.m n.: c: =ttet t=:= ten e.:11 5:
- ci=
- f:. :
movement of the MSB in the NTC.
Basis:
The MTC material will have shown, during fabrication, that it j
has 15 ft-lb of absorbed energy at o' F.
Having Charpy test results, at 0' F, which show ductility (or other appropriate l
test to show that the Nil Ductility Temperature is lower than 80 F), will avoid the potential for brittle failure when the
' ' ~
cask is moved at 40' F or higher. The MTC shell will have a temperature higher than antiient due to the heat source from the irradiated fuel.
- However, for conservatism and simplicity, it is recommended that the ambient temperature be used as the minimum shell temperature. If movement at lower temperatures is ever required, additional specific analysis or other actions that meet the approval of the NRC must be provided.
l A-29 hb
l
,,.a m asa ra n s a Coosastsi VELO rAn x0ctExx Sz:rrrno:TlerEr Ns1141t ?4.v.v.
.w,.w c:.
4 an-e ~.c., n n Alt 0Y R'0DS CORPORATION CERTIFICATE OF A'lALYSIS i
h P.O. BOX 517/1500 KAREN LANE Q,.
HANOVER, PA 17331 7-CERTIFIE[ N N TEST REPCRT i
't WELDSTAR COMPANY Customer Order No.: 2244A-A l
1730 MITCHElf ROAD order No.: 144017-1 l
AURORA. IL 60504 ;" ' -
his Material Conforms to Specification:
'Y r s.;&. 4. N.c#
ASME STA 5.20 SEC:II; FART C & ASME SEC III.SUBSEC
'f L M I-F-t M '#-
NB FCE CLASS;1 MATERIAL 1989 ED.
1990' ADD.' ASME Trade ired,. S STA 3.01,. CLASS;T2f;SCH. E.10 CTE PART'21 APPLIES J
' er.Trad=a rk s Dus1' Shield II 70 L%^-W ' T-
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1936 1996 i
Years PHONE (630) 859-3100 AURORA, IL 60507 1150 P.O. BOX 1150
+
+
CERTIFICATE OF COMPLIANCE ISSUED Au6ust22,1997 i
CUSTOMER: rmnners Energy l
CUSTOMER PO#: 00238240 SHIP TICKET #: N917295 DESCRIPTION: 495 !bs. spooled w;re (33# spools) ESAB
.".: ' :- 170;,T T.:C.~.7:T.;C.."..O Lot W51122 l
l
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h MM CMTR(sl one copf pa inzu covers the matenal sh:pped agazast the above nferenced pun:hnee order m:mber The above smtenal will most code requirements of ASME Secuco II, Part C and h III 1986 Edzuon through 1988 Addenda. NB2400 for Clan 1 restenal, with specal impact y.ei of15 Mbe minimum absorbed mergy at 50' F, and tbc requremeans ofASME Boiler and Pnssun Vessel Code curnet adem and =AAmda far h II, C, SFA 5.20, :=d is in compHarw with the abcm referenced purchase order m:mber We cert:fy that the matenal shipped has been bandled in compliance wi:h our id=*Jh and venScenen pro 5 rum.
All vceders on Weldstar's.yy.4 vendor list have been =*ed by Weldstar.
Weldstar's Qualny Assurance Program Revision K, dated November 12,1996 meets the %- of ASME Secuan III, NCA-3800, !995 Edinon.
The prtmsions ofNRC 10CFR Part 21 apply to this ord-r.
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1750 MITCHELL ROAD, AURORA. IL 60504-9594 PHONE (630) 859-3100 1000 E. MAIN STREET, LOGANRPORT, IND. 44947 5011 PHONE (2 9) 7221177 2650 BOND STREET, UNIVERSITY PARK. IL 60466 3181 PHONE (708) 534-E561
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VELDSTAR COMPANY custonnar Order No.: 901556
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1750 MITCHELL ROAD Order No.: 68953/RMA 3798 AURORA. IL 60504
' mis Materiki Conforza to Specification:
l ASME SFA 5.20 SEC II PART C AND ASME SEC i
III. SUBSEC NB FOR C1 JUS 1 MATERIAL 1995
[
ED.. 1995 ADD. ASME 5FA 5.01. CLASS T3.
SCHEDULE K. 10 CTR PART 21 APPLIES Trade Raana or Tradannerk Dual Shield II 70712 Diameter Sizes.045" x 338 Spool Type: E71T-1 / 717-12MJ / 717-12MJH8 Weight.: 4.752 lbs.
Test No.: 2-27679-00 Let Wimmber 51122 Ihielding Cas: 75I AR / 252 CD X-Rays satisfactory
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Carbon:
.07 Type Ste al A-285 Manganese
~1.30 Tull Split Tripla Quad Volts Amps Chroutitus:
.02 i
77 946 rx *.
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1.01 a
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Essults:
Weldad Relieved Molybdanam:
.01 8 Hrs. # 1150'T.
Ttanss ten:
Yield 81.000 73.500 Copper:
<.01 Tensile 88.000 85.500 Titanissa:
Elaegation (2'). I 28.0 27.0 Phosphorus:
. 0 13 Rad. of Area 72.4 73.4 Sulphur
.007 Vanaditan:
.01 marpy V-Wote.h lapacts Testad 0 0'7.
Cobalt:
Ft. Lbs.
109-117-120 90 ee-92 Cool Esta: 100'T.
Lat. Exp.
83-76-80 71-61-67 nr.ax/br. above 600*T.
