ML19309C569
| ML19309C569 | |
| Person / Time | |
|---|---|
| Site: | Three Mile Island  |
| Issue date: | 05/01/1967 |
| From: | JERSEY CENTRAL POWER & LIGHT CO., METROPOLITAN EDISON CO. |
| To: | |
| References | |
| NUDOCS 8004080804 | |
| Download: ML19309C569 (36) | |
Text
{{#Wiki_filter:_ - _ _ _ _ _ _ . . _ _ _ _ _ _ _ _ _ _ _ _ d' Docket 50-289 Supplement No. 2 November 6,1967 QUESTION With respect to the brittle fracture mode of failure provide the 11.2 following additional infor=ation: 11.2.1 The assumed distribution of the initial NDT temperature through the plate thickness. State also the experimental basis for this assump-tion and the degree of conservatism involved. ANSWER The distribution of NDTT through the plate thickness was assumed to be a constant value of +10 F. The +10 F was assumed because the B&W Material Specification requires that material in the core region vill have, as a maxi =u=, an initial NDTT of +10 F at a depth below the surface equal to 1/h T. The use of a constant value through the thickness of the plate is conservative when consideration is given to the recent work from Lehigh University,(1) B&W,(2) and others.(3) From the references cited it is found that, for all practical pur-poses, the)NDTT at 1/k T is the same as the NDTT at 1/2 T for plates in the thickness range of 8 to 12 in. Our analysis is conservative in that it did not consider the benefit which could be gained by considering the enhanced properties which exist at the surface. From References 1 and 2 the NDTf at the surface vould be expected to be -50 F. ,f 'b The AEC, with the cooperation of Industry, is at present engaged in a program of material character 1:ation which will further substanti-ate the data presented here. 11.2.2 The assumed ti=e-integrated neutron flux (nyt) at the reactor ves-sel inner dia=eter. l ANSWER The assumed time-integrated neutron flux (nvt) at the reactor ves- ! sel inner vall is 3 x 10 9 1 n/c=2 (E > 1 gev). This value is stated ' in the PSAR Section h.l.h.1, page h-3. 11.2.3 The profile of the NDT temperature shift through the thickness of the plate. ANSWER The NDTT profile at the end of Station life was assumed to be a constant value of 250 ? through the thickness of the reactor vessel I vall. This value was stated in the PSAR Section h.1.k.1, page h-3. The use of a constant value for NDTT shift is very conservative be-cause the analysis did not consider the beneficial effect which can < be realized by considering the self-shielding (h) of the material to radiation damage. 0004 005 O v 11.2 , 8004080 570 0 f
Docket 50-289 Supplement No. 2 November 6,1967 REFERENCES (1)Strunk, S. S., Pense, A. W., and Stout, R. D., The Properties and Micro-structure of Spray-Quenched Thick-Section Steels, Welding Research Coun-cil Bulletin No. 120, February 1967 (Appendix A) ( B&W Data en SA-302GB Ma; rial.(Appendix B) (3) Naval Reactors Program Data (Classified). (16)NRL Memo No. 1731, p. 15 - 21. l 0004 006 ( e J
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i Docket 50-289 Supplement No. 2 November 6,1967 APPENDIX A THE PROPERTIES NiD MICROSTRUCTURE OF SPRAY-QUENCHED THICK-SECTION STEELS by S. S. Strunck, A. W. Pense and R. D. Stout Reprinted frem Welding Research Council Bulletin No. 120 February 1967 ) Welding Rer.earch Council New York, N. Y. 0004 007 M CLIMAX MOLY 3DENUM CCMPANY An AMAX Division 1270 Avenue of the Anericas, New York, N. Y. 10020 Printed in U.S.A.
