ML083590339
| ML083590339 | |
| Person / Time | |
|---|---|
| Site: | FitzPatrick  |
| Issue date: | 12/04/2008 |
| From: | Gustin H, Herrmann T Structural Integrity Associates |
| To: | Office of Nuclear Reactor Regulation |
| References | |
| 10202970, JAFP-08-0131 0800769.311, Rev 1 | |
| Download: ML083590339 (66) | |
Text
JAFP-08-0131 James A. Fitzpatrick Nuclear Power Station Docket No. 50-333 Structural Integrity Associates Calculation 0800769.311 Crack Growth Analysis for Recirculation Inlet Nozzle N-2C I
Structural Integrity Associates, Inc.
File No.: 0800769.311 CALCULATION PACKAGE Project No.: 0800769 Quality Program: El Nuclear El Commercial PROJECT NAME:
Fitzpatrick RO 18 Weld Overlay Preparation CONTRACT NO.:
10202970 CLIENT:
PLANT:
Entergy Nuclear Operations, Inc.
JA Fitzpatrick CALCULATION TITLE:
Crack Growth Analysis for Recirculation Inlet Nozzle N-2C Document Affected Project Manager Preparer(s) &
Revision Pages Revision Description Approval Checker(s)
R Signature & Date Signatures & Date 0
1-12 Initial Issue A-i -A-2 B-i -B-51 In Computer Te ann Clark Oberembt Files
[TJH]
12/03/08
[CJO]
12/03/08 Terry Herrmann
[TJH]
12/03/08 Hal Gustin
[HLG]
12/03/08 1, 3, 7-10 Revised Reference 6 to
,B B-51 use a non-Proprietary Document.
Terry Herrmann Terry Herrmann
[TJH]
12/04/08
[TJH] 12/04/08 Hal Gustin
[HLG]
12/04/08 Page 1 of 12 F0306-01 RO
Structural Integrity Associates, Inc.
Table of Contents
1.0 INTRODUCTION
/OBJECTIVE.............................................................................
3 2.0 M ETH O D O LO G Y..................................................................................................
3 3.0 FLAW CHARACTERIZATION.............................................................................
3 4.0 D E SIG N IN PU T S.........................................................................................................
4 4.1 Materials and Geometry..............................................................................
4 4.2 L oading.....................................................................................................
4 5.0 ASSUMPTIONS...................................................................................................
6 6.0 CRACK GROWTH CALCULATIONS.................................................................
6 6.1 Fatigue Crack Growth (FCG)......................................................................
6 6.2 Intergranular Stress Corrosion Cracking (IGSCC)......................................
7 7.0 RESULTS AND CONCLUSIONS..........................................................................
8 8.0 R EFEREN CE S...................................................................................................
9 Appendix A FLAW INDICATION PARAMETERS...................................................
A-1 Appendix B PC-CRACK OUTPUT FILES.....................................................................
B-i List of Tables Table 1: R esults Sum m ary....................................................................................
............ 10 List of Figures Figure 1. Crack Model: Elliptical Longitudinal Crack in a Cylinder (a/l=0.1)..................... 11 F igure 2. P ath D efi nitions.......................................................................................................
11 Figure 3. Fracture Mechanics Results, K-vs-a Curve (from pc-CRACK)......................
12 File No.: 0800769.311 Page 2 of 12 Revision: 1 F0306-01
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1.0 INTRODUCTION
/OBJECTIVE An axially oriented, surface-connected indication was found in the recirculation inlet nozzle-to-safe end, N-2C-SE, dissimilar metal weld (DMW) during the September 2008 refueling outage at !.A.
Fitzpatrick Nuclear Power Plant (JAF). This indication is elliptical and is located in the weld and weld butter.
The purpose of this calculation package is to apply linear elastic fracture mechanics (LEFM) to calculate crack growth in the nozzle-to-safe end dissimilar metal weld (DMW) for the reactor pressure vessel (RPV) recirculation inlet nozzle N-2C at JAF. Loads considered are internal pressure and weld overlay (WOL) repair residual stresses. Both fatigue crack growth (FCG) and Intergranular Stress Corrosion Cracking (IGSCC) are considered.
2.0 METHODOLOGY The allowable end-of-evaluation period flaw depth to thickness ratio (a/t) was taken from Table IWB-3641-3, which is derived by the methodology of Appendix C of ASME Code,Section XI [1].
The geometry and design pressure for the N-2C nozzle is documented in a separate design input calculation [2]. The post-weld overlay (WOL) repair residual hoop stresses are documented in a separate stress analysis calculation [3].
Crack growth is computed using linear elastic fracture mechanics (LEFM) techniques. IGSCC growth is determined by computing the stress intensity factor versus flaw depth curve (K-vs.-a) at steady state normal operating conditions. Crack growth laws for Alloy 600 weld metals (Alloy 82/Alloy 182) are used at the susceptible DMW material region [1]. The time for the observed flaw to grow to 75% of the weld thickness is determined, with and without the benefit of WOL residual stresses.
The crack growth analysis was performed using the LEFM analysis option in pc-CRACK for WindowsTM software [7]. This software includes options for the evaluation of FCG and IGSCC, and allows for defining load cases, material properties, crack models, and the selection of the applicable crack growth law. Appendix B contains pc-CRACK output of the IGSCC and FCG growth analyses.
3.0 FLAW CHARACTERIZATION The inspection results were provided in Reference [5], and are included in Appendix A of this calculation. The indication is a semi-elliptical surface connected flaw, bounded by parameters 1 = 0.8" and a = 0.51". Figure 1 shows an illustration of the crack model used in this analysis.
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This indication was evaluated and shown to satisfy the requirements of Appendix C and Table IWB-3641-3 [1].
Current a/t = 0.51/1.2188 = 0.42 0
Stress Ratio = (PD/2t)/Sm = 7.371/23.3 = 0.32
- Nondimensional Flaw Length = lf/(rt)
= 0.8/(7.1875*1.2188)1/2 = 0.27 0 Allowable a/t = 0.75 The indication was also evaluated after implementation of the WOL repair. The locally increased wall thickness (design minimum value of 0.41" [3]) reduces the a/t ratio from 0.42 to 0.31.
4.0 DESIGN INPUTS 4.1 Materials and Geometry Details of the recirculation inlet nozzle materials and geometry are provided in References [2] and [3].
The section evaluated for crack growth, and considered representative for the susceptible material region, is described below:
Material (Safe End):
SA-182 F304 low carbon Material (Nozzle):
SA-508 Class 2 Material (Weld):
Alloy 82/182 Pressure (P) 1:
1250 psi Outside radius OR = 7.1875 in.
Inside radius2 IR = 5.96875 in.
Thickness t = 1.2188 in.
Pipe cross-sectional Area= 3t(OR 2-IR2)
= 50.37 in2 Section modulus Z=7t/4(OR 4-IR 4)/OR = 152.93 in3 Note 1: The pressure used for analysis is the vessel design pressure [2], which is approximately equal to the recirculation system operating pressure.
Note 2: IR measurement is radius to base metal less cladding thickness.
4.2 Loading Loads considered in this evaluation are internal pressure and WOL residual stresses. Bending stresses are oriented parallel to the observed axial flaw, and do not affect such a flaw. Hoop stresses tend to open an axial flaw, and are due entirely to internal pressure. The through-wall residual stress distributions are curve fit with a third order polynomial in the form shown below:
O'(X) = Co + ClX + C 2X2 + C 3X3 (1)
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where:
a = stress (axial or hoop) x = distance from the inside surface Residual stress results were obtained for through-wall paths in the susceptible material regions. The paths used are as defined in Figure 2. It is important to note that the critical paths selected within the susceptible material regions have different path lengths. The intent for this approach is to characterize the residual stresses for each of the different loading conditions for three different locations within the DMW. Applied stress intensity factors are conservatively computed for one representative section using the most limiting path of the three paths analyzed. Residual stresses have a strong effect on IGSCC growth. They have a much less significant effect on fatigue crack growth, since they are steady state secondary stresses, and contribute to FCG only through a mean stress effect.
Internal Pressure The pressure stress is evaluated at the design pressure, 1250 psi. Given this pressure and the nozzle geometry the primary hoop stress (Phoop) is calculated as follows:
Primary hoop stress Phoop = circumferential pressure stress= P*(OR)/t= 7371 psi.
Note that in this formulation, the OR is used, rather than the IR, which accounts for pressure on the crack face. In addition, the thin wall formula is used per the guidance in ASME Section XI, Appendix C, section C-3410 [1], which results in a conservatively higher calculated hoop stress than would result from using the thick wall formula used in Reference [3]. This value of Phoop is assumed to be constant through the thickness and is represented by the Co coefficient from Equation (1).
WOL Residual Stresses The residual stresses which result from implementing a weld repair are developed from the ANSYS model described in Reference [4]. The values of stresses are given for 70'F and 55 10F. These stresses vary across the thickness and are represented by the curve fit Equation 1. These stresses are obtained using the ANSYS output files "RSDUAL_70F.RES" and "RSDUAL_55 1F.RES", and they are digitized using pc-CRACK to perform the curve fit. Three paths were investigated and the bounding paths for hoop stress within the DMW region were determined by calculating the K-vs-a curves within pc-CRACK, Figure 3. These bounding residual stresses are used for the crack growth analysis.
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5.0 ASSUMPTIONS Basic assumptions for the analysis are listed below:
" The through-wall residual stress distribution is sufficiently represented with a third order polyinomial curve fit.
- This residual stress is considered in addition to the applied membrane stress calculated above.
Weld residual stresses are steady state secondary stresses.
- Bending stresses are oriented parallel to the observed flaw and, therefore, do not affect the observed axially oriented flaw.
6.0 CRACK GROWTH CALCULATIONS 6.1 Fatigue Crack Growth (FCG)
FCG is calculated using the loading described in section 4.2. The minimum stress intensity Kmin is taken as the weld repair residual hoop stress distribution at 70'F, which is present when the plant is shutdown. Path 2 from Figure 3 is bounding at 70'F. The maximum stress intensity Kmax is the combination of the pressure hoop stress and the residual hoop stress at 55 I°F. Path 1 from Figure 3 is bounding at 551 VF. This stress intensity range represents the range seen from shutdown to startup. The FCG after 10,000 applied cycles is calculated using pc-CRACK software using the crack growth law for austenitic material in air, as described by Figure C-32 10-1 in Section XI Appendix C of the ASME Code [1]. Note that 10,000 cycles was an arbitrary number chosen as the limit of the pc-CRACK calculations.Section XI does not yet provide a FCG correlation for austenitic materials in a water environment. Appendix B contains output files for FCG with and without WOL residual stresses.
The stress intensity components of Kmax and Kmin for the weld overlay case are shown below. For the condition where residual stresses were not considered, the Kresidual components do not apply.
Kmax Kmin Kresidual 551 Kpressure Kresidual 70 File No.: 0800769.311 Revision: 1 Page 6 of 12 F0306-01.
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6.2 Intergranular Stress Corrosion Cracking (IGSCC)
For IGSCC, the applied K (Kmax above) is the crack driving force. The time needed to grow the crack to 75% through the as-repaired wall thickness is calculated. PVP2008-61299 [6] provides stress corrosion crack growth laws for high nickel base austenitic alloys. Fitzpatrick is on hydrogen water chemistry (HWC) [8]. Therefore, the HWC case is evaluated.
The SCC growth law is:
da
-=COK" in/hrforK 1 <25ksilin dt da
-C, in/hr for K, > 25 ksi~in (2)
(3)
- where, Water Chemistry CO C1 n
Hydrogen 3.2E-10 5.OE-06 3.0 K, = stress intensity factor at flaw tip (ksiVin)
The K-dependent crack growth rates are calculated with pc-CRACK using the coefficients shown above and the K values developed within the software. For this evaluation the K-independent crack growth rates were not used since the combined stress intensity factor was never greater than +25 ksi\\Iin, as seen in Figure 3. Appendix B contains pc-CRACK output files for the following cases:
- IGSCC case without residual stresses.
- FCG case without residual stresses.
- FCG case with WOL residual stresses.
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The pc-CRACK and ANSYS computer files used in this evaluation are listed below.