2 Shaar 70-70-70 60-70-70 Frahaat:
65'F.
Interpass : 325'T.
Charpy V-Notch Impacts Testad 0 -20*7.
Tt Lbs.
112-96-107 41-73-50 Tillets: Or Vertical-Up/
Lat. Exp.
43-69-70 33-57-39 Overhead I Shear 70-70-70 30-40-30 Charpy V-Wotch Impacts Tasted 0 -40'F.
Ft. Lbs.
99-78-109-102-102 Lat. Exp.
69-56-78-74-70
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Tensile Speciman.505" I shaar 70-70-70-50-50
'i Impact Specimen.39&* x.394*
Deallry Systema Progres !asee 7 tie seterlel le wartif:ed to be Wo. 6, how. 4, ested 07/16/96.
f ree of ery enre.a.ry centeeleasken.
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rhe sedersignes certifies 12at the refrtente of tAls r1Ppart are State et Petmey1wente
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scrarat,e and that all operetlema performed by the cederstgr.or.
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- t. Lbe.
77-54-85 AL. Esp.
39-66-66 Shear 50-60-70 GLT N N NETHOD a wwuam ANALYSIS 1.
3.2 PC./100 0 07 VILD METAL 2.
3.1 3.
2.2 4
3.1 2.9 ATIIAGE AE VOLTAGE 26 AMPERIS 230 DC+
s
,0.2175 85.8302 70 0.225.
88.5352 70 0.2325 92.0591.
70 0.24 95.6015 70 0.2475 99.161 70 0.255 102.736 70 0.2625 106.325 70 0.27 109.926 70 0.2775 113.539-70' O.285 117.162 70 0.2925 120.793 70 0.3 124.431-70 0.3075 129.959 70-0.315 135.523 70 0.3225 141.122 70 0.33 146.752-70 0.3375 152.412-70
^0.345 158.098 70 0.3525 163.81 70
- 2. :
100.;40 70 0.3675 175.298 70
'O.375 181.071
- 70 Critical crack size =
'O.1735 i
l Li_ _ _ _ - - - - _ _ - - _ _ _ - - - - - - -
tm pc-CRACK for Windows Vers en 3.0, Mar. 27, 1997 (C) Ocpy:1;..
'E4 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info 9structint.ccm Linear Elastic Fracture Mechanics Date: Thu Nov 20 11:00:13 1997 File: 80.LFP
Title:
CPC-060: LIMITING ZERO DEGREE FLAWS Load Cases:
Case: DROP 2 - - Stress Distribution Depth Stress 0.0000 4J.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients vase ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. crack size:
0.3750
Stress Intensity Factor--------------------
Crack Case Case Case Size RES~ DUAL MEMSRANE DROP 2 I
r-a
?
0.0075 4.98488 1.19637 7.12042 0.0150-7.09853 1.~,0365 10.034 0.0225 8.75371 2.10089 12.2441-
-0.0300 10 *.77 2.4424E 14.0849 I
0.0375.
11.4554 2.74931 15.6861 0.0450 12.6334 3.03202 17.1144 0.0525-13.737 3.29688 18.4094 0.0600 14.7832 3.54796 19.5969 0.0675.
15.7835 3.78805 20.695 o
I 0.0750 16.7465 4.01917-21.7166 0.0825-17.9075 4.29781 22.9894 0.0900,
.19.0627
- t. 57506 24.2291 j
0.0975 20.2147 4.85153 25.4397 O.1050 21.3655 5.12771 26.6243 0.1125 22.5167 5.404 27.7854 0.1200 23.6695 5.68069 28.9252
.0.1275 24.8252-5.95805 30.0451 1
0.1350 25 9845-6.23629 31.1465 0.1425 27.1482 6.51557 32.2305 0.1500 2P.3168
.6.79604 33.298 0.1575 2s.7019 7.12847 34.bue4 0.1650 31.1029 7.46469 35.8642 0.'1725 32.5197 7.80472 37.1309 0.1800 33.9523 8.14855 38.3864
'O 1875 35.4007 8.49617 39.63
'O.1950 36.8649 8.84758 40.8616
-0.2025 38.3448 9.20276 42.0805
'O.2100 39.8404 9.56169 43.2863 0.21'/5 41-5515 9.92437 44.4787 0.2250 42.8782~
10.2908 45.6571 0.2325 44.8048 10.7532 47.2543 0,2400 46.7591 11.2222 48.8424
'O.2475 48.7407 11.6978 50.4204 0.'2550 50.7491
'12.1798 51.9869 0.2625 52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775 '
56.9322 13.6637 56.607 0.2850 59.0448 14.1708 58.117 0.2925 61.1827 14.6838 59.6102 0.3000 63.3455 15.2029 61.0856 0.3075 66.4177' 15.9402 63.5413 0.3150' 69.5356 16.6886 65.9877 0.3225 72.6988 17.4477 68.423 0.3300 75.9066 18.2176 70.8454 0.3375
.79.1584 18.998 73.2532 0.3450
'87.4536 19.7889 75.6445 0.3525 85.7917
' 20.59 78.0178 0.3600 89.1722 21.4013 80.3714
- 0.3675' 92.5944 22.2227 82.7036 l
0.3750 96.0581 23.0529 85.0129 l
l l
I 4 * '
IL_____z_____1_________._____________.____
" terial fracture toughness:
.cerial :0: A516_80 Depth K1c 0.0000 80.0000 0.3750-80.0000 0.7500 80.0000 Load. combination for critical crack size:
Load Case-Scale Factor RESIDUAL 1.0000
' DROP 2 1.0000 Crack Total Size K
Kic 0.0075 12.1053 80 0.015 17.1326-80 0.0225 20.9978 80 0.03 24.2618' 80 0.0375
'27.1415' 80 0.045-29,7478 80 0.0525 32.1464 80
-0.06 34.3801 80 0.0675 36.4785 80
'O.075 38.4631 80' O.0825-40.897 80 0.09 43.2916.