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,e 3roperties anc Microstructure o" spray-Quenclec
~1iceSection Stee s by S. S. Strunck, A. W. Pense and R. D. Stout l
l AasTaACT. With the increasing use of thick-seC' tion demands with the conyggtjongj materig]3 3 quenched and tempered steels for nuclear and chemical l reactors, there is a definite need for informatson on the With this increase in wall thickness, both si properties of some of the newer low-alloy high-strength and toughness are decreased and fabricatio I steels when given such thick-section heat treatment. Of particular interest are yield and tensile strengths attainable, are increased. It is to be expected, thei the notch toughness to be expected, the plastic fatigue both new materials and heat treatments she strengths available and the kinds of microstructure that developed for such heavy walled vessel a appear to be characteristic of these thicknesses. In the program reported here, four quenched and tem. tions. In practice, these two developme) l pered heavy-section steele--A212 Grade B, A533 Grade B, cor 1plementary. The new maten.a ls as A542 and A543-were studied in the simulated 6-in. thick for these vessels are of significantly greater 1 and 12.in. thick quenched, tempced and stress-relieved con-ability than those previously used. This ioYwere"*eN*t"'[t*" t p Nv"ide a SNte$tionSf Z quenching and tempering treatments mc properties and structure of heavy-section, heat-treated, sirable than with conventional steels beer I low-*lloY *t"Is. heavy sections where accelerated cooling The results show that increasing the secu.on size from 6 to 12 in. produced no important changes in strength, notch little to improve, for example, a carbon sti toughr-se or fatigue resistance in these steels in the higher alloy steels respond to produce mier ! (f s quenched, tempered and stress-relieved condition. When comparing 1.in. thick plate with the heavy sections, strength decreased only modestly while notch toughness decreased substantially. Because of their initial good toughness, tures representing improved strength and ness. The use of such steels has alread: shown to be of advantage in section sizes i I however, the alloy steels still exhibited transition tempera-tures below -10' F. The fatigue and elevated temperature in. both from the standpoint of strength anc properties of the steels were similar to those found in thinner toughness.' 8 In section sizes over 4 m.. sections of equivalent tensile strength. The results of the industrial experience has already been ob microstructure study confirmed the mechanical property However, a program surveying some of the tests in that little diNerence in tri rostructure was observed and more promising matenals in a syst between the 6-in. and 12 in. conditions. manner had not been done. Therefore, tl l introduction gram described in this paper was underta provide such a survey of four of the newer In view of the recent trend to larger pressure walled pressure-vessel materials. vessels for the higher operating pressures and In this program, four steels-A212 Grade temperatures of the nuclear power and chemical the quenched and tempered condition), industries, considerable effort has been expended Grade B, A542 and A543-Al of which in the development of new materials and heat potential use in heavy-walled vessels, weri treatment procedures for large heavy-walled re. pared in heavy-section sizes. It was be actor vessels. In the past, these vessels have that four properties are of interest in a sti been of carbon or low-alloy steels and the heat the response of low-alloy steels to acce I treatment most commonly used has been cooling in heavy sections. The first of normalizing And stress relieving. Current in- is yield and tensile strength at roon dustrial practice is moving away from these more elevated temperatures. The advantage e i established materials and procedures because of steels must be realized by practical incre: both economics and safety. As the size and re- both yield and tensile strength in the center quirements of the newer vessels have increased, nesses of heavy-section plates if they are so has the wall thickness required to meet these attractive. The extent to which such ini V s. s. strumek ;. R., mech Anstant. A. W. Pease is Associate Profameer,and can be maintained as section size increas l R. D. Stout la Desa of the Graduate School. Imhgh Umaversaty. Bethleh.ai. Comes an important question. Pa. A second area of importance, indeed a i a.D,0iTO*utt.e j tCE.E"sT."".aNe'I.* ,$"""" """' one from the safety standpoint, is the k m sc u s
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ghness properties that can be expected as a Because of the thickness of these plates, it was alt of quenching and tempering of a heavy- possible to perform duplicate mechanical prop- ! tion low-alloy steel plate. It has been shown erty tests on both center- and quarter-thickness i t a favorable balance of both strength and positions to reveal any differences in the behavior ghness can be maintained in thinner-section of materials from these locations. Therefore,
-alloy plates; to what extent can this be main- there were essentially eight sources of material aed as section sizes increase? Because of the for testing, i.e., center- and quarter-thickness sortance of this area, the notch toughness tests locations in four different steels. The as-received tducted in this program were supplemented by properties of the plates are listed in Table 2.