File Name Description RSDUAL 70F.RES ANSYS Residual Stress Output at 70'F RSDUAL 551F.RES ANSYS Residual Stress Output at 551 'F FCG-NORSDL.OUT pc-CRACK Output File for Fatigue Crack Growth with Weld Overlay and without Residual Stresses FCG-WOL.OUT pc-CRACK Output File for Fatigue Crack Growth with Weld Overlay and considering Residual Stresses IGSCCHWC-NORSDL.OUT pc-CRACK Output File for IGSCC with Weld Overlay, Hydrogen Water Chemistry and without Residual Stresses IGSCCHWC-WOL.OUT pc-CRACK Output File for IGSCC with Weld Overlay, Hydrogen Water Chemistry and considering Residual Stresses N2.LFM pc-CRACK Input File for Recirculation Inlet Nozzle N-2 7.0 RESULTS AND CONCLUSIONS This evaluation shows that the indication found during 2008 inspection of the JAF N-2C nozzle-to-safe end weld is acceptable and meets the requirements of ASME Code,Section XI, Appendix C and Table IWB-3641-3 [1]. Table 1 provides a summary of the calculation results. The additional wall thickness provided by the WOL repair will allow for another 20 years of operation even when conservatively ignoring the beneficial effects WOL residual stresses. However, the WOL residual stresses provide a significant benefit to the mitigation of crack growth, especially for IGSCC growth. Taking credit for these residual stresses produces a negative stress intensity factor, resulting in no further crack growth at this location.
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8.0 REFERENCES
- 1.
ASME Boiler & Pressure Vessel Code,Section XI, 2001 Edition, with Addenda through 2003.
- 2.
SI Calculation No. 0800769.30 1, Rev. 0, "Design Input for RPV Recirculation Inlet & Outlet Nozzle Finite Element Analyses and Flaw Evaluation Readiness."
- 3.
SI Calculation No. 0800769.302, Rev. 3, "Contingency Dissimilar Metal Weld Overlay Design for Recirculation Inlet Nozzle for Fitzpatrick."
- 4.
SI Calculation No. 0800769.307, Rev. 2, "Residual Stress Analysis of Recirculation Inlet Nozzle with and without Weld Overlay Repair."
- 5.
Hitachi Customer Notification Form (CNF-001R1), "N-2C-SE Indication Parameters," dated September, 26, 2008, SI File No. 0800769.201.
- 6.
ASME Paper PVP2008-61299, "Nickel Alloy Crack Growth Correlations in BWR Environment and Application to Core Support Structure Welds Evaluation," July, 2008, SI File No. BWRVIP-01-259P.
- 7.
pc-CRACK for Windows, Version 3.1-98348, Structural Integrity Associates, 1998.
- 8.
James A. FitzPatrick Nuclear Power Plant License Renewal Application, Appendix A, Section A.2.1.33 File No.: 0800769.311 Page 9 of 12 Revision: I F0306-01i
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Table 1: Results Summary IGSCC Water Chem Time Crack Growth hours years No Residual Stresses Hydrogen 175200 20 0.0849 in With Residual Stresses Hydrogen 175200 20 No Growth I
Without Residual Stresses 0.0048 in With Residual Stresses No Growth Note 1: Fatigue crack growth calculations are for 10,000 transient cycles.
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S= Co+ClX+C 2x 2 +C3 )X3 Co: inner aunface stress (x=O)
R a_
t Calculated K isthemaximurn of K at points 1 and 2 at each crack depth(a)
REQUIRED IqPUTS:
Ref t:
wall thickness Raju and Newman, PVP -Vol 58 a: maxrmm crack depth (a.. i 0.8t)
Figure 1. Crack Model: Elliptical Longitudinal Crack in a Cylinder (a/l=0.1)
AN Qcr 9 2006 MAT NUM Path 3 Path 2 Path 1 10:24:35 Recirculation Inlet Nozzle Finite Element Model For Fitzpatrick Figure 2. Path Definitions File No.: 0800769.311 Revision: 1 Page 11 of 12 F0306-0]
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40 20__
S 0 c -20 E
-40
-60
-80 P1 _rsdl_70F_hoop P2_rsdl_70F_hoop P3_rsdl_70F_hoop P1 _rsdl_551F_hoop P2_rsdi_551F_hoop P3_rsdl_551 Fhoop primary hoop stress Crack Size, a (in)
Figure 3. Fracture Mechanics Results, K-vs-a Curve (from pc-CRACK)
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Appendix A FLAW INDICATION PARAMETERS File No.: 0800769.311 Revision: 1 F0306-01 RO Page A-I of A-2
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Appendix B PC-CRACK OUTPUT FILES File No.: 0800769.311 Revision: I F0306-01 R0 Page B-I of B-51
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Output for IGSCC case without residual stresses:
tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 - '98 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax:
408-978-8964 E-mail: pccrack@stru~tint.com Linear Elastic Fracture Mechanics Date: Mon Dec 01 15:37:11 2008 Input Data and Results File: N2.LFM
Title:
JAF N2 Crack Growth Without Residual Stresses Load Cases:
Case ID: Plrsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000
-39.7170 0.0793
-40.3490 0.1587
-40.7120 0.2380
-40.9920 0.3173
-40.0580 0.3967
-36.4000 0.4760
-30.3220 0.5553
-22.7690 0.6347
-12.5050 0.7140
-1.5176 0.7933 3.8362 0.8727 6.5966 0.9520 8.8339 1.0313 10.6030 1.1107 11.4380 1.1900 11.8810 1.2693 13.8740 File No.: 0800769.311 Revision: 1 Page B-2 of B-51 F0306-01 RO
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1.3487 1.4280 1.5073 1.5867 17.0970 18.6230 18,0990 15.5500 Case ID: P2_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584 0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-40,6750
-38,7950
-36,3090
-35,6780
-38.8330
-33,5040
-39,3260
-36,5530
-21,1880
-4.6270 9.1298 15.3010 16.8200 16.7900 15.8530 14.3480 15.4520 20.0010 24.3720 27.8520 29.3440 Case ID: P3_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000
-38.4610 0.0853
-39.5790 0.1707
-49.1040 0.2560
-51.6050 0.3413
-51.2820 0.4266
-47.4160 0.5120
-41.6810 0.5973
-32.7260 0.6826
-20.8590 0.7679
-9.6705 File No.: 0800769.311 Revision: 1 Page B-3 of B-51 F0306-01 RO
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0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-0.2673 7.0081 8.3770 9.4758 9.1873 9.0162 11.2680 15.8210 18.7370 21.4980 23.6410 Case ID: Plrsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693 1.3487 1.4280 1.5073 1.5867
-26.5210
-26.9270
-26.9240
-26.3780
-24.6910
-20.6710
-14.6190
-7.2662 2.3816 12.6720 17.6200 20.1090 22.0400 23.5030 22.1790 20.0260 17.4550 20.1960 21.3010 20.4310 17.8390 Case ID: P2_rsdl_551Fhoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584
-32.6410
-30.4050
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0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-23.6480
-25.6030
-20.0130
-25.0810
-22.2480
-7.8169 7.6241 20.3840 26.0170 27.2700 27.0450 24.8660 20.2130 16.8180 20.8460 24.6800 27.6550 28.8950 Case ID: P3_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0853 0.1707 0.2560 0.3413 0.4266 0.5120 0.5973 0.6826 0.7679 0.8533 0.9386 1.0239 1.1093 1*1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-29.0710
-31.1390
-37.1380
-38.5510
-37.6290
-34.0970
-29.0900
-20.9770
-10.0800 0.1012 8.4945 14.8890 15.7350 16.1220 13.6400 11.2460 8.7844 12.6900 15.0840 17.3120 19.0350 File No.: 0800769.311 Page B-5 of B-51 Revision: 1 F0306-O1RO
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Stress Coefficients CO C1 Case ID C2 C3 Type P1 rsdl 70F hoo P2_rsdl_70F hoo P3 rsdl 70F hoo P1-rsdl-551F ho P2 rsdl 551F ho P3 rsdl 551F'ho primary hoop st
-42.6891
-39.4702
-42.8367
-30.5175
-32.6415
-34.3878 7.371
-7.07378
-30.1753
-48.9998 11.0008 1.43969
-24.6287 0
115.185 145.503 154.565 90.953 105.477 118.724 0
-56.0956
-64.3057
-62.0792
-50.9343
-53.8
-52.269 0
StressDist StressDist StressDist StressDist StressDist StressDist Coeff Through Wall Stresses for Load Cases With Stress Coeff-------
Wall Case Depth primary ho 0.0000 0.1220 0.2440 0.3660 0.4880 0.6100 0.7320 0.8540 0.9760 1.0980 1.2200 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 Crack Model: Elliptical Longitudinal Crack in Cylinder (t/R=0.1,a/l=0.1)
WARNING: The stress intensity factor (K) is the maximum of K at the surface and K at the deepest point at each crack depth.
Crack Parameters:
Wall thickness:
Max. crack size:
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-Stress Intensity Factor--------------------
Crack Case Size P1_rsdl_70 Case P2_rsdl_70 Case Case Case P3_rsdl, 70 P1_rsdl_55 P2_rsdl_55 0.0244
-6.71806 0.0488
-9.48828 0.0732
-11.6043-0.0976
-13.3793 0.1220.
-14.9344 0.1464
-16.3317 0.1708
-17.6407 0.1952
-18.9295 0.2196
-20.1503 0.2440
-21.3137 0.2684
-22.4279 0.2928
-23.4987 0.3172
-24.5309 0.3416
-25.6197 0.3660
-26.7332 0.3904
-27.8254 0.4148
-28.8976 0.4392
-29.9508 0.4636
-30.9857 0.4880
-32.0029 0.5124
-33.1651 0.5368
-34.3204 0.5612
-35.4642 0.5856
-36.5961 0.6100
-37.7156 0.6344
-38.8222 0.6588
-39.9702 0.6832
-41.236 0.7076
-42.4914 0.7320
-43.7352 0.7564
-44.9667 0.7808
-46.1849 0.8052
-47.3889 0.8296
-48.6983 0.8540
-50.0665 0.8784
-51.4199 0.9028
-52.7572 0.9272
-53.1925 0.9516
-52.6735 0.9760
-52.0769 File No.: 0800769.311 Revision: 1
-6.22218
-8.80282
-10.784
-12.4539
-13.9239
-15.2508
-16.4992
-17.7332
-18.907
-20.0303
-21.1103
-22.1523
-23.1605
-24.2264
-25.3196
-26.3954
- -27.455
-28.4989
-29.5277
-30.5417
-31.7001
-32.8544
-34.0000
-35.1362
-36.2624
-37.3778
-38.536
-39.813
-41.0815
-42.3404
-43.5886
-44.8248
-46.048
-47.3774
-48.7665
-50.1416
-51.5014
-52.8443
-53.0186
-52.2251
-6.76032
-9.57471
-11.7426
-13.5761
-15.1956
-16.6625
-18.0472
-19.4205
-20.7315
-21.9907
-23.2059
-24.3829
-25.5263
-26.7386
-27.9863
-29.2194
-30.439
-31.6459
-32.8407
-34.0238
-35.3773
-36.7324
-38.0839
-39.4311
-40.7733
-42.1099
-43.5031
-45.0418
-46.579
-48.1134
-49.6438
-51.1689
-52.6876
-54.3414
-56.0763
-57.8054
-59.527
-61.2397
-62.942
-64.6325
-4.79525
-6.76207
-8.25709
-9.50485
-10.5924
-11.5643
-12.4699
-13.3569
-14.1919
-14.9827
-15.735
-16.4531
-17.1404
-17.8612
-18.5937
-19.3064
-20.0001
-20.6755
-21.333
-21.973
-22.7021
-23.4195
-24.1222
-24.8097
-25.4817
-26.1377
-26.812
-26.6359
-26.054
-25.3891
-24.6421
-23.8134
-22.9039
-21.974
-21.0074
-19.9712
-18.8676
-17.6986
-16.4669
-15.1748
-5.13368
-7.24594
-8.85602
-10.2036
-11.3814
-12.4371
-13.4234
-14.392
-15.3066
-16.1754
-17.0044
-17.7981
-18.5602
-19.3613
-20.1775
-20.9742
-21.7524
-22.5126
-23.2553
-23.9809
-24.808
-25.6248
-26.4279
-27.2167
-27.9908
-28.7496
-29.5319
-30.3916
-31.2364
-31.7379
-31.0844
-30.3369
-29.4957
-28.6297
-27.719
-26.7251
-25.6496
-24.4942
-23.261
-21.952 Page B-7 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-51.6976
-51.2794
-50.8105
-50.295
-49.7375
-49.1428
-48.5185
-47.8864
-47.2532
-46.6274
-51.6365
-50.9895
-50.2715
-49.4867
-48.6393
-47.7339
-46.7905
-45.8538
-44.8991
-43.935
-66.5355
-68.4384
-70.3271
-72.1998
-74.0551
-75.8777
-75.5827
-75.2889
-74.9613
-74.6071
-14.0253
-12.847
-11.6338
-10.3904
-9.12204
-7.83391
-6.53329
-5.23966
-3.96252
-2.71053
-20.7907
-19.5863
-18.331
-17.0293
-15.6858
-14.3055
-12.8971
-11.4835
- 10.0689
-8.66168
Stress Intensity Factor-Crack Case Case Size P3_rsdl_55 primary ho 0.0244
-5.42025 0.0488
-7.6673 0.0732
-9.39176 0.0976
-10.8449 0.1220
-12.1237 0.1464
-13.2777 0.1708
-14.3633 0.1952
-15.4364 0.2196
-16.4569 0.2440
-17.4335 0.2684
-18.3725 0.2928
-19.2785 0.3172
-20.1552 0.3416
-21.0823 0.3660
-22.0333 0.3904
-22.9696 0.4148
-23.8919 0.4392
-24.8009 0.4636
-25.6973 0.4880
-26.5812 0.5124
-27.5913 0.5368
-28.5985 0.5612
-29.5988 0.5856
-30.5916 0.6100
-31.5764 0.6344
-32.5526 0.6588
-33.5671 0.6832
-34.6861 0.7076
-35.7989 File No.: 0800769.311 Revision: 1 1.92366 2.74502 3.39203 3.9515 4.45674 4.92465 5.36888 5.80088 6.21779 6.62266 7.0178 7.40494 7.78545 8.17085 8.55815 8.94264 9.32488 9.70534 10.0844 10.4625 10.859 11.2565 11.6547 12.0536 12.4535 12.8544 13.2633 13.6898 14.1185 Page B-8 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
0.7320 0.7564 0.7808 0.8052 0.8296 0.8540 0.8784 0.90 28 0.9272 0.9516 0.9760 1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-36.9044
-38.0017
-39.0899
-40.1681
-41.3407
-42.5671
-43.7829
-44.9871
-46.1785
-47.3561
-48.1482
-47.8113
-47.4277
-46.9864
-46.4907
-45.944
-45.3499
-44.7235
-44.099
-43.4594
-42.8116 14.5494 14.9826 15.4181 15.856 16.3116 16.7796 17.2508 17.7251 18.2026 18.6832 19.167 19.6987 20.2373 20.7801 21.3272 21.8785 22.4339 22.9901 23.5412 24.0961 24.6548 Crack Growth Laws:
Law ID: IGSCCHWC Type: Corrosion Model: Paris da/dN = c * (dK)An where dK = Kmax - Kmin dK > Kthres Kmax < K1c Material parameters:
c = 3.2000e-010 n =
3.0000 Kthres 0.0000 Material Fracture Toughness KIc:
Material ID: Alloy 82/182 File No.: 0800769.311 Revision: 1 Page B-9 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
Depth KIc 0.0000 0.7500 1.5000 63.2500 63.2500 63.2500 Material ID: high toughness Depth KIc 0.0000 0.7500 1.5000 200.0000 200.0000 200.0000 Initial crack size=
0.5100 Max. crack size=
1.2200 Number of blocks=
1 Print increment of block=
1 Cycles Subblock
/Time Calc. Print Crk. Grw.