80
'O.0975 45.6544 80 0.105 47.9897 80 0.1125 50.3021 80 0.12 52.5947 80 0.1275 54.8703 80 0.135 57.131 80 0.1425 59.3787 80 0.15
'61.6148 80.
0.1575 64.2884-
.80 0.165~
66.9671 80
-0.1725 69.6506 80 0.18' 72.3386' B0
.0.1875~
75.0308 80 0.195 77.7265 80 J0.2025-80.4253 80 0.21 83.1267 80
[.-
l i
0.2175 85.8302 80-0.225 88.5352 80 0.2325 92.0591 80 0.24 95.6-'.5 20 0.2475 99.161 80 0.255 102.736 80 0.2625 106.315 80 0.27 109.926 80 0.2775 113.53D 80 0.285 117.162 80 0.2925 120.793 80 0.3 124.431 80 0.3075 129.959 80 0.315 135.523 80 0.3225 141.122 80 0.33 146.752 80 0.3375 152.412 80 0.345 158.098 80 0.3525 163,82 80 0.36 169.544 80 U.ae/:
tis. eve ou 0.375 181.071 80 l
Critical crack sire =
0.2013 i
i I
l
te i
pc-CRACK for Windows l
Versten 3.0, Mar.
2",
1997
- 0; Ocpy
- _ght 'S4 - '97 Structural Integrity Associates, Inc.
3315 Almacen Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info 8structint.com Linear Elastic Fracture Mechanics Date: Thu Nov 20 11:00:51 1997 File: 90.LFM
Title:
CPC-060: LIMITING ZERO DEGREE FLAWS Load Cases:
Case: DROP 2 --- Stress Distribution Depth S::ess 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients Case ID CO C1 C2 C3 Type
]
RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist i
Crack hodel: Single Edge Cracked Plate Crack Parameters:
Plate width:
0.7500 Max. crack size:
0.3750
Stress Intensity Factor--------------------
Crack Case Case Case Size RESIDUAL MEMBRANE DROP 2 N ((
ft
0.0075 4.98488 1.19637 7.12042 0.0150 7.09853 1.70365 10.034 0.0225 8.75371 2.10089 12.2441 0.0300 10.177 2.44148
'4.0949 0.0375 11.4554 2.74931 15.686*
0.0450 12.6334 3.03202 17.1144 0.0525 13.737 3.29688 18.4094 0.0600 14.7832 3.54796 19.5969 0.0675 15.7835 3.78805 20.695 J
0.0750 16.7465 4.01917 21.7166 1
0.0825 17.9075 4.29781 22.9894 0.0900 19.0627 4.57506 24.2291 0.0975 20.2147 s.85153 25.4397 0.1050 21.3655 5.12771 26.6243 0.1125 22.5167 5.404 27.7854 0.1200 23.6605 5.68069 28.9252 l
0.1275 24.8252 5.95805 30.0451 0.1350 25.9845 6.23629 31.1465 0.1425 27.1482 6.51557 32.2305 0.1500 28.3168 6.79604 33.298 U.iSia is.iU43 i.12 6 %'i 5g.a6e
)
0.1650 31.1029 7.46469 35.8642 0.1725 32.5197 7.80472 37.1309 I
0.1800 33.9523 8.14855 38.3864 l
3.1875 35.40C7 8.49617 39.63 0.1950 36.8649 8.84758 40.8616 i
0.2025 38.3448 9.20276 42.0805 0.2100 39.8404 9.56169 43.2863 0.2175 41.3515 9.92437 44.4787 0.2250 42.8782 10.2908 45.6571 0.2325 44.8048 10.7532 47.2343 0.2400 46.7591 11.2222 48.8424 0.2475 48.7407 11.6978 50.4204 0.2550 50.7491 12.1798 51.9869 0.2625 52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775 56.9322 13.6637 56.607 0.2850 59.0448 14.170P 58.117 0.2925 61.1827 14.6838 59.6102 0.3000 63.3455 15.2029 61.0856 0.3075 66.4177 15.9402 63.5413 0.3150 69.5356 16.6886 65.9877 0.3225 72.6988 17.4477 68.423 0.3300 75.9066 18.2176 70.8454 0.3375 79.1584 18.998 73.2532 0.3450.
82.4536 19.7889 75.6445 0.3525 85.7917 2D $s 78.0178 0.3600 89.1722 21.4013 80.3714 i
0.3675 92.5944 22.2227 82.7036 0.3750 96.0581 23.0539 85.0129 l
l I
i i
l l
L______.____________.______
i
"*:erial fracture toughness:
.cerial ID: A516,90 Depth Kic l
0.0000 90.0000 4
0.3750 90.0000 0.7500 90.00cv 4
Load combina::en for c::t ical crack si:e:
Lead Case Scale Factor RESIDUAL.