ne-strain fracture toughness evaluations on 33B, A542, and A543 by Westinghouse, and Heat Treatment
.ch tensile tests were conducted on the A212B i A533B by Syracuse University. Heat treated In order to produce data useful in evaluating the terial from this program was furnished to them suitability of the four quenched and tempered this purpose. The results of these tests are steels to heavy-section service,it was necessary to .orted separately in this Bulletin. heat treat the plates to reproduce heavy-section 1 third area of interest in this study is the quenched and tempered microstructures. It can igue resistance of the steels in the 1000 to be seen from Table 1 that the plates as-received ),000 cycle failure range. While few failures in were from 6% to 8 in. in thickness. Since this .ssure vessels have been directly attributed to initial thickness insured that the plates were igue, the role of fatigue in initiating cracks that representative of heavy sections in chemistry and d to failures cannot be ignored in vessel design. rolling practice it was decided to cut %-in. thick The fourth area of interest in the study of the test plates from the center thickness and quarter els is the influence of the cooling treatments on thickness positions of the original plates and to microstructures that are produced by the heat treat these test plates in such a manner as to l t I
enching and tempering of heavy sections. match the cooling rate from austenitizing that crostructure may appear to be of second- w uld be characteristic of two typical plate thick-r interest when mechanical property data nesses-6 in. and 12 in. In order to select cooling l ,known. Since properties of alloy plates are rates appropriate for these thicknesses, a large ongly influenced by microstructure, the evalua- body of both calculated and experimental data on n of microstructures produced by the heat cooling rates during the quenching of heavy-atmen: of heavy-section plate can give valuable section plates was obtained and studied.+-* /
.es to the combinations of steels and treatments These data are summarized in Fig. 1. Since it are required in order to produce useful relatively few of the experimental cooling rate data 3perties as section size is increased, available were obtained on large-size heavy-section The study reported in this paper must be con. plates, and dip as well as spray quenching may be ered limited in scope in that it includes dat i m single heats of only four typical steels. How.
3r, the specimens were cut from both the quarter 'e . ,
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rcially produced heavy plates and thus the ,,k .O +-gyp l 'estigation provides coordinated data on the j _# 1racteristics of commercially-produced low-oy high-strength steels when heat treated for t- k'A 7 ;;og l l avy-section service. It should therefc.e serve 4i t i g,
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~1 tiled pressure vessels were included in the experi- j **h %g mtal study. These were A212 Grade B, A533 *"" Nd ade B, AS42, and A543. The chemical com- e,h ,
sitions of these steels are listed in Table 1. te four steels were obtained as heavy thickness I g oduction plates, as indicated. Both quarter- . a a . s.r... i zo 3. d center-section chemical analyses were done on Ne Sce -- ase production plates and are listed in Table 1. sg.1-cooling rates in plates quenened frorn austenitizing 4- ,,o , , t' , 's V
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Table 1--Compositions and Heat.Trootment Temperatures for the Heavy Section Steels As O Steel C Mn P S Si Ni Cr Afa Cu Al nerived thickness, in. Treatment temperature A212B Ladle .25 .70 .012 .037 .23 .15 .07 .. .16 .037 6% Austenitizing 1650' F 1 Quarter .27 .72 .007 .o25 .24 .12 .08 <.01 .15 .020 Tempering 1200* F 8 hr Center .28 .73 .007 025 .24 .13 .08 <.01 .16 .019 Stress relief 1100' F 24 A533P Ladi. .20 1.28 .019 .030 .21 .53 .15 .52 .27 .031 7% Austenitizing 1650' F 1 Quarter .19 1.26 .024 .02S .25 .52 - .13 .52 .30 .022 Tempermg 1200* F 8 hr Center .18 1.25 .024 .025 .24 .52 .13 .51 .29 .025 Stress relief 1100* F 24 A543 Ladle .17 .32 .013 .017 .28 3.65 1.86 .48 ... . . 8 A stenitizing 1575' F 1 Quarter .16 .34 .014 .020 .27 3.60 1.89 .53 .07 .004 Tempering 1200* F 8 hr Center .15 .32 .013 .020 .28 3.55 1.85 .50 .06 <.004 Stress relief 1100* F 24 A542 Ladle .14 .46 .010 .020 .28 .25 2.35 .99 .19 024 7% Austenitizing 1750' F 1 Quarter .15 .46 .013 .024 .31 .21 2.32 1.14 .23 .006 Tempering 1200* F 8 hr Center .15 .46 .013 .027 .30 .22 2.34 1.11 .22 .006 Strene relie(1100' F 24 hr Table 2-As-Iteceived Mechanical Properties
- of the Heavy-Section Steels Yield Tensile To El. Te R of Charpy V.notca Material Heat treatment str. ksi str. ksi (2 in.) A energy, ft.lb A212B Aust.1650' F, water quench, tempered 1225' F, 6 41.7 74.2 33 at 10' F--41, 40, 4 hr, strees relieved 1125' F,20 hr, furnace cool A533B Aust.1575' F, water quench, tempered 1225' F, 69.4 89.9 27 66.2 at 10' F-37,35,3E 4 hr, strees relieved 1125' F,30 hr, furnace cool A542 Aust.1700' F, water quench, tempered 1175' F, 7 94.7 111.4 19 60.5 at 10' F-23,30,24 hr, air cool A543 Double quenched and tempered 96.1 119.1 16.8 44.5 at 10' F-60, 60, 7f at -120* F--35, 36, e a Longitudinal properties, quarter thickness.