incre. incre. Law Mat.
Klc growth 175200 20 1000 IGSCCHWC Alloy 82/182 Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor growth primary hoop stress 1.0000 Crack growth results:
Total Subblock Cycles Cycles
/Time
/Time Kmax DaDn DeltaK R
/DaDt Kmin Da a
a/thk Block:
1 1000 1000 2000 2000 3000 3000 4000 4000 1.08e+001 1.08e+001 1.08e+001 1.08e+001 0.00e+000 0.00e+000 0.00e+000 0.00e+000 1.08e+001 0.00 4.06e-007 1.08e+001 0.00 4.07e-007 1.08e+001 0.00 4.08e-007 1.08e+001 0.00 4.08e-007 8.12e-006 0.5104 0.31 8.14e-006 0.5108 0.31 8.15e-006 0.5112 0.31 8.17e-006 0.5116 0.31 File No.: 0800769.311 Revision: 1 Page B-10 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
5000 5000 1.09e+001 0.00e+000 1.09e+001 0.00 4.09e-007 8.18e-006 0.512 0.31 6000 6000 1.09e+001 0.00e+000 1.09e+001 0.00 4.10e-007 8.20e-006 0.5124 0.31 7000 7000 1.09e+001 0.00e+000 1.09e+001 0.00 4.1le-007 8.21e-006 0.5129 0.31 8000 8000 1.09e+001 0.00e+000 1.09e+001 0.00 4.1 le-007 8.23e-006 0.5133 0.32 9000 9000 1.09e+001 0.00e+000 1.09e+001 0.00 4.12e-007 8.24e-006 0.5137 0.32 10000 10000 1.09e+001 0.00e+000 1.09e+001 0.00 4.13e-007 8.26e-006 0.5141 0.32 11000 11000 1.09e+001 0.00e+000 1.09e+001 0.00 4.14e-007 8.27e-006 0.5145 0.32 12000 12000 1.09e+001 0.00e+000 1.09e+001 0.00 4.14e-007 8.29e-006 0.5149 0.32 13000 13000 1.09e+001 0.00e+000 1.09e+001 0.00 4.15e-007 8.30e-006 0.5153 0.32 14000 14000 1.09e+001 0.00e+000 1.09e+001 0.00 4.16e-007 8.32e-006 0.5157 0.32 15000 15000 1.09e+001 0.00e+000 1.09e+001 0.00 4.17e-007 8.33e-006 0.5162 0.32 16000 16000 1.09e+001 0.00e+000 1.09e+001 0.00 4.17e-007 8.35e-006 0.5166 0.32 17000 17000 1.09e+001 0.00e+000 1.09e+001 0.00 4.18e-007 8.37e-006 0.517 0.32 18000 18000 1.09e+001 0.00e+000 1.09e+001 0.00 4.19e-007 8.38e-006 0.5174 0.32 19000 19000 1.09e+001 0.00e+000 1.09e+001 0.00 4.20e-007 8.40e-006 0.5178 0.32 20000 20000 1.1Oe+001 0.00e+000 1.1Oe+001 0.00 4.21e-007 8.41e-006 0.5183 0.32 21000 21000 1.10e+001 0.00e+000 1.0Oe+001 0.00 4.21e-007 8.43e-006 0.5187 0.32 22000 22000 1.1Oe+001 0.00e+000 1.10e+001 0.00 4.22e-007 8.44e-006 0.5191 0.32 23000 23000 1.1Oe+001 0.00e+000 1.10e+001 0.00 4.23e-007 8.46e-006 0.5195 0.32 24000 24000 1.1Oe+001 0.00e+000 1.10e+001 0.00 4.24e-007 8.48e-006 0.5199 0.32 25000 25000 1.10e+001 0.00e+000 1.1Oe+001 0.00 4.25e-007 8.49e-006 0.5204 0.32 26000 26000 1.10e+001 0.00e+000 1.1Oe+001 0.00 4.25e-007 8.51e-006 0.5208 0.32 27000 27000 1.10e+001 0.00e+000 1.10e+001 0.00 4.26e-007 8'.52e-006 0.5212 0.32 28000 28000 1.10e+001 0.00e+000 1.10e+001 0.00 4.27e-007 8.54e-006 0.5216 0.32 29000 29000 1.1Oe+001 0.00e+000 1.1Oe+001 0.00 4.28e-007 8.56e-006 0.5221 0.32 30000 30000 1.1Oe+001 0.00e+000 1.10e+001 0.00 4.29e-007 8.57e-006 0.5225 0.32 31000 31000 1.10e+001 0.00e+000 1.1Oe+001 0.00 4.29e-007 8.59e-006 0.5229 0.32 32000 32000 1.10e+001 0.00e+000 1.1Oe+001 0.00 4.30e-007 8.61e-006 0.5234 0.32 33000 33000 1.10e+001 0.00e+000 1.1Oe+001 0.00 4.31e-007 8.62e-006 0.5238 0.32 34000 34000 1.lie+001 0.00e+000 1.lle+001 0.00 4.32e-007 8.64e-006 0.5242 0.32 35000 35000 1.1 le+001 0.00e+000 1.11 e+001 0.00 4.33e-007 8.66e-006 0.5247 0.32 36000 36000 1.lle+001 0.00e+000 1.lle+001 0.00 4.34e-007 8.67e-006 0.5251 0.32 37000 37000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.34e-007 8.69e-006 0.5255 0.32 38000 38000 1.le+001 0.00e+000 1.lie+001 0.00 4.35e-007 8.71e-006 0.526 0.32 39000 39000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.36e-007 8.72e-006 0.5264 0.32 40000 40000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.37e-007 8.74e-006 0.5268 0.32 41000 41000 1.lie+001 0.00e+000 1.lie+001 0.00 4.38e-007 8.76e-006 0.5273 0.32 42000 42000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.39e-007 8.77e-006 0.5277 0.32 43000 43000 1.lie+001 0.00e+000 l.lle+001 0.00 4.39e-007 8.79e-006 0.5281 0.32 44000 44000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.40e-007 8.81e-006 0.5286 0.32 45000 45000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.41e-007 8.82e-006 0.529 0.32 46000 46000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.42e-007 8.84e-006 0.5295 0.33 47000 47000 1.1 le+001 0.00e+000 1.1 le+001 0.00 4.43e-007 8.86e-006 0.5299 0.33 48000 48000 1.12e+001 0.00e+000 1.12e+001 0.00 4.44e-007 8.87e-006 0.5304 0.33 49000 49000 1.12e+001 0.00e+000 1.12e+001 0.00 4.45e-007 8.89e-006 0.5308 0.33 File No.: 0800769.311 Page B-11 of B-51 Revision: 1 F0306-01 RO
Structural Integrity Associates, Inc.
50000 51000 52000 53000 54000 55000 56000 57000 58000 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000 87000 88000 89000 90000 91000 92000 93000 94000 50000 1.12e+001 0.00e+000 1.12e+001 51000 1.12e+001 0.00e+000 1.12e+001 52000 1.12e+001 0.00e+000 1.12e+001 53000 1.12e+001 0.00e+000 1.12e+001 54000 1.12e+001 0.00e+000 1.12e+001 55000 1.12e+001 0.00e+000 1.12e+001 56000 1.12e+001 0.00e+000 1.12e+001 57000 1.12e+001 0.00e+000 1.12e+001 58000 1.12e+001 0.00e+000 1.12e+001 59000 60000 61000 62000 63000 64000 65000 66000 67000 68000 69000 70000 71000 72000 73000 74000 75000 76000 77000 78000 79000 80000 81000 82000 83000 84000 85000 86000 87000 88000 89000 90000 91000 92000 93000 94000 1.12e+001 0.00e+000 1.12e+001 1.12e+001 0.00e+000 1.12e+001 1.12e+001 0.00e+000 1.12e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.13e+001 0.00e+000 1.13e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+00I 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001 0.00e+000 1.14e+001 1.14e+001'0.00e+000 1.14e+001 0.00 4.45e-007 8.91e-006 0.5312 0.33 0.00 4.46e-007 8.93e-006 0.5317 0.33 0.00 4.47e-007 8.94e-006 0.5321 0.33 0.00 4.48e-007 8.96e-006 0.5326 0.33 0.00 4.49e-007 8.98e-006 0.533 0.33 0.00 4.50e-007 9.00e-006 0.5335 0.33 0.00 4.5 1e-007 9.Ole-006 0.5339 0.33 0.00 4.52e-007 9.03e-006 0.5344 0.33 0.00 4,53e-007 9.05e-006 0.5348 0.33 0.00 4.53e-007 9.07e-006 0-5353 0.33 0.00 4.54e-007 9.09e-006 0.5357 0.33 0.00 4.55e-007 9.10e-006 0.5362 0.33 0.00 4.56e-007 9.12e-006 0.5367 0.33 0.00 4.57e-007 9.14e-006 0.5371 0.33 0.00 4.58e-007 9.16e-006 0.5376 0.33 0.00 4.59e-007 9.18e-006 0.538 0.33 0.00 4.60e-007 9.20e-006 0.5385 0.33 0.00 4.6le-007 9.2le-006 0.5389 0.33 0.00 4.62e-007 9.23e-006 0.5394 0.33 0.00 4.63e-007 9.25e-006 0.5399 0.33 0.00 4.63e-007 9.27e-006 0.5403 0.33 0.00 4.64e-007 9.29e-006 0.5408 0.33 0.00 4.65e-007 9.3 1e-006 0.5413 0.33 0.00 4.66e-007 9.32e-006 0.5417 0.33 0.00 4.67e-007 9.34e-006 0.5422 0.33 0.00 4.68e-007 9.36e-006 0.5427 0.33 0.00 4.69e-007 9.38e-006 0.5431 0.33 0.00 4.70e-007 9.40e-006 0.5436 0.33 0.00 4.71e-007 9.42e-006 0.5441 0.33 0.00.4.72e-007 9.44e-006 0.5445 0.33 0.00 4.73e-007 9.46e-006 0.545 0.33 0.00 4.74e-007 9.48e-006 0.5455 0.33 0.00 4.75e-007 9.50e-006 0.546 0.34 0.00 4.76e-007 9.52e-006 0.5464 0.34 0.00 4.77e-007 9.54e-006 0.5469 0.34 0.00 4.78e-007 9.55e-006 0.5474 0.34 1.14e+001 0.00e+000 1.14e+001 0.00 4.79e-007 9.57e-006 0.5479 0.34 1.14e+001 0.00e+000 1.14e+001 0.00 4.80e-007 9.59e-006 0.5483 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.81e-007 9.61e-006 0.5488 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.82e-007 9.63e-006 0.5493 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.83e-007 9.65e-006 0.5498 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.84e-007 9.67e-006 0.5503 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.85e-007 9.69e-006 0.5508 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.86e-007 9.71e-006 0.5512 0.34 1.15e+001 0.00e+000 1.15e+001 0.00 4.87e-007 9.73e-006 0.5517 0.34 File No.: 0800769.311 Revision: 1 Page B-12 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
95000 96000 97000 98000 99000 95000 96000 97000 98000 99000 1.15e+001 1.15e+001 1.15e+001 1.15e+001 1.15e+001
(
C C
C C
100000 100000 1.