1.0000 DROF2 1.0000 Crack Tets)
Size K
K1c i
0.0075 12.1053 90 0.015 17.1326 90 0.0225 20.9978 90 l
0.03 24.2618-90
)
0.0375 27.1415 90 i
0.045 29.7478 90 0.0525 32.1464 90 0.06 34.3801 90 0.0675 36.4785 90 0.075 39.4631 90 0.0825 40.897 90 0.09 43.2918 90 0.0975 45.6544 90 i
0.105 47.9897 90 0.1125 50.3021 90 0.12 52.5947 90 0.1275 54.8703 90 0.135 57.131 90 0.1425 59.3787 90 0.15 61.6148 90 0.1575 64.2884 90 0.165 66.9671 90 0.1725 69.6506 90 0.18 72.3386 90 0.1875 75.0308 90 0.195 77.7265 90 0.2025 80.4253 90 0.21 e3.1207 90 I
3 I
i l
I I
,s.
m-L t_____
o 0.2175 85.8302 90 0.225 88.5352 90 0.2325 92.0591 90 C.24 95.6015 90 i
0.2475 99.161 90 0.255 102.736 90 j
0.2625 106.325 90 0.27 109.926 90 0.2775 113.539 90 j
0.285 117.162 90
.0.2925 120.793 90 0.3 124.431 90 1
0.3075 129.959 90 O.315 135.523 90 0.3225 143.122 90 l
0.33 146.752 90 0.3375 152.412 90 0.345 158.098 90 0.3525 163.81 90 0.36 169.544 90 U.JOID LID.4po 29 0.375 131.071 90 Critical crack size =
0.2291 i
I l
l l
l l
l l
I L
l i
,6 l
L__________________
1 1
4 Q
l l
l l
l tm pc-CRACK for Wincows Version 3.0, Mar. 27, 1997 (C; Copyr:;h: '54 -
'9-5 :uctural Integ::ty Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-976-8964 E-mail: info @structant.com Linear Elastic Fracture Mechanics Date: Thu Nov 20 11:01:34 1997 File: 100.LFM
Title:
CPC-060: LIMITING ZERO DEGREE FLAWS Lead Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients wase ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Single Edge Cracked Pla e Crack Partmeters:
Plate w!1th:
0.7500 Max. crack size:
0.3750
Stress Intensity Factor--------------------
Crack Case Case Case Size RESID"AL MEMBRANE DROP 2 nba 0
?
0.0075 4.98488 1.19637 7.12042 i
'0.0150
.7.09853 1.7.0365 10.034 I
0.0225 8.75371 2.10089 12.2441 I
0.03:1 10.17'
'2.44:45 14.3549
'O.0375 11.4554 2.74931 15.686*
.{
0.0450 12 #334 3.03202 17.1144 1
0.0525 13.737 3.29688 38.4094 0.0ca; 14.7832
.3.54796' 19.5969 0.0675 15.7835 3.78805 20.695
'I f
0.0750 16.7465 4.01917 21.7166 0.0825 17.9075 4.29781 22.9894 i
0.0900 19.0627 4.57506 24.2291 I
0.0975-20.2147 5.85153 25.4397 0.1050 21.3655 5.12771 26.6243 0.1125 22.5167 5.404 27.7854 0.1200-23.6695-5.68069 28.9252 0.1275 24.8252 5.95805-30.0451
- 0.1350 25.9845-6.23629 31.1465 1
0.1425 27.1482
'6.51557 32.2305 j
0.1500 28.3168 6.79604 33.298
)
0.1575
'23.70'~
7.*1547 04.;004 0.1650 31.1029 7.46469 35.8642
'O.1725 32.5197 7.80472 37.1309
.0.1800 33.9523 8.14855 38.3864 0.1875 35.4007 8.49617 39.63
- 0.1950 36.8649 8.847S8
.40.8616 0.2025 38.3448 9.20276 42.0805 0.2100 39.8404-9.56169 43.2863 0.2175 41.3515 9.92437-44.4787 0.2250 42.8782 10.2908 45.6571 0.2325' 44.8048 10.7532 47.2543 0.2400 46.7591 11.2222 48.8424 0.2475 48.7407 11.6978 50.4204 0.2550 50.7491 12.1798-51.9869 0.'2625
-52.784 12.6682 53.5409 0.2700 54.8452 13.1628 55.0813 0.2775:
56.9322 13.6637 56.607 0.2850 59.0448 14.1708 58.117 0.2925-61.1827 14.6838 59.6102 0.3000 63.3455 15.2029 61.0856 0.3075 66.4177 15.9402 63.5413 i
0.3150' 69.5356
'16.6886 65.9877 0.3225 71.6988 17.4477 68.423 0.3300
'75.9066 18.2176 70.8454 0.3375 79.1584 18.998.
73.2532 0.3450 82.4536 19.7889 75.6445 0.3525' 85.7917 20.59 78.0178 0.3600
.89.1722 21.4013 80.3714 l
0.3675-92.5944 22.2227 82.7036
{
0.3750-96.0581 23.0539 85.0129 i
j IV
"eterial fracture toughness:
aterial ID: A516_100 Depth K1c 0.0000 100.0000 0.3750 100.0000 0.7500 100.0000 Load combination for critical crack size:
Load Case Scale Factor RESIDUAL 1.0000 DROP 2 1.0000 Crack Total Size K
Kic 0.0075 12.1053 100 0.015 17.1326 100 0.0225 20.9978 100 0.03 24.2618 100 0.0375 27.1415 100 0.045 29.7476 100 0.0525-32.1464 100
'O.06 34.3801 100 0.0675 36.4785 100 0.075 38.4631 100 0.0825 40.897 100 0.09 43.2918 100 0.0975 45.6544 100 0.105 47.9897 100 0.1125 50.3021 100 0.12 52.5947 100 0.1275 54.8703 100 0.135 57.131 100 0.1425 59.3787 100 0.15 61.6148 100 0.1575 64.2084 100 0.165 66.9671 100 0.1725 69.6506 100 0.18 72.3386 100 0.1875 75.0308 100 0.195 77.7265 100 0.2025 80.4253 100 0.21 63.1267 100 l
0
.M rs
3 0.2175 85.8302 100 0.225 88.5352 100 0.2325 92.0591 100 0.24 9 5. s ' '. !