101000 1010001.
102000 102000 1.
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113000 1130001.
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115000 1150001.
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117000 117000 1.
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126000 126000 1.
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128000 128000 1.
129000 129000 1.
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132000 132000 1.
133000 133000 1.
134000 134000 1.
135000 135000 1.
136000 136000 1.
137000 137000 1.
138000 138000 1.
139000 139000 1.
File No.: 0800769.311 Revision: 1 15e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 16e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 17e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 18e+001 19e+001 19e+001 19e+001
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) 1.18e+001 S1. 19e+001 S1. 19e+001 S1. 19e+001 1.00 4.88e-007 9.75e-006 0.5522 0.34 1.00 4.89e-007 9.77e-006 0.5527 0.34 1.00 4.90e-007 9.79e-006 0.5532 0.34
).00 4.9le-007 9.8le-006 0.5537 0.34
).00 4.92e-007 9.84e-006 0.5542 0.34 0.00 4.93e-007 9.86e-006 0.5547 0.34 0.00 4.94e-007 9.88e-006 0.5552 0.34 0.00 4.95e-007 9.90e-006 0.5557 0.34 0.00 4.96e-007 9.92e-006 0.5561 0.34 0.00 4.97e-007 9.94e-006 0.5566 0.34 0.00 4.98e-007 9.96e-006 0.5571 0.34 0.00 4.99e-007 9.98e-006 0.5576 0.34 0.00 5.00e-007 0.00 5.0le-007 0.00 5.02e-007 0.00 5.03e-007 0.00 5.04e-007 0.00 5.05e-007 0.00 5.06e-007 0.00 5.08e-007 0.00 5.09e-007 0.00 5.10e-007 0.00 5.11e-007 0.00 5.12e-007 0.00 5.13e-007 0.00 5.14e-007 0.00 5.15e-007 0.00 5.16e-007 0.00 5.17e-007 0.00 5.19e-007 0.00 5.20e-007 0.00 5.21 e-007 0.00 5.22e-007 0.00 5.23e-007 0.00 5.24e-007 0.00 5.25e-007 0.00 5.27e-007 0.00 5.28e-007 0.00 5.29e-007 0.00 5.30e-007 0.00 5.3 1e-007 0.00 5.32e-007 0.00 5.34e-007 0.00 5.35e-007 0.00 5.36e-007 1.00e-005 0.5581 0.34 1.00e-005 0.5586 0.34 1.00e-005 0.5591 0.34 1.01e-005 0.5596 0.34 1.Ole-005 0.5602 0.34 1.Ole-005 0.5607 0.34 1.Ole-005 0.5612 0.34 1.02e-005 0.5617 0.34 1.02e-005 0.5622 0.35 1.02e-005 0.5627 0.35 1.02e-005 0.5632 0.35 1.02e-005 0.5637 0.35 1.03e-005 0.5642 0.35 1.03e-005 0.5647 0.35 1.03e-005 0.5652 0.35 1.03e-005 0.5658 0.35 1.03e-005 0.5663 0.35 1.04e-005 0.5668 0.35 1.04e-005 0.5673 0.35 1.04e-005 0.5678 0.35 1.04e-005 0.5684 0.35 1.05e-005 0.5689 0.35 1.05e-005 0.5694 0.35 1.05e-005 0.5699 0.35 1.05e-005 0.5705 0.35 1.06e-005 0.571 0.35 1.06e-005 0.5715 0.35 1.06e-005 0.572 0.35 1.06e-005 0.5726 0.35 1.06e-005 0.5731 0.35 1.07e-005 0.5736 0.35 1.07e-005 0.5742 0.35 1.07e-005 0.5747 0.35 Page B-13 of B-51 F0306-01 RO
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140000 141000 142000 143000 144000 145000 146000 147000 148000 149000 150000 151000 152000 153000 154000 155000 156000 157000 158000 159000 160000 161000 162000 163000 164000 165000 166000 167000 168000 169000 170000 171000 172000 173000 174000 175000 175200 140000 141000 142000 143000 144000 145000 146000 147000 148000 149000 150000 151000 152000 153000 154000 155OO0 156000 157000 158000 159000 160000 161000 162000 163000 164000 165000 166000 167000 168000 169000 170000 171000 172000 173000 174000 175000 175200 1.19e+001 0.00e+000 1.19e+001 1.19e+001 0.00e+000 1.19e+001 1.19e+001 0.00e+000 1.19e+001 0.00e+000 1.19e+001 0.00e+000 1.19e+001 0.00e+000 1.19e+001 0.00e+000 1.19e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.20e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.21e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 1.22e+001 0.00e+000 End of pc-CRACK Oul 1.19e+001 1.19e+001 1.19e+001 1.19e+001 1.19e+001 1.19e+001 0.00 5.37e-007 1.07e-005 0.00 5.38e-007 1.08e-005 0.00 5.39e-007 1.08e-005 0.00 5.41e-007 1.08e-005 0.00 5.42e-007 1.08e-005 0.00 5.43e-007 1.09e-005 0.00 5.44e-007 1.09e-005 0.00 5.46e-007 1.09e-005 0.5752 0.35 0.5758 0.35 0.5763 0.35 0.5769 0.35 0.5774 0.35 0.5779 0.35 0.5785 0.36 0.579 0.36 1.20e+001 0.00 5.47e-007 1.09e-005 0.5796 0.36 1.20e+001 0.00 5.48e-007 1.1Oe-005 0.5801 0.36 1.20e+001 0.00 5.49e-007 1.10e-005 0.5807 0.36 1.20e+001 0.00 5.50e-007 1.10e-005 0.5812 0.36 1.20e+001 0.00 5.52e-007 1.10e-005 0.5818 0.36 1.20e+001 0.00 5.53e-007 1.1 e-005 0.5823 0.36 1.20e+001 0.00 5.54e-007 1.lie-005 0.5829 0.36 1.20e+001 0.00 5.55e-007 1.20e+001 0.00 5.57e-007 1.20e+001 0.00 5.58e-007 1.20e+001 0.00 5.59e-007 1.21e+001 0.00 5.61e-007 1.21e+001 0.00 5.62e-007 1.21e+001 0.00 5.63e-007 1.21e+001 0.00 5.64e-007 1.21e+001 0.00 5.66e-007 1.21e+001 0.00 5.67e-007 1.21e+001 0.00 5.68e-007 1.21e+001 0.00 5.70e-007 1.21e+001 0.00 5.71e-007 1.21e+001 0.00 5.72e-007 1.21e+001 0.00 5.74e-007 1.22e+001 0.00 5.75e-007 1.22e+001 0.00 5.76e-007 1.22e+001 0.00 5.78e-007 1.22e+001 0.00 5.79e-007 1.22e+001 0.00 5.80e-007 1.lie-005 0.5834 0.36 1.1le-005 0.584 0.36 1.12e-005 0.5846 0.36 1.12e-005 0.5851 0.36 1.12e-005 0.5857 0.36 1.12e-005 0.5862 0.36 1.13e-005 0.5868 0.36 1.13e-005 0.5874 0.36 1.13e-005 0.5879 0.36 1.13e-005 0.5885 0.36 1.14e-005 0.5891 0.36 1.14e-005 0.5896 0.36 1.14e-005 0.5902 0.36 1.14e-005 0.5908 0.36 1.15e-005 0.5913 0.36 1.15e-005 0.5919 0.36 1.15e-005 0.5925 0.36 1.16e-005 0.5931 0.36 1.16e-005 0.5936 0.36 1.16e-005 0.5942 0.36 1.22e+001 0.00 5.82e-007 1.16e-005 0.5948 0.37 1.22e+001 0.00 5.82e-007 1.16e-005 0.5949 0.37 File No.: 0800769.311 Revision: 1 Page B-14 of BL51 F0306-01 RO
Structural Integrity Associates, Inc.
Output for FCG case without residual stresses:
tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax:
408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Mon Dec 01 15:14:06 2008 Input Data and Results File: N2.LFM
Title:
JAF N2 Crack Growth Without Residual Stresses Load Cases:
Case ID: Plrsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000
-39.7170 0.0793
-40.3490 0.1587
-40.7120 0.2380
-40.9920 0.3173
-40.0580 0.3967
-36.4000 0.4760
-30.3220 0.5553
-22.7690 0.6347
-12.5050 0.7140
-1.5176 0.7933 3.8362 0.8727 6.5966 0.9520 8.8339 1.0313 10.6030 1.1107 11.4380 1.1900 11.8810 1.2693 13.8740 File No.: 0800769.311 Revision: 1 Page B-15 of B-51 F0306-01 RO
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1.3487 1.4280 1.5073 1.5867 17.0970 18.6230 18.0990 15.5500 Case ID: P2_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584 0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-40.6750
-38.7950
-36.3090
-35.6780
-38.8330
-33.5040
-39.3260
-36.5530
-21.1880
-4.6270 9.1298 15.3010 16.8200 16.7900 15.8530 14.3480 15.4520 20.0010 24.3720 27.8520 29.3440 Case ID: P3_rsdl_70Fhoop --- Stress Distribution Depth Stress 0,0000 0,0853 0,1707 0,2560 0,3413 0,4266 0,5120 0,5973 0,6826 0,7679
-38.4610
-39.5790
-49.1040
-51.6050
-51.2820
-47.4160
-41.6810
-32.7260
-20.8590
-9.6705 File No.: 0800769.311 Revision: 1 Page B-16 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-0.2673 7.0081 8.3770 9.4758 9.1873 9.0162 11.2680 15.8210 18.7370 21.4980 23.6410 Case ID: Plrsdl_551Fhoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693 1.3487 1.4280 1.5073 1.5867
-26.5210
-26.9270
-26.9240
-26.3780
-24.6910
-20.6710
-14.6190
-7.2662 2.3816 12.6720 17.6200 20.1090 22.0400 23.5030 22.1790 20.0260 17.4550 20.1960 21.3010 20.4310 17.8390 Case ID: P2_rsdl_55 1F_hoop --- Stress Distribution Depth Stress 0.0000
-32.6410 0.0792
-30.4050 0.1584
-26.2400 File No.: 0800769.311 Revision: 1 Page B-17 of B-51 F0306-01 RO
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0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-23.6480
-25.6030
-20.0130
-25.0810
-22.2480
-7.8169 7.6241 20.3840 26.0170 27.2700 27.0450 24.8660 20.2130 16.8180 20.8460 24.6800 27.6550 28.8950 Case ID: P3_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0853 0.1707 0.2560 0.3413 0.4266 0.5120 0.5973 0.6826 0.7679 0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-29.0710
-31.1390
-37.1380
-38.5510
-37.6290
-34.0970
-29.0900
-20.9770
-10.0800 0.1012 8.4945 14.8890 15.7350 16.1220 13.6400 11.2460 8.7844 12.6900 15.0840 17.3120 19.0350 File No.: 0800769.311 Revision: 1 Page B-18 of B-51 F0306-01 RO
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Stress Coefficients CO Case ID Cl C2 C3 Type P1 rsdl 70F hoo P2 rsdl 70F hoo P3 rsdl 70F hoo P1 rsdl 551F ho P2 rsdl 551F ho P3_rsdl_551F ho primary hoop st
-42.6891
-39.4702
-42.8367
-30.5175
-32.6415
-34.3878 7.371
-7.07378
-30.1753
-48.9998 11.0008 1.43969
-24.6287 0
115.185 145.503 154.565 90.953 105.477 118.724 0
0
-56.0956
-64.3057
-62.0792
-50.9343
-53.8
-52.269 Coeff StressDist StressDist StressDist StressDist StressDist StressDist Through Wall Stresses for Load Cases With Stress Coeff-------
Wall Case Depth primary ho 0.0000 0.1220 0.2440 0.3660 0.4880 0.6100 0.7320 0.8540 0.9760 1.0980 1.2200 7.371 7.371 7.371.
7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 Crack Model: Elliptical Longitudinal Crack in Cylinder (t/R=0. 1,a/l=0. 1)
WARNING: The stress intensity factor (K) is the maximum of K at the surface and K at the deepest point at each crack depth.
Crack Parameters:
Wall thickness:
Max. crack size:
1.6288 1.2200
Stress Intensity Factor --------------------
Crack Case Case Case Case Size P1_rsdl_70 P2_rsdl_70 P3_rsdl_70 P1_rsdl_55 Case P2_rsdl_55 File No.: 0800769.311 Revision: 1 Page B-19 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
0.0244
-6.71806 0.0488
-9.48828 0.0732
-11.6043.
0.0976
-13.3793 0.1220
-14.9344 0.1464
-16.3317 0.1708
-17.6407 0.1952
-18.9295 0.2196
-20.1503 0.2440
-21.3137 0.2684
-22.4279 0.2928
-23.4987 0.3172
-24.5309 0.3416
-25.6197 0.3660
-26.7332 0.3904
-27.8254 0.4148
-28.8976 0.4392
-29.9508 0.4636
-30.9857 0.4880
-32.0029 0.5124
-33.1651 0.5368
-34.3204 0.5612
-35.4642 0.5856
-36.5961 0.6100
-37.7156 0.6344
-38.8222 0.6588
-39.9702 0.6832
-41.236 0.7076
-42.4914 0.7320
-43.7352 0.7564
-44.9667 0.7808
-46.1849 0.8052
-47.3889 0.8296
-48.6983 0.8540
-50.0665 0.8784
-51.4199 0.9028
-52.7572 0.9272
-53.1925 0.9516
-52.6735 0.9760
-52.0769 1.0004
-51.6976 1.0248
-51.2794 1.0492
-50.8105 1.0736
-50.295 1.0980
-49.7375 File No.: 0800769.311 Revision: 1
-6.22218
-8.80282
-10.784
-12.4539
-13.9239
-15.2508
-16.4992
-17.7332
-18.907
-20.0303
-21.1103
-22.1523
-23.1605
-24.2264
-25.3196
-26.3954
-27.455
-28.4989
-29.5277
-30.5417
-31.7001
-32.8544
-34
-35.1362
-36.2624
-37.3778
-38.536
-39.813
-41.0815
-42.3404
-43.5886
-44.8248
-46.048
-47.3774
-48.7665
-50.1416
-51.5014
-52.8443
-53.0186
-52.2251
-51.6365
-50.9895
-50.2715
-49.4867
-48.6393
'-6.76032
-9.57471
-11.7426
-13.5761
-15.1956
-16.6625
-18.0472
-19.4205
-20.7315
-21.9907
-23.2059
-24.3829
-25.5263
-26.7386
-27.9863
-29.2194
-30.439
-31.6459
-32.8407
-34.0238
-35.3773
-36.7324
-38.0839
-39.4311
-40.7733
-42.1099
-43.5031
-45.0418
-46.579
-48.1134
-49.6438
-51.1689
-52.6876
-54.3414
-56.0763
-57.8054
-59.527
-61.2397
-62.942
-64.6325
-66.5355
-68.4384
-70.3271
-72.1998
-74.0551
-4.79525
-6.76207
-8.25709
-9.50485
-10.5924
-11.5643
-12.4699
-13.3569
-14.1919
-14.9827
-15.735
-16.4531
-17.1404
-17.8612
-18.5937
-19.3064
-20.0001
-20.6755
-21.333
-21.973
-22.7021
-23.4195
-24.1222
-24.8097
-25.4817
-26.1377
-26.812
-26.6359
-26.054
-25.3891
-24.6421
-23.8134
-22.9039
-21.974
-21.0074
-19.9712
-18.8676
-17.6986
-16.4669
-15.1748
-14.0253
-12.847
-11.6338
-10.3904
-9.12204
-5.13368
-7.24594
-8.85602
-10.2036
-11.3814
-12.4371
-13.4234
-14.392
-15.3066
-16.1754
-17.0044
-17.7981
-18.5602
-19.3613
-20.1775
-20.9742
-21.7524
-22.5126
-23.2553
-23.9809
-24.808
-25.6248
-26.4279
-27.2167
-27.9908
-28.7496
-29.5319
-30.3916
-31.2364
-31.7379
-31.0844
-30.3369
-29.4957
-28.6297
-27.719
-26.7251
-25.6496
-24.4942
-23.261
-21.952
-20.7907
-19.5863
-18.331
-17.0293
-15.6858 Page B-20 of B-51 F0306-OI RO
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1.1224 1.1468 1.1712 1.1956 1.2200
-49.1428
-48.5185
-47.8864
-47.2532
-46.6274
-47.7339
-46.7905
-45.8538
-44.8991
-43.935
-75.8777
-75.5827
-75.2889
-74.9613
-74.6071
-7.83391
-6.53329
-5.23966
-3.96252
-2.71053
-14.3055
-12.8971
-11.4835
-10.0689
-8.66168 Stress Intensity Factor, Crack Case Case Size P3_rsdl_55 primary ho 0.0244
-5.42025 0.0488
-7.6673 0.0732
-9.39176 0.0976
-10.8449 0.1220
-12.1237 0.1464
-13.2777 0.1708
-14.3633 0.1952
-15.4364 0.2196
-16.4569 0.2440
-17.4335 0.2684
-18.3725 0.2928
-19.2785 0.3172
-20.1552 0.3416
-21.0823 0.3660
-22.0333 0.3904
-22.9696 0.4148
-23.8919 0.4392
-24.8009 0.4636
-25.6973 0.4880
-26.5812 0.5124
-27.5913 0.5368
-28.5985 0.5612
-29.5988 0.5856
-30.5916 0.6100
-31.5764 0.6344
-32.5526 0.6588
-33.5671 0.6832
-34.6861 0.7076
-35.7989 0.7320
-36.9044 0.7564
-38.0017
'0.7808
-39.0899 0.8052
-40.1681 0.8296
-41.3407 File No.: 0800769;311 Revision: 1 1.92366 2.74502 3.39203 3.9515 4.45674 4.92465 5.36888 5.80088 6.21779 6.62266 7.0178 7.40494 7.78545 8.17085 8.55815 8.94264 9.32488 9.70534 10.0844 10.4625 10.859 11.2565 11.6547 12.0536 12.4535 12.8544 13.2633 13.6898 14.1185 14.5494 14.9826 15.4181 15.856 16.3116 Page B-21 of B-51 F0306-01 RO
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0.8540 0.8784 0.9028 0.9272 0.9516 0.9760 1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-42.5671
-43.7829
-44.9871
-46.1785
-47.3561
-48.1482
-47.8113
-47.4277
-46.9864
-46.4907
-45.944
-45.3499
-44.7235
-44.099
-43.4594
-42.8116 16.7796 17.2508 17.7251 18.2026 18.6832 19.167 19.6987 20.2373 20.7801 21.3272 21.8785 22.4339 22.9901 23.5412 24.0961 24.6548 Crack Growth Laws:
Law ID: Fatigue_551 Model: ASME Section XI - austenitic stainless steel in air environment da/dN = C
- IOAF
- S
- dKA3.3 where S
1.0 for R< 0
=1.0+ 1.8*R for 0 < R< 0.79
=-43.5 +57.97 *R for 0.79<R< 1 F = code specified function of temperature dK = Kmax - Kmin R = Kmin / Kmax where:
C
- 1OAF = 1.8424e-010 is for the currently selected units of:
force: kip length: inch temperature:
551.0000 Fahrenheit Material Fracture Toughness KIc:
Material ID: Alloy 82/182 File No.: 0800769.311 Revision: 1 Page B-22 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
Depth KIc 0.0000 0.7500 1.5000 63.2500 63.2500 63.2500 Material ID: high toughness Depth KIc 0.0000 0.7500 1.5000 200.0000 200.0000 200.0000 Initial crack size=
Max. crack size=
0.5100 1.2200 Number of blocks=
1 Print increment of block=
1
. Cycles Calc. Print Subblock
/Time incre. incre.
Crk. Grw.
Law Mat.
Klc growth 10000 10 100 Fatigue_551 Alloy 82/182 Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor growth primary hoop stress 1.0000 Crack growth results:
Total Subblock Cycles Cycles
/Time
/Time Kmax Kmin DaDn DeltaK R
/DaDt Da a
a/thk Block:
1 100 100 1.08e+001 0.00e+000 1.08e+001 0.00 4.77e-007 4.77e-006 0.51 0.31 200 200 1.08e+001 0.00e+000 1.08e+001 0.00 4.77e-007 4.77e-006 0.5101 0.31 300 300 1.08e+001 0.00e+000 1.08e+001 0.00 4.77e-007 4.77e-006 0.5101,0.31 400 400 1.08e+001 0.00e+000 1.08e+001 0.00 4.77e-007 4.77e-006 0.5102 0.31 File No.: 0800769.311 Revision: 1 Page B-23 of B-51 F0306-01 RO
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500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 500 600 700 800 900 1.08e+001 0.00e+000 1.08e+001 1.08e+001 0.00e+000 1.08e+001 1.08e+001 0.00e+000 1.08e+001 1.08e+001 0.00e+000 1.08e+001 1.08e+001 0.00e+000 1.08e+001 0.00 4.77e-007 4.77e-006 0.5102 0.31 0.00 4.77e-007 4.77e-006 0.5103 0.31 0.00 4.78e-007 4.78e-006 0.5103 0.31 0.00 4.78e-007 4.78e-006 0.5104 0.31 0.00 4.78e-007 4.78e-006 0.5104 0.31 1000 1.08e+001 1100 1.08e+001 1200 1.08e+001 1300 1.08e+001 1400 1.08e+001 1500 1.08e+001 1600 1.08e+001 1700 1.08e+001 1800 1.08e+001 1900 1.08e+001 2000 1.08e+001 2100 1.08e+001 2200 1.08e+001 2300 1.08e+001 2400 1.08e+001 2500 1.08e+001 2600 1.08e+001 2700 1.08e+001 2800 1.08e+001 2900 1.08e+001 0.00e+000 1.08e+001 0.00 4.78e-007 4.78e-006 0.5105 0.31 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 0.00e+000 1.08e+001 0.00 4.78e-007 4.78e-006 0.5105 0.31 1.08e+001 0.00 4.78e-007 4.78e-006 0.5106 0.31 1.08e+001 0.00 4.78e-007 4.78e-006 0.5106 0.31 1.08e+001 0.00 4.78e-007 4.78e-006 0.5107 0.31 1.08e+001 0.00 4.78e-007 4.78e-006 0.5107 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.5108 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.5108 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.5109 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.5109 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.511 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.511 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.511 0.31 1.08e+001 0.00 4.79e-007 4.79e-006 0.5111 0.31 1.08e+001 1.08e+001 1.08e+001 1.08e+001 1.08e+001 1.08e+001 3000 1.08e+001 0.00e+000 1.08e+001 3100 1.08e+001 0.00e+000 1.08e+001 3200 1.08e+001 0.00e+000 1.08e+001 3300 1.08e+001 0.00e+000 1.08e+001 3400 1.08e+001 0.00e+000 1.08e+001 3500 1.08e+001 0.00e+000 1.08e+001 3600 1.08e+001 0.00e+000 1.08e+001 3700 1.08e+001 0.00e+000 1.08e+001 3800 1.08e+001 0.00e+000 1.08e+001 3900 1.09e+001 0.00e+000 1.09e+001 4000 1.09e+001 0.00e+000 1.09e+001 4100 1.09e+001 0.00e+000 1.09e+001 4200 1.09e+001 0.00e+000 1.09e+001 4300 1.09e+001 0.00e+000 1.09e+001 4400 1.09e+001 0.00e+000 1.09e+001 4500 1.09e+001 0.00e+000 1.09e+001 4600 1.09e+001 0.00e+000 1.09e+001 4700 1.09e+001 0.00e+000 1.09e+001 4800 1.09e+001 0.00e+000 1.09e+001 0.00 4.80e-007 4.80e-006 0.5111 0.31 0.00 4.80e-007 4.80e-006 0.5112 0.31 0.00 4.80e-007 4.80e-006 0.5112 0.31 0.00 4.80e-007 4.80e-006 0.5113 0.31 0.00 4.80e-007 4.80e-006 0.5113 0.31 0.00 4.80e-007 4.80e-006 0.5114 0.31 0.00 4.80e-007 4.80e-006 0.5114 0.31 0.00 4.80e-007 4.80e-006 0.5115 0.31 0.00 4.80e-007 4.80e-006 0.5115 0.31 0.00 4.81e-007 4.81e-006 0.5116 0.31 0.00 4.81e-007 4.81e-006 0.5116 0.31 0.00 4.81e-007 4.81e-006 0.5117 0.31 0.00 4.81e-007 4.81e-006 0.5117 0.31 0.00 4.81e-007 4.81e-006 0.5118 0.31 0.00 4.81e-007 4.81e-006 0.5118 0.31 0.00 4.81e-007 4.81e-006 0.5119 0.31 0.00 4.81e-007 4.81e-006 0.5119 0.31 0.00 4.81e-007 4.81e-006 0.512 0.31 0.00 4.82e-007 4.82e-006 0.512 0.31 0.00 4.82e-007 4.82e-006 0.5121 0.31 0.00 4.82e-007 4.82e-006 0.5121 0.31 0.00 4.82e-007 4.82e-006 0.5122 0.31 0.00 4.82e-007 4.82e-006 0.5122 0.31 0.00 4.82e-007 4.82e-006 0.5123 0.31 0.00 4.82e-007 4.82e-006 0.5123 0.31 4900 4900 1.09e+001 0.00e+000 1.09e+001 0.00 4.82e-007 4.82e-006 0.5123 0.31 File No.: 0800769.311 Revision: 1 Page B-24 of B-51 F0306-01 RO