120 0.2475 99.161 100 l
0.255 102.736 100 0.2625 106.325 100 0.27 109.926 100 0.2775 113.539 100 0.285 117.162 100 1
0.2925 120.793 100 0.3 124.431 100 0.3075 129.959 100 0.315 135.523 100 0.3225 141.122 100 0.33 146.752 100 0.3375 152.412 100 0.345 158.098 100 0.3525 163.81 100 j
i 0.36 169.544 100 0.Sois ish. ira-Avu 0.375 181.071 J00 l
i Critical crack size =
0.2493 A
I tm 4
p:-CPACK for Windows Version 3.0, Mar. 27, 1997
.C' Copy :,ght '64 -
'9" Structural Integ:1ry Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-ma11: infoOstruetint.com l
Linear Elastic Fracture tiechanics Date: Mon Nov 24 1?:13:59 1997 File: CCP60A.LFM
Title:
CPC-060: SUBSURFACE DEFECT, KID =60 Load Cases:
Case: DRDP2 --- Stress Distribution l
Depth Stress J
l 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 l
Stress Coefficients j
wase ID CD C1 C2 C3 Type i
RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 Stress 0ist l
i l
l Crack Meiel: Center Cracked Flate Under Relaote Tension Stress I
l Crack Parameters:
Plate Half W:.dth:
0.3750 Crack depth:
0.3000
Stress Intensity Fact =:--------------------
Crack Case Case Case Size RESIDUAI.
MEMEFANE DROP 2 t
I U 1/
I
7 f
1 0.0060 4.11943 0.988664 5.94573 i
0.0120 5.82841 1.39882 8.41235 0.0180 7.14374 1.7145 10.3108 0.0240 8.25766 1.98184
- 1.918f 0.C300 9.245C1 2.2188 13.3437 0.0360 10.1444 2.43466 14.6418 0.0420 10.9791 2.63498 15.8465 L 0480 11.7643 2.82342 16.9798 0.0540 12.5107 3.00257 18.0572 l
0.0600 13.2264 3.17434 19.0902 0.0660 13.9176 3 34021 20.0877 0.0720 14.589 3.50137 21.0569 0.0780 15.2449 3.65878 22.0035 0.0840 15.8886 3.81226 22.9326 0.0900 16.523 3.96552 23.8482 0.0960 17.1508 4.11618 24.7543 0.1020 17.7742 4.2658 25.6541 j
0.1080 18.3954 4.41489 26.5507 0.1140 19.0164 4.56392 27.447 l
0.1200 19.639 4.71336 28.3457 0.1260 20.2651 4.be3ee er.e*>$
0.1320 20.8965 5.01516 30.1607 0.1380 21.5349 5.16837 31.0821 0.1440 22.182 5.32369 32.0161 0.1500 22.8398 5.48154 32.9655 0.1560 23.5099 5.64238 33.9327 0.1620 24.1944 5.80665 34.9206 0.1680 24.8952 5.97486 35.9322 0.1740 25.6146 6.1475 36.9705 0.1800 26.3547 6.32513 38.0387 0.1860 27.1181 6.50834 39.1405 0.1920 27.9074 6.69777 40.2797 0.1980 28.7255 6.89411 41.4605 l
0.2040 29.5756 7.39814 42.6875 1
0.2100 30.4613 7.31071 43.9659 0.2160 31.3866 7.53277 45.3012 0.2220 32.3558 7.76538 46.7002 0.2280 33.3739 8.00974 48.1698 0.2340 34.4467 8.26722 49.7182 0.2400 35.5807 8.53936 51.3549 0.2460 36.7232 8.82798 53.0906 1
l 0.2520 38.0631 9.13514 54.9378 l
0.2580 39.4304 9.46328 56.9112 0.2640 40.897 9.81529 59.0282 i
0.2700 42.4774 10.1946 61.3092 O.2760 44,1886 10.6053 63.7789 0.2820 46.0514 21.0523 66.4677 0.2880 48.0916 11.542 69.4124 0.2940 50.34*4 12.0819 72.6595 0.3000 52.9414 12.6819 76.2679 A)'
n-T
I a
- Material fracture toushness:
.aterial D: a516-60 Depth K1c 0.0000 60.0000 0.3750-60.0000-0.7500'
.60.0000.
Load combination for critical crack size:
Load Case' Scale Factor RESIDUAL 1.0000
' DROP 2.
1.0000 C ra c.k L
~ Tntel Size K
K1c 0.006 10.0652 60 0.012 114.2408 60 0.018 17.4545 60 0.024 20.1762 60 0.03
~22.5887 60 0.036-24.78631 60 0.042 26.8256 60 i
0.048 28.7441 60 0.054 30.5679 60 0.06 32.3166 60 0.066 34.0053-6'0 0.072 35.6459 60 0.078
~37.2484 60 0.084-38.8211 60 0.09 40.3712 60 0.'096-41.905.