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5000 5000 1.09e+001 0.00e+000 1.09e+001 0.00 4.82e-007 4.82e-006 0.5124 0.31 5100 5100 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5124 0.31 5200 5200 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5125 0.31 5300 5300 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5125 0.31 5400 5400 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5126 0.31 5500 5500 1.09e+001 0.00e+000 1.09e+001 0.00 4*83e-007 4.83e-006 0.5126 0.31 5600 5600 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5127 0.31 5700 5700 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5127 0.31 5800 5800 1.09e+001 0.00e+000 1.09e+001 0.00 4.83e-007 4.83e-006 0.5128 0.31 5900 5900 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5128 0.31 6000 6000 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5129 0.31 6100 6100 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5129 0.31 6200 6200 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.513 0.31 6300 6300 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.513 0.31 6400 6400 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5131 0.32 6500 6500 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5131 0.32 6600 6600 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5132 0.32 6700 6700 1.09e+001 0.00e+000 1.09e+001 0.00 4.84e-007 4.84e-006 0.5132 0.32 6800 6800 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5133 0.32 6900 6900 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5133 0.32 7000 7000 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5134 0.32 7100 7100 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5134 0.32 7200 7200 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5135 0.32 7300 7300 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5135 0.32 7400 7400 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5136 0.32 7500 7500 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5136 0.32 7600 7600 1.09e+001 0.00e+000 1.09e+001 0.00 4.85e-007 4.85e-006 0.5137 0.32 7700 7700 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5137 0.32 7800 7800 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5137 0.32 7900 7900 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5138 0.32 8000 8000 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5138 0.32 8100 8100 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5139 0.32 8200 8200 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5139 0.32 8300 8300 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.514 0.32 8400 8400 1.09e+001 0.00e+000 1.09e+001 0.00 4.86e-007 4.86e-006 0.5140.32 8500 8500 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5141 0.32 8600 8600 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5141 0.32 8700 8700 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5142 0.32 8800 8800 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5142 0.32 8900 8900 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5143 0.32 9000 9000 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5143 0.32 9100 9100 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5144 0.32 9200 9200 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5144 0.32 9300 9300 1.09e+001 0.00e+000 1.09e+001 0.00 4.87e-007 4.87e-006 0.5145 0.32 9400 9400 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5145 0.32 File No.: 0800769.311 Page B-25 of B-51 Revision: 1 F0306-01 RO
V Structural Integrity Associates, Inc.
9500 9500 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5146 0.32 9600 9600 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5146 0.32 9700 9700 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5147 0.32 9800 9800 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5147 0.32 9900 9900 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5148 0.32 10000 10000 1.09e+001 0.00e+000 1.09e+001 0.00 4.88e-007 4.88e-006 0.5148 0.32 End of pc-CRACK Output File No.: 0800769.311 Revision: 1 Page B-26 of B-51 F0306-01 R0
Structural Integrity Associates, Inc.
Output for IGSCC case with WOL residual stresses:
tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax:
408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Mon Dec 01 14:53:25 2008 Input Data and Results File: N2.LFM
Title:
JAF N2 Crack Growth with WOL Load Cases:
Case ID: P1_rsdl_70F_hoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693
-39.7170
-40.3490
-40.7120
-40.9920
-40.0580
-36.4000
-30.3220
-22.7690
-12.5050
-1.5176 3.8362 6.5966 8.8339 10.6030 11.4380 11.8810 13.8740 File No.: 0800769.311 Revision: 1 Page B-27 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
1.3487 1.4280 1.5073 1.5867 17.0970 18.6230 18.0990 15.5500 Case ID: P2_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584 0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-40.6750
-38.7950
-36.3090
-35.6780
-38.8330
-33.5040
-39.3260
-36.5530
-21.1880
-4.6270 9.1298 15.3010 16.8200 16.7900 15.8530 14.3480 15.4520 20.0010 24.3720 27.8520 29.3440 Case ID: P3_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0853 0.1707 0.2560 0.3413 0.4266 0.5120 0.5973 0.6826 0.7679
-38.4610
-39:5790
-49.1040
-51.6050
-51.2820
-47.4160
-41.6810
-32.7260
-20.8590
-9.6705 File No.: 0800769.311 Revision: 1 Page B-28 of B-51 F0306-OI RO
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0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-0.2673 7.0081 8.3770 9.4758 9.1873 9.0162 11.2680 15.8210 18.7370 21.4980 23.6410 Case ID: P l rsdl_551 F_hoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693 1.3487 1.4280 1.5073 1.5867
-26.5210
-26.9270
-26.9240
-26.3780
-24.6910
-20.6710
-14.6190
-7.2662 2.3816 12.6720 17.6200 20.1090 22.0400 23.5030 22.1790 20.0260 17.4550 20.1960 21.3010 20.4310 17.8390 Case ID: P2_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584
-32.6410
-30.4050
-26.2400 FilleNo.: 0800769.311 Revision: 1 Page B-29 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.6295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-23.6480
-25.6030
-20.0130
-25.0810
-22.2480
-7.8169 7.6241 20.3840 26.0170 27.2700 27.0450 24.8660 20.2130 16.8180 20.8460 24.6800 27.6550 28.8950 Case ID: P3_rsdl_551Fhoop --- Stress Distribution Depth Stress 0.0000 0.0853 0.1707 0.2560 0.3413 0.4266 0.5120 0.5973 0.6826 0.7679 0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-29.0710
-31.1390
-37.1380
-38.5510
-37.6290
-34.0970
-29.0900
-20.9770
-10.0800 0.1012 8.4945 14.8890 15.7350 16.1220 13.6400 11.2460 8.7844 12.6900 15.0840 17.3120 19.0350 File No.: 0800769.311 Revision: 1 Page B-30 of B-51 F0306-01 RO
V Structural Integrity Associates,, Inc.
Stress Coefficients CO Case ID C1 C2 C3 Type P1 rsdl 70F hoo P2 rsdl 70F hoo P3 rsdl 70F hoo P1 rsdl 551F ho P2 rsdl 551F-ho P3 rsdl 551F ho primary hoop st
-42.6891
-39.4702
-42.8367
-30.5175
-32.6415
-34.3878 7.371
-7.07378
-30.1753
-48.9998 11.0008 1.43969
-24.6287 0
115.185 145.503 154.565 90.953 105.477 118.724 0
-56.0956
-64.3057
-62.0792
-50.9343
-53.8
-52.269 0
StressDist StressDist StressDist StressDist StressDist StressDist Coeff r-Through Wall Stresses for Load Cases Wall Case Depth primary ho With Stress Coeff-------
0.0000 0.1220 0.2440 0.3660 0.4880 0.6100 0.7320 0.8540 0.9760 1.0980 1.2200 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 Crack Model: Elliptical Longitudinal Crack in Cylinder (t/R=0.1,a/l=0. 1)
WARNING: The stress intensity factor (K) is the maximum of K at the surface and K at the deepest point at each crack depth.
Crack Parameters:
Wall thickness:
Max. crack size:
1.6288 1.2200 File No.: 0800769.311 Revision: 1 Page B-31 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
Stress Intensity Factor --------------------
Crack Case Case Case Case Case Size P1_rsdl_70 P2_rsdl_70 P3_rsdl_70 P1_rsdl_55 P2_rsdl_55 0.0244
-6.71806 0.0488
-9.48828 0.0732
-11.6043 0.0976
-13.3793 0.1220
-14.9344 0.1464
-16.3317 0.1708
-17.6407 0.1952
-18.9295 0.2196
-20.1503 0.2440
-21.3137 0.2684
-22.4279 0.2928
-23.4987 0.3172
-24.5309 0.3416
-25.6197 0.3660
-26.7332 0.3904
-27.8254 0.4148
-28.8976 0.4392
-29.9508 0.4636
-30.9857 0.4880
-32.0029 0.5124
-33.1651 0.5368
-34.3204 0.5612
-35.4642 0.5856
-36.5961 0.6100
-37.7156 0.6344
-38.8222 0.6588
-39.9702 0.6832
-41.236 0.7076
-42.4914 0.7320
-43.7352 0.7564
-44.9667 0.7808
-46.1849 0.8052
-47.3889 0.8296
-48.6983 0.8540
-50.0665 0.8784
-51.4199 0.9028
-52.7572 0.9272
-53.1925 0.9516
-52.6735 0.9760
-52.0769 File No.: 0800769.311 Revision: 1
-6.22218
-8.80282
-10.784
-12.4539
-13.9239
-15.2508
-16.4992
-17.7332
-18.907
-20.0303
-21.1103
-22.1523
-23.1605
-24.2264
-25.3196
-26.3954
-27.455
-28.4989
-29.5277
-30.5417
-31.7001
-32.8544
-34.0000
-35.1362
-36.2624
-37.3778
-38.536
-39.813
-41.0815
-42.3404
-43.5886
-44.8248
-46.048
-47.3774
-48.7665
-50.1416
-51.5014
-52.8443
-53.0186
-52.2251
-6.76032
-9.57471
-11.7426
-13.5761
-15.1956
-16.6625
-18.0472
-19.4205
-20.7315
-21.9907
-23.2059
-24.3829
-25.5263
-26.7386
-27.9863
-29.2194
-30.439
-31.6459
-32.8407
-34.0238
-35.3773
-36.7324
-38.0839
-39.4311
-40.7733
-42.1099
-43.5031
-45.0418
-46.579
-48.1134
-49.6438
-51.1689
-52.6876
-54.3414
-56.0763
-57.8054
-59.527
-61.2397
-62.942
-64.6325
-4.79525
-6.76207
-8.25709
-9.50485
-10.5924
-11.5643
-12.4699
-13.3569
-14.1919
-14.9827
-15.735
-16.4531
-17.1404
-17.8612
-18.5937
-19.3064
-20.0001
-20.6755
-21.333
-21.973
-22.7021
-23.4195
-24.1222
-24.8097
-25.4817
-26.1377
-26.812
-26.6359
-26.054
-25.3891
-24.6421
-23.8134
-22.9039
-21.974
-21.0074
-19.9712
-18.8676
-17.6986
-16.4669
-15.1748
-5.13368
-7.24594
-8.85602
-10.2036
-11.3814
-12.4371
-13.4234
-14.392
-15.3066
-16.1754
-17.0044
-17.7981
-18.5602
-19.3613
-20.1775
-20.9742
-21.7524
-22.5126
-23.2553
-23.9809
-24.808
-25.6248
-26.4279
-27.2167
-27.9908
-28.7496
-29.5319
-30.3916
-31.2364
-31.7379
-31.0844
-30.3369
-29.4957
-28.6297
-27.719
-26.7251
-25.6496
-24.4942
-23.261
-21.952 Page B-32 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-51.6976
-51.2794
-50.8105
-50.295
-49.7375
-49.1428
-48.5185
-47.8864
-47.2532
-46.6274
-51.6365
-50.9895
-50.2715
-49.4867
-48.6393
-47.7339
-46.7905
-45.8538
-44.8991
-43.935
-66.5355
-68.4384
-70.3271
-72.1998
-74.0551
-75.8777
-75.5827
-75.2889
-74.9613
-74.6071
-14.0253
-12.847
-11.6338
-10.3904
-9.12204
-7.83391
-6.53329
-5.23966
-3.96252
-2.71053
-20.7907
-19.5863
-18.331
-17.0293
-15.6858
-14.3055
-12.8971
-11.4835
-10.0689
-8.66168 Stress Intensity Factor--.............
Crack Case Case Size P3_rsdl_55 primary ho 0.0244
-5.42025 0.0488
-7.6673 0.0732
-9.39176 0.0976
-10.8449 0.1220
-12.1237 0.1464
-13.2777 0.1708
-14.3633 0.1952
-15.4364 0.2196
-16.4569 0.2440
-17.4335 0.2684
-18.3725 0.2928
-19.2785 0.3172
-20.1552 0.3416
-21.0823 0.3660
-22.0333 0.3904
-22.9696 0.4148
-23.8919 0.4392
-24.8009 0.4636
-25.6973 0.4880
-26.5812 0.5124
-27.5913 0.5368
-28.5985 0.5612
-29.5988 0.5856
-30.5916 0.6100
-31.5764 0.6344
-32.5526 0.6588
-33.5671 0.6832
-34.6861 0.7076
-35.7989 File No.: 0800769.311 Revision: 1 1.92366 2.74502 3.39203 3.9515 4.45674 4.92465 5.36888 5.80088 6.21779 6.62266 7.0178 7.40494 7.78545 8.17085 8.55815 8.94264 9.32488 9.70534 10.0844 10.4625 10.859 11.2565 11.6547 12.0536 12.4535 12.8544 13.2633 13.6898 14.1185 Page B-33 of B-51 FO0306-01 RU
VStructural Integrity Associates, Inc.
0.7320 0.7564 0.7808 0.8052 0.8296 0.8540 0.8784 0.9028 0.9272 0.9516 0.9760 1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-36.9044
-38.0017
-39.0899
-40.1681
-41.3407
-42.5671
-43.7829
-44.9871
-46.1785
-47.3561
-48.1482
-47.8113
-47.4277
-46.9864
-46.4907
-45.944
-45.3499
-44.7235
-44.099
-43.4594
-42.8116 14.5494 14.9826 15.4181 15.856 16.3116 16.7796 17.2508 17.7251 18.2026 18.6832 19.167 19.6987 20.2373 20.7801 21.3272 21.8785 22.4339 22.9901 23.5412 24.0961 24.6548 Crack Growth Laws:
Law ID: IGSCCHWC Type: Corrosion Model: Paris da/dN = c * (dK)^n where dK = Kmax - Kmin dK > Kthres Kmax < Klc Material parameters:
c = 3.2000e-010 n =
3.0000 Kthres=
0.0000 Material Fracture Toughness KMc:
Material ID: Alloy 82/182 File No.: 0800769.311 Revision: 1 Page B-34 of B-51 F0306-01 RO
Structural Integrity Associates, Inc.
Depth KIc 0.0000 0.7500 1.5000 63.2500 63.2500 63.2500 Material ID: high toughness Depth KIc 0.0000 0.7500 1.5000 200.0000 200.0000 200.0000 Initial crack size=
Max. crack size=
0.5100 1.2200 Number of blocks=
Print increment of block=
1 1
Cycles Calc. Print Crk. Grw.
Subblock
/Time incre. incre.
Law Mat.
Klc growth 175200 100 1000 IGSCCHWC Alloy 82/182 Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor growth primary hoop stress Plrsdl_551 F-hoop 1.0000 1.0000 Crack growth results:
Total Subblock Cycles Cycles
/Time /Time DaDn Kmax Kmin DeltaK R
/DaDt Da a a/thk Block:
1 1000 1000-1.18e+001 2000 2000 -1.18e+001 3000 3000-1.18e+001 0.00e+000 -1.18e+00l 0.00 0.00e+000 0.00e+000 0.51 0.31 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.51 0.31 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.51 0.31 File No.: 0800769.311 Revision: 1 Page B-35 of B-51 F0306-01 R0
V Structural Integrity Associates, Inc.
4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 21000 22000 23000 24000 25000 26000 4000 -1.18e+001 5000 -1.18e+001 6000 -1.18e+001 7000 -1.18e+001 8000 -1.18e+001 9000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.1 8e+00 1 CC C
(
C C
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).00 0.OOe+000 0.OOe+000
).00 0.OOe+000 0.OOe+000
).00 0.00e+000 0.00e+000
).00 0.00e+000 0.00e+000
).00 0.OOe+000 0.OOe+000
).00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51.0.31 0.51 0.31 0.51 0.31 0.51 0.31 24000 -1.18e+001 0.00e+000 -1.1 8e+001 0.00 0.00e+000 0.00e+000 25000 -1.18e+001 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 26000 -1.18e+001 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 27000 27000 -1.18e+/-001 28000 28000 -1.18e+001 29000 29000 -1.18e+001 30000 30000 -1.18e+001 31000 31000 -1.18e+001 32000 32000 -1.18e+001 33000 33000 -1.18e+001 34000 34000 -1.18e+001 35000 35000-1.18e+001 36000 36000 -1.18e+001 37000 37000 -1.18e+001 38000 38000 -1.18e+001 39000 39000 -1.18e+001 40000 40000 -1.18e+001 41000 41000 -1.18e+001 42000 42000 -1.18e+001 43000 43000 -1.18e+001 44000 44000 -1.18e+001 45000 45000 -1.18e+001 46000 46000 -1.18e+001 47000 47000 -1.18e+001 48000 48000 -1.18e+001 File No.: 0800769.311 Revision: 1 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31) 0.51 0.31 0.51 0.31 0.51 0.31 0.51 0.31 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00 0.ooe+000 0.ooe+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 0.00 0.00e+000 0.00e+000 Page B-36 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
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-1.18e+001
-1.18e+001
-1.18e+001
-1. 18e+001
-1.18e+001
-1. 18e+001
-1.18e+001
-1.18e+001 90000 -1.18e+001 91000 -1.18e+001 92000 -1.18e+001 93000 -1.18e+001 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.51 0.31 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.51 0.31 File No.: 0800769.311 Revision: 1 Page B-37 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
94000 95000 96000 97000 98000 99000 100000 101000 102000 103000 104000 105000 106000 107000 108000 109000 110000 111000 112000 113000 114000 115000 116000 117000 118000 119000 120000 121000 122000 123000 124000 125000 126000 127000 128000 129000 130000 131000 132000 133000 134000 135000 136000 137000 138000 94000 -1.18e+001 0.00e+000 -1.18e+001 C 95000 -1.18e+001 0.00e+000 -1.18e+001 (
96000 -1.18e+001 0.00e+000 -1.18e+001 (
97000 -1.18e+001 0.00e+000 -1.18e+001 (
98000 -1.18e+001 0.00e+000 -1.18e+001 I 99000 -1.18e+001 0.00e+000 -1.18e+001 (
100000 -1.18e+001 0.00e+000 -1.18e+001 101000 -1.18e+001 0.00e+000-1.18e+001 102000 -1.18e+001 0.00e+000 -1.18e+001 103000 -1.18e+001 0.00e+000 -1.18e+001 104000 -1.18e+001 0.00e+000 -1.18e+001 105000 -1.18e+001 0.00e+000 -1.18e+001 106000 -1.18e+001 0.00e+000 -1.18e+001 107000 -1.18e+001 0.00e+000 -1.18e+001 108000 -1.18e+001 0.00e+000 -1.18e+001 109000 -1.18e+001 0.00e+000 -1.18e+001 110000 -1.18e+001 0.00e+000 -1.18e+001 111000-1.18e+/-001 0.00e+000-1.18e+001 112000 -1.18e+001 0.00e+000 -1.18e+001
).00 0.00e+000 0.00e+000 0.51 0.31
).00 0.00e+000 0.00e+000 0.51 0.31
).00 0.00e+000 0.00e+000 0.51 0.31
).00 0.00e+000 0.00e+000 0.51 0.31
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V Structural Integrity Associates, Inc.
139000 140000 141000 142000
- 143000, 144000 145000 146000 147000 148000 149000 150000 151000 152000 153000 154000 155000 156000 157000 158000 159000 160000 161000 162000 163000 164000 165000 166000 167000 168000 169000 170000 171000 172000 173000 174000 175000 175200 139000 -1.18e+001 140000 -1.18e+001 141000 -1.18e+001 142000 -1.18e+001 143000 -1.18e+001 144000 -1.18e+001 145000 -1.18e+001 146000 -1.18e+001 147000 -1.18e+001 148000 -1.18e+001 149000 -1.18e+001 150000 -1.18e+001 151000 -1.18e+001 152000 -1.18e+001 153000 -1.18e+001 154000 -1.18e+001 155000 -1.18e+001 156000 -1.18e+001 157000 -1.18e+001 158000 -1.18e+001 159000 -1.18e+001 160000 -1.18e+001 161000 -1.18e+001 162000 -1.18e+001 163000 -1.18e+001 164000 -1.18e+001 165000 -1.18e+001 166000 -1.18e+001 167000 -1.18e+001 168000 -1.18e+001 1.69000 -1.18e+001 170000 -1.18e+001 171000 -1.18e+001 172000 -1.18e+001 173000 -1.18e+001 174000 'l 18e+001
.175000 -1.18e+001 175200 -1.18e+001 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+/-000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000'-1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.06e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.00e+000 -1.18e+001 0.00 0.00e+000 0.00e+000 0.00e+000 -1.1 8e+00 1 0.00 0.00e+000 0.00e+000 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.51 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 0.31 End of pc-CRACK Output File No.: 0800769.311 Revision: 1 Page B-39 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
Output for FCG case with WOL residual stresses:
tm pc-CRACK for Windows
. Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.
3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax:
408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Mon Dec 01 15:01:52 2008 Input Data and Results File: N2.LFM
Title:
JAF N2 Crack Growth with WOL Load Cases:
Case ID: Plrsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693
-39.7170
-40.3490
-40.7120
-40.9920
-40.0580
-36.4000
-30.3220
-22.7690
-12.5050
-1.5176 3.8362 6.5966 8.8339 10.6030 11.4380 11.8810 13.8740 File No.: 0800769.311 Revision: 1 Page B-40 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
1.3487 1.4280 1.5073 1.5867 17.0970 18.6230 18.0990 15.5500 Case ID: P2_rsdl_70Fhoop --- Stress Distribution Depth Stress 0.0000 0.0792 0.1584 0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-40.6750
-38.7950
-36.3090
-35.6780
-38.8330
-33.5040
-39.3260
-36.5530
-21.1880
-4.6270 9.1298 15.3010 16.8200 16.7900 15.8530 14.3480 15.4520 20.0010 24.3720 27.8520 29.3440 Case ID: P3_rsdl_70F_hoop --- Stress Distribution Depth Stress 0.0000
-38.461(
0.0853
-39.579(
0.1707
-49.104(
0.2560
-51.605(
0.3413
-51.282(
0.4266
-47.416(
0.5120
-41.681(
0.5973
-32.726(
0.6826
-20.859(
0.7679
-9.6705 File No.: 0800769.311 Revision: 1
)
- )
)
)
Page B-41 of B-Si F0306-01 R0
Structural Integrity Associates, Inc.