60 O.102 43.4283' 60 0.108 44.9461 60
'O.114 46.4633
- 60 0.12 47.9847 60 0.126 49.5145 60
-0.132
~51.0572 60 0.138-52.617 60.
G 144 54.1982 60' o.15 55.8052 00
.0.156 57.4426 60 0.162 59.1 5 60~
0.168 60.8274 60 Ie e
a S
b
1 1
?
0.174 62.585 60 0.18 64.3934 60 0.186 66.2586 6C 0.192 68.'87' 60 0.198 70.186 60 0.204 72.2631 60 0.21 74.4272 60 0.216 76.6879 60 0.222 79.056 60 0.228 81.5437 60 0.234 84.1649 60 0.24 86.9355 60 0.246 89.8738 60 0.252 93.0009 60 0.258 96.3416 60 0.264 99.9252 60 0.27 103.787 60 0.276 107.968 60 0.282 112.519 60 n.?pg 117 Ana en 0.294 123.001 60 0.3 129.109 60 I
Critical crack size =
0.1652 I
-l I
1 I
I l
l i
t hY l
l
a tm pc-CRACK for Windows Vers;en 3.0, Mar. 27, 1997
':: ::py:_ght '54
'97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice:
408-978-8200 Fax:
408-978-8964 E-mail: info 9structint.com Linear Elastic Fracture Mechanics Date: Mon Nov 24 12:15:34 1997 File: CCP70.LFM
Title:
CPC-060: SUBSURFACE DEFECT, KID =70 Load Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients case ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Cente: Cracked Plate Under Remete Tension Stress Crack Parameters:
Pletc Half Width:
0.3750 Crack depth:
0.3000
Stress
- ntenstty Facter--------------------
Crack Case Case case Site RES~ DUAL MEMBRANE DROP 2 i
t 3
l-j l
1
0.0060.
4.11943 0.988664 5.94573 0.0120' 5'.82841
'1.39882 8.41235 0.0180 7.14374 1.7145 10.3108
.0.0240 8.25766 1.95184-11.9186 0.0300 9.24501 2.2188 13.3437 0.0360 10.1444.
2.43466 14.6418 0.0420 10.9791
- 2.63498 15.8465 0.0480
.11.7643 2.82342 16.9798 0.0540-12.5107 3.00257 18.0572
'O.0600 13.2264 3.17434 19.0902 0.0660 13.9176 3.34021 20.0877
'0.0720 14.589 3.50137 21.0569 0.0780 15.2449 3.65878 22.0035 0.0840 15.8886 3.81326
'22.9326 0.0900 16.f?3 3.96552 23.8482
.0.0960 17.15JE
-4.11618 24.7543 0.1020 17.7742 4.2658 25.6541 0.1080 18.3954 4.41489 26.5507 0.1140 19.0164 4.56392 27.447-n,5?nn 3o amo
.o 9, v. c to 3497 0.'1260 20.2651 4.86363 29.249'4 0.1320 20.8965 5.01516 30.1607 0.1380 21.5349 5.16837 31.0821 0.1440 22.182 5.32369-32.0161 0.1500 22.8398-5.48154 32.9655 0.1560 23.5099 5.64238 33.9327 0.1620 24.1944 5.80665 34.9206
- 0.1680 24.8952 5.97486 35.9322 0.1740' 25.6146 6.1475 36.9705 0.1800 26.3547 6.32513 38.0387 0.1860L 27.1181 6.50834 39.1405 0.1920-27.9074 6.69777 40.2797, 0.1980 28.7255 6.89411 41.4605
- 0.2040 29.5756
-7.09814 42.6875-0.2100" 30.4613' 7.31071 43.9659
- 0.2160-31.3866 7.53277 45.3013 0.2220-32.3558~
7.76538 46.7002 0.2280
,33.3739-8.00974~
48.1698 0.2340-34.4467 8.26722 49.7182 0.2400 35.5807 8.53936 51.3549 0.24601
.36.7832' 8.82798 53.0906 0.2520 38.063*
9.13514 54.9378 0.2580 39.4304 9.46328 56.9112 0.2640 40.897 9.81529 59.0282 0,2700 42.4774 10.1946 61.3092 0.2760 44.1886 10.6053 63.7789
- 0.2820 46.0514 11.0523 66.4677 h
0.2880 48.0916 11.542 69.4124 0.2940 50.'3414
-12.0514 72.6595-0.3000, 52.641(
12.6819 76~2679 4
.o l-V T 3I r\\jb
9 "aterial fracture toughness:
.aterial ID: a516-70 Depth K1c 0.0000 70.0000 0.3750 70.0000 0.7500 70.0000 Load-combination for critical crack size:
Load Case Scale Factor RESIDUAL 1.0000 DROP 2 1.0000 C..
a local Si:e K
Kic 0.006 10.0652 70 0.012 14.2408 70 0.018 17.4545 70 0.024 20.1762 70 0.03 22.5887 70 0.036 24.7863 70 0.042 26.8256 70 0.048 28.7441 70 0.054 30.5679 70 j
0.06 32.3166 70 i
~0.066 34.0053 70 0.072 35.6459 70 0.078 37.2484 70 0.084-38.8211 70 0.09 40.3712 70 0.096 41.905 70 0.102 43.4283 70 0.108 44.9461 70 0.114 46.4633 70 0.12 47.9847 70 0.126 49.5145 70 0.132 51.0572 70 0.138 52.617 70 0.144 54.1982 70 0.15 55.8052 70 0.156 57.4426 70 0.162 59.115 70 0.168 60.8274 70 o
t A?3 I
n.-
L
I
\\
j 0.174 62.585 70 I
0.18 64.3934 70 f
0.186 66.2586 70 l
0."32 i!..!.