0.8533 0.9386 1.0239 1.1093 1.1946 1.2799 1.3652 1.4506 1.5359 1.6212 1.7065
-0.2673 7.0081 8.3770 9.4758 9.1873 9.0162 11.2680 15.8210 18.7370 21.4980 23.6410 Case ID: P 1_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0793 0.1587 0.2380 0.3173 0.3967 0.4760 0.5553 0.6347 0.7140 0.7933 0.8727 0.9520 1.0313 1.1107 1.1900 1.2693 1.3487 1.4280 1.5073 1.5867
-26.5210
-26.9270
-26.9240
-26.3780
-24.6910
-20.6710
-14.6190
-7.2662 2.3816 12.6720 17.6200 20.1090 22.0400 23.5030 22.1790 20.0260 17.4550 20.1960 21.3010 20.4310 17.8390 Case ID: P2_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000
-32.6410 0.0792
-30.4050 0.1584
-26.2400 File No.: 0800769.311 Revision: 1 Page B-42 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
0.2376 0.3168 0.3960 0.4752 0.5544 0.6336 0.7128 0.7920 0.8712 0.9503 1.0295 1.1087 1.1879 1.2671 1.3463 1.4255 1.5047 1.5839
-23.6480
-25.6030
-20.0130
-25.0810
-22.2480
-7.8169 7.6241 20.3840 26.0170 27.2700 27.0450 24.8660 20.2130 16.8180 20.8460 24.6800 27.6550 28.8950 Case ID: P3_rsdl_551F_hoop --- Stress Distribution Depth Stress 0.0000 0.0853 0.1707 0.2560 0.3413 0,4266 0,5120 0,5973 0,6826 0,7679 0,8533 0,9386 1,0239 1,1093 1,1946 1,2799 1,3652 1,4506 1,5359 1,6212 1,7065
-29.0710
-31.1390
-37.1380
-38.5510
-37.6290
-34.0970
-29.0900
-20.9770
-10.0800 0.1012 8.4945 14.8890 15.7350 16.1220 13.6400 11.2460 8.7844 12.6900 15.0840 17.3120 19.0350 File No.: 0800769.311 Revision: 1 Page B-43 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
Stress Coefficients Cl C2 Case ID CO C3 Type P1 rsdl 70F hoo P2 rsdl 70F hoo P3-rsdt_70F-hoo P1 rsdl 551F ho P2 rsdl 551F ho P3 rsdl 551F ho primary hoop st
-42.6891
-39.4702
-42.8367
-30.5175
-32.6415
-34.3878 7.371
-7.07378
-30.1753
-48.9998 11.0008 1.43969
-24.6287 0
115.185 145.503 154.565 90.953 105.477 118.724 0
-56.0956
-64.3057
-62.0792
-50.9343
-53.8
-52.269 0
StressDist StressDist StressDist StressDist StressDist StressDist Coeff
Through Wall Stresses for Load Cases With Stress Coeff-------
Wall Case Depth primary ho 0.0000 0.1220 0.2440 0.3660 0.4880 0.6100 0.7320 0.8540 0.9760 1.0980 1.2200 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 7.371 Crack Model: Elliptical Longitudinal Crack in Cylinder (t/R=0.1,a/l=0. 1)
WARNING: The stress intensity factor (K) is the maximum of K at the surface and K at the deepest point at each crack depth.
Crack Parameters:
Wall thickness:
Max. crack size:
1.6288 1.2200
Stress Intensity Factor --------------------
Crack Case Case Case Case Size Plrsdl_70 P2_rsdl_70 P3_rsdl_70 Plrsdl_55 Case P2_rsdl_55 File No.: 0800769.311 Revision: 1 Page B-44 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
0.0244
-6.71806 0.0488
-9.48828 0.0732
-11.6043 0.0976
-13.3793 0.1220
-14.9344
'0.1464
-16.3317 0.1708
-17.6407 0.1952
-18.9295 0.2196
-20.1503 0.2440
-21.3137 0.2684
-22.4279 0.2928
-23.4987 0.3172
-24.5309 0.3416
-25.6197 0.3660
-26.7332 0.3904
-27.8254 0.4148
-28.8976 0.4392
-29.9508 0.4636
-30.9857 0.4880
-32.0029 0.5124
-33.1651 0.5368
-34.3204 0.5612
-35.4642 0.5856
-36.5961 0.6100
-37.7156 0.6344
-38.8222 0.6588
-39.9702 0.6832
-41.236 0.7076
-42.4914 0.7320
-43.7352 0.7564
-44.9667 0.7808
-46.1849 0.8052
-47.3889 0.8296
-48.6983 0.8540
-50.0665 0.8784
-51.4199 0.9028
-52.7572 0.9272
-53.1925 0.9516
-52.6735 0.9760
-52.0769 1.0004
-51.6976 1.0248
-51.2794 1.0492
-50.8105 1.0736
-50.295 1.0980
-49.7375 File No.: 0800769.311 Revision: 1
-6.22218
-8.80282
-10.784
-12.4539
-13.9239
-15.2508
-16.4992
-17.7332
-18.907
-20.0303
-21.1103
-22.1523
-23.1605
-24.2264
-25.3196
-26.3954
-27.455
-28.4989
-29.5277
-30.5417
-31.7001
-32.8544
-34
-35.1362
-36.2624
-37.3778
-38.536
-39.813
-41.0815
-42.3404
-43.5886
-44.8248
-46.048
-47.3774
-48.7665
-50.1416
-51.5014
-52.8443
-53.0186
-52.2251
-51.6365
-50.9895
-50.2715
-49.4867
-48.6393
-6.76032
-9.57471
-11.7426
-13.5761
-15.1956
-16.6625
-18.0472
-19.4205
-20.7315
-21.9907
-23.2059
-24.3829
-25.5263
-26.7386
-27.9863
-29.2194
-30.439
-31.6459
-32.8407
-34.0238
-35.3773
-36.7324
-38.0839
-39.4311
-40.7733
-42.1099
-43.5031
-45.0418
-46.579
-48.1134
-49.6438
-51.1689
-52.6876
-54.3414
-56.0763
-57.8054
-59.527
-61.2397
-62.942
-64.6325
-66.5355
-68.4384
-70.3271
-72.1998
-74.0551
-4.79525
-6.76207
-8.25709
-9.50485
-10.5924
-11.5643
-12.4699
-13.3569
-14.1919
-14.9827
-15.735
-16.4531
-17.1404
-17.8612
-18.5937
-19.3064
-20.0001
-20.6755
-21.333
-21.973
-22.7021
-23.4195
-24.1222
-24.8097
-25.4817
-26.1377
-26.812
-26.6359
-26.054
-25.3891
-24.6421
-23.8134
-22.9039
-21.974
-21.0074
-19.9712
-18.8676
-17.6986
-16.4669
-15.1748
-14.0253
-12.847
--11.6338
-10.3904
-9.12204
-5.13368
-7.24594
-8.85602
-10.2036
-11.3814
-12.4371
-13.4234
-14.392
-15.3066
-16.1754
-17.0044
-17.7981
-18.5602
-19.3613
-20.1775
-20.9742
-21.7524
-22.5126
.-23.2553
-23.9809
-24.808
-25.6248
-26.4279
-27.2167
-27.9908
-28.7496
-29.5319
-30.3916
-31.2364
-31.7379
-31.0844
-30.3369
-29.4957
-28.6297
-27.719
-26.7251
-25.6496
-24.4942
-23.261
-21.952
-20.7907
-19.5863
-18.331
-17.0293
-15.6858 Page B-45 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
1.1224 1.1468
- 1. 1712
- 1. 1956 1.2200
-49.1428
-48.5 185
-47.8864
-47.2532
-46.6274
-47.7339
-46.7905
-45.8538
-44.8991
-43.935
-75.8777
-75.5827
-75.2889
-74.96 13
-74.6071
-7.8339 1
-6.53329
-5.23966
-3.96252
-2.7 1053
-14.3055
-12.8971
-11.4835
- 10.0689
-8.66 168
Stress Intensity Factor ----------
Crack Case Case Size P3_rsdl_55 primary ho 0.0244
-5.42025 0.0488
-7.6673 0.0732
-9.39176 0.0976
-10.8449 0.1220
-12.1237 0.1464
-13.2777 0.1708
-14.3633 0.1952
-15.4364 0.2196
-16.4569 0.2440
-17.4335 0.2684
-18.3725 0.2928
-19.2785 0.3172
-20.1552 0.3416
-21.0823 0.3660
-22.0333 0.3904
-22.9696 0.4148
-23.8919 0.4392
-24.8009 0.4636
-25.6973 0.4880
-26.5812 0.5124
-27.5913 0.5368
-28.5985 0.5612
-29.5988 0.5856
-30.5916 0.6100
-31.5764 0.6344
-32.5526 0.6588
-33.5671 0.6832
-34.6861 0.7076
-35.7989 0.7320
-36.9044 0.7564
--38.0017 0.7808
-39.0899 0.8052
-40.1681 0.8296
-41.3407 File No.: 0800769.311 Revision: 1 1.92366 2.74502 3.39203 3.95 15 4.45674 4.92465 5.36888 5.80088 6.2 1779 6.62266 7.0178 7.40494 7.78545
- 8. 17085 8.55 815 8.94264 9.32488 9.70534 10.0844 10.4625 10.859 11.2565 11.6547 12.0536 12.4535
- 12. 8544 13.2633 13.6898 14.1185 14.5494 14.9826 15.4181 15.856 16.3 116 Page B-46 of B-Si F0306-01 RO
Structural Integrity Associates, Inc.
0.8540 0.8784 0.9028 0.9272 0.9516 0.9760 1.0004 1.0248 1.0492 1.0736 1.0980 1.1224 1.1468 1.1712 1.1956 1.2200
-42.5671
-43.7829
-44.9871
-46.1785
-47.3561
-48.1482
-47.8113
-47.4277
-46.9864
-46.4907
-45.944
-45.3499
-44.7235
-44.099
-43.4594
-42.8116 16.7796 17.2508 17.7251 18.2026 18.6832 19.167 19.6987 20.2373 20.7801 21.3272 21.8785 22.4339 22.9901 23.5412 24.0961 24.6548 Crack Growth Laws:
Law ID: Fatigue_551 Model: ASME Section XI - austenitic stainless steel in air environment da/dN= C
- 10AF
- S
- dK^3.3 where S = 1.0 for R < 0
=1.0 + 1.8
- R for 0 < R < 0.79
=-43.5+57.97*R for 0.79<R< 1 F = code specified function of temperature dK = Kmax - Kmin R = Kmin / Kmax where:
C
- 1OAF = 1.8424e-010 is for the currently selected units of:
force: kip length: inch temperature: 551.0000 Fahrenheit Material Fracture Toughness KIc:
Material ID: Alloy 82/182 File No.: 0800769.311 Revision: 1 Page B-47 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
Depth KIc 0.0000 0.7500 1.5000 63.2500 63.2500 63.2500 Material ID: high toughness Depth KIc 0.0000 0.7500 1.5000 200.0000 200.0000 200.0000 Initial crack size=
Max. crack size=
0.5100 1.2200 Number of blocks=
Print increment of block=
1 1
t Cycles Calc. Print Crk. Grw.
Subblock
/Time incre. incre.
Law Mat.
Klc growth 10000 10 100 Fatigue_551 Alloy 82/182 Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor growth primary hoop stress P1_rsdl_551F-hoop 1.0000 1.0000 P2_rsdl_70F hoop 1.0000 Crack growth results:
Total Subblock Cycles Cycles
/Time
/Time Kmax DaDn Kmin DeltaK R
/DaDt Da aa/thk Block:
1 100 100 -1.18e+001 -3.16e+001 1.98e+001 2.67 0.00e+000 0.00e+000 200 200 -1.18e+001 -3.16e+001 1.98e+001 2.67 0.00e+000 0.00e+000 300 300 -1.18e+001 -3.16e+001 1.98e+001 2.67 0.00e+000 0.00e+000 0.51 0.31 0.51 0.31 0.51 0.31 File No.: 0800769.311 Revision: 1 Page B-48 of B-51 F0306-01 RO
V Structural Integrity Associates, Inc.
400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 400 -1.18e+001 -
500 -1.18e+001 -
600 -1.18e+001 -
700 -1.18e+001 -
800 -1.18e+001 -
900 -1.18e+001 -
1000 -1.18e+001 1100 -1.18e+001 1200 -1.18e+001 1300 -1.18e+001 1400 -1.18e+001 1500 -1.18e+001 1600 -1.18e+001 1700 -1.18e+001 1800 -1.18e+001 1900 -1.18e+001 2000 -1. 18e+001 2100 -1.18e+001 2200 -1.18e+001 2300 -118e+001 2400 -1.18e+001 2500 -1.18e+001 2600 -1.18e+001 2700 -1.18e+001 2800 -1.18e+001 2900 -1.18e+001 3000 -1.18e+001 3100 -1.18e+001 3200 -1.18e+001 3300 -1.18e+001 3400 -1.18e+001 3500 -1.18e+001 3600 -1.18e+001 3700 -1.18e+001 3800 -1.18e+001 3900 -1.18e+001 4000 -1.18e+001 4100 -1.18e+001 4200 -1.18e+001 4300 -1.18e+001 4400 -1.18e+001 4500 -1.18e+001 4600 -1.18e+001 4700 -1.18e+001 4800 -1.18e+001 3.16e+001 1 3.16e+001 1 3.16e+001 1 3.16e+001 1 3.16e+001 1 3.16e+001 1
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001'
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+001
-3.16e+00 1,
-3.16e+001
-3.16e+001
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V Structural Integrity Associates, Inc.
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V Structural Integrity Associates, Inc.
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