0
{
0.198 70.186 70 0.204 72.2631 70 0.21 74.4272 70 a
0.216 76.6879 70 l
0.222 79.056 70 i
0.228 81.5437.
70 l
0.234 84.1649 70 O.24 86.9355 70 0.246 89.8738 70 0.252-93.0009 70 0.258 96.3416 70 4
0.264 99.9252 70 l
0.27 103.787 70 l
0.276 107.968 70 1
0.282 112.519 70 O ooo 317 ena 7e 0.294 123.001 70 l
0.3 129.109 70 l
Critical crack size =
0.1976 l
l i
i 1
i u, na l
i
t.m pc-CRACK for Windows Versien 3.0, Mar. 27, 1997 (C) Copyrigh: '84 - '97 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 voice:
408-978-8200 Fax:
408-978-2964 E-mail: info @structint.com Linear Elastic Fracture Mechanics Date: Mon Nov 24 12:16:49 1997 File: CCP80.LFM s
Title:
CPC-060: SUBSURFACE DEFECT, KID =80 Load Cases:
Case: DROF2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients Case ID CO C1 C2 C3 Type RESIDUAL 30 0
0 0
Coeff MIMERANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3000
Stress Intensity Factor--------------------
Crack Case Case Case Size RESIDUAL MIMERANE DROF2
\\
l s
0.0060 4.11943 0.988664 5.94573 0.0120 5.82841 1.39882 0.41235 0.0180 7.14374 1.7145 10.3108 0.024C 8.25766 1.98184
~1.9186 l
0.0300 9.24501 2.2188 13.3437 l
0.0360 10.1444 2,43466 14.6418 l
0.0420 10.9791 2.63498 15.8465 l
0.0480 11.7643 2.82342 16.9798 0.0540 12.5107 3.00257 18.0572 0.0600 13.2264 3.17434 19.0902 0.0660 13.9176 3.34021 20.0877 0.0720 14.589 3.50137 21.0569 0.0780 15.2449 3.65878 22.0035 0.0840 15.8886 3.81326 22.9326 0.0900 16.523 3.96552 23.8482 0.0960 17.1508 4.11618 24.7543 0.1020 17.7742 4.2658 25.6541 0.1080 18.3954 4.41489 26.5507 0.1140.
19.0164 4.56392 27.447 n.196n 19.439 4,7112c
?o 14:7 0.1260 20.2651 4.86363 29.2494 0.1320 20.8965 5.01516 30.1607 0.1380 21.5349 5.16837 31.0821 0.1440 22.182 5.32369 32.0161 0.1500 22.8398 5.48154 32.9655 0.1560 23.5099 5.64238 23.9327 0.1620 24.1944 5.80665 34.9206 0.1680 24.8952 5.97486 35.9322 0.1740 25.6146 6.1475 36.9705 0.1800 26.3547 6.32513 38.0387 0.1860 27.1181 6.50834 39.1405 0.1920 27.9074 6.69777 40.2797 0.1980 28.7255 6.f9411 41.4605 0.2040 29.5756 7.09814 42.6875 0.2100 30.4613 7.31071 43.9659 0.2~60 31.3866 7.53277 45.3013 0.2220 32.3558
?.76538 46.7002 0.2280 33.3739 8.00974 48.1698 0.2340 34.4467 8.26722 49.7182 0.2400 35.5807 8.53936 51.3549 0.2460 36.7832 8.82798 53.0906 0.2520 38.0631 9.13514 54.9378 0.2580 39.4304 9.46328 56.9112 0.2640 40.897 9.81529 59.0282 0.2700 42.4774 10.1946 61.3092 0.2760 44.1886 10.6053 63.7789 0.2820 46.0514 11.0523 66.4677 0.2880 48.0916 11.542 69.4124 0.2940 50.3414 12.0819 72.6595 0.3000 52.8414 12.6819 76.2679 i
~
t, Material fracture toughness:
a e :a1 ID: a516-80 Depth Kic 0.0000 80.0000 0.375C 80.0000 0.7500 80.0000 Load combination for c::tical. crack' size:
. Load Case Scale Factor RESIDUAL 1.0000 DROP 2.
1.0000
' Crack Total Size K
K1c 0.006 10.0652 80-0.012 14.2408 80
'O.018 17.4545 80 0.024 20.1762 80 LO.03 22.5887 80
-0.036
.24.7863 80' 0.042-26.8256 80 0.048 28.7441 80 0.054 30.5679 80 0.06 32.3166 80 0.066 34.0053 80 0.072 35.6459 80, 0.078 37.2484 80
.0.084 38.8211 80 0.09 10.3712 80 4.096 41.905 80 0.102 43.4283 80 0.108 44.9461 80 O.114 46.4633 80 0.T.
47.9847 80 0.126 49.5145 80 0'132 51.0572 80
)
0.138 52.617 80
-0.144 54.1982 80 l
J 0.15 55.8052 80
~
0.156 57.4426 80 C2162 59.115 80
-0.168 60.8274 80 1
l i
e A36
~
r.
l l
l 0.174 62.585 80 0.18 64.3934 80 0.186 66.2586 80 0.192 68.1871 60 l
0.198 70.186 80 0.204 72.2631 80 0.21 74.4272 80 l
0.216 76.6879 80 i
0.000 79.056 80 0.22R 81.5437 80' l
0.234
'84.1649 80 0.24 86.9355 80 0.246 89.8738 80 0.252 93.0009 80 0.258 96.3416 80 0.264 99.9252 80 0.27 103.787 80 0.276 107.968 80 0.282 112.519 80 0.266 22i.50%
ou 0.294 123.001 80 0.3 129.109 80 Critical crack size =
0.2244 f
l t
~
A37
.__--_______________________a
e i
tm I
pc-CRACK for Wincows Version 3.0, Mar. 27, 1997 l
(C; Cepy::;ht 'E4 - '97 l
Structural Integrity Associates, Inc.
l 3315 Almaden Expressway, Suite 24 i
l San Jose, CA 95118-1557 Voice:
408-978-8200 1
Tax:
408-97E-8964 1
E-mail: info @structint.com l
Linear Elastic Tracture Mechanics Date: Mon Nov 24 12:17:52 1997 File: CCP90.LIN 1
l
Title:
CPC-060: SUBSURTACE DEFECT, K:D=90 Load Cases:
Case: DROP 2 --- Stress Distribution Depth Stress 0.0000 43.3000 0.3750 7.2000 0.7500
-28.9000 Stress Coefficients case ID CD C1 C2 C3 Type RES DUAL 30 0
0 0
Coeff MEMBRANE 7.2 0
0 0
Coeff DROP 2 43.3001
-96.2668 0
0 StressDist Crack Model: Center Cracked Plate Under Remote Tension Stress l
l Crack Parameters:
Plate Half Width:
0.3750 Crack depth:
0.3000 l
i
Stress Intensity Tacte:--------------------
Crack Case Case Case Si:e RES: DUAL MEMERANE DROF2 i
l 1
l l
l i
I
~
p\\ a%
=
m s
0.0060 4.11943 0.988664 5.94573 0.0120 5.82841 1.39882 8.41235 0.0180 7.14374 1.7145 10.3108 0.C240 S.25766 1.98184 11.9186 0.0300 9.24501 2.2188 13.3437 0.0360 10.1444 2.43466 14.6418 0.0420 10.9791 2.63498 15.8465 0.0480 11.7643 2.82342 16.9798 0.0540 12.5107 3.00257 18.0572 0.0600 13.2264 3.17434 19.0902 0.0660 13.9176 3.34021 20.0877 0.0720 14.589 3.50137 21.0569 0.0780 15.2449 3.65878 22.0035 0.0840 15.8886 3.81326 22.9326 0.0900 16.523 3.96552 23.8482 0.0960 17.1508 4.11618 24.7543 0.1020 17.7742 4.2658 25.6541 0.1080 18.3954 4.41489 26.5507 0.1140 19.0164 4.56392 27.447 o.,?nn
,o cse e,13,c 7e are 0.1260 20.2651 4.86363 29.2494 0.1320 20.8965 5.01516 30.1607 0.1380 21.5349 5.16837 31.0821 0.1440 22.182 5.32369 32.0161 0.1500 22.8398 5.48154 32.9655 0.1560 23.5099 5.64238 33.9327 0.1620 24.1944 5.80665 34.9206 0.1680 24.8952 5.97486 35.9322 0.1740 25.6146 6.1475 36.9705 0.1800 26.3547 6.32513 38.0387 0.1860 27.1181 6.50834 39.1405 0.1920 27.9074 6.69777 40.2797 l
0.1980 28.7255 6.89411 41.4605 0.2040 29.5756 7.09814 42.6875 0.2100 30.4613 7.31071 43.9659 0.2160 31.3866 7.53277 45.3013 0.2220 32.3558 7.76538 46.7002 0.2200 33.3739 8.00974 48.1698 0.2340 34.4467 8.26722 49.7182 0.2400 35.5807 8.53936 51.3549 0.2460 36.7832 8.82798 53.0906 0.2520 38.0631 9.13514 54.9378 0.2580 39.4304 9.46328 56.9112 0.2640 40.897 9.81529 59.0282 0.2700 42.4774 10.1946 61.3092 0.2760 44.1886 10.6053 63.7789 0.2820 46.0514 11.0523 66.4677 0.2880 48.0916 11.542 69.4124 0.2940 50.3414 12.0819 72.6595 0.3000 52.d414
'12.6819 76.2679 l
1
s aterial fracture toughness:
v
.ter:a1 10: a516-90 Depth Kic 0.0000 90.0000 0.3750 90.0000 0.7500 90.0000 Load cer.bination fc: c :tical crack size:
Load Case Scale Facter RESIDUAL 1.0000 DROP 2 1.0000 Size K
K1c 0.006 10.0652 90 0.012 14.2408 90 0.018 17.4545 90 0.024 20.1762 90 0.03 22.5887 90 0.036 24.7863 90 0.042 26.8256 90 0.04E 28.7441 90 f
0.054 30.5679 90 0.06 32.3166 90 1
1 0.066 34.0053 90 0.072 35.6459 90 0.078 37.2464 90 l
0.004 38.6211 90 O.09 40.3712 90 0.096 41.905 90 0.102 43.42E3 90 l
0.108 44.9461 90 I
0.114 46.4633 90 O.12 47.9847 90 l
0.126 49.5145 90 0.132 51.0572 90 l
0.135 52.617 90 O.144 54.1982 90 0.15 55.8052 90 O.156 57.4426 90 C.162 59.115 90 0.16E 60.8274 90 n
t-
..N
.