employed for accelerated cooling of heavy plates, x 16 in. x 24 in. with internal baffles adjuste it was thought wise to select generally conservative obtain the desired cooling rate. The co< values for cooling rates attainable from quenching. rates were obtained for the latger plates by t The cooling rates selected to represent the 6-in. aluminum foil bases set at experimentally d and 12.in. thicknesses were 0.85* F/sec and 0.25* mined distances from a free hanging plate. Th F/sec, respectively, and are indicated on Fig.1. ocouples were attached to the plates b. These two cooling rates were then reprodt ced in austeritizing to monitor the cooling rates dt the %-in. thick test plates by simulated cooling the " quenching" cycle. Since some variatic treatments. cooling rates did occur, only plates with co. The material received for the program was in the rates within 0.05* F/see of that selected form of plates approximately 10% in. wide by 24 used in the experimental study. To reduce in. long by the plate thickness (6-8 in.), These effects, approximately l' 's in. was removed were cut into two sections approximately 10% in. the test plate edges before specimens were by 18 in. by the thickness and 10% in. by 6 in. by chined. the thickness. The plates were then sectioned The tempering treatment given to the p along the thickness dimension and %.in. thick (Table 1) was designed to simulate the ty-slices were removed at both quarter thickness treatment given to a heavy-section plate. E positions and two %-in. thick slices were removed heavy-section plates often receive one or i on either sid.e of the center-thickness position. long stress-relief treatments during fabrics These plates were then heat treated as indicated operations, it was also felt desirable to inclu in Table 1. A system of aluminum foil baffles heavy-section stress-relief treatment, followec was used to retard the cooling of the plates from a cooling rate from stress. relief as specified by austenitizing to the degree necessary to produce ASME Boiler and Pressure Vessel Code for a the desired cooling rates. This system varied in. thick plate. The test plates were accordi (~ somewhat with the size of the test plate, but stress-relieved for 24 hr at 1100* F followet basically consisted of cooling the smaller plates cooling at a rate of approximately 40' F pe in an aluminum foil lined box of dimensions 12 in. to 600* F. In order to determine if this na s+ se 0004 010
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l l l 21ing treatment from stress-relief was deleterious Results and Discussion toughness, some plates were cooled at a rate of With regard to the data obtained in this study, P F per hour (approximating the air cooling of leavy section plate) to study the effect of this t is important to keep in mind that the program is made up of single-heat data only for the four steels g , )hng treatment. involved and provides no statistical information. I On the other hand, the heats used in the study are i commercially produced heavy-section steels and sting Schedule therefore do represent material taken from heats The schedule of tests for each of the four steels of acceptable commercial quality. Moreover, the quarter- and center thickness and at two cooling real value of the program lies not so much in the es (6-in. and 12-in. . thickness simulations) specific levels of strength and toughness obtained,
- luded room- and elevated-temperature tension as in the comparative behavior of the various -
its, Charpy V-notch and drop weight tests, steels and in the general response of the steels to d cantilever bending fatigue tests. In addition heat treatment in heavy sections. these mechanical property tests, photomicro-aphs were prepared of each of the four steels in e simulated 6-in. and 12-in. conditions at various The results of the room- and elevated-tempera-iges in their heat treatment. ture tension tests for the four steels may be found The tension tests were performed in air on in Table 3 and in Figs. 2 to 9. Forthree of the four igitudinal 0.252.in. diam tension test specimens steels tested the difference in cooling rate between th 1.0 in. gage length. Tests were performed the 0.85* F/sec (6-in.) condition and the 0.25' F/ room temperature and at elevated temperatures sec (12-in.) condition did not produce any ap-i to 1100* F. A strain rate of 0.05 in./mmute preciable difference in mechanical properties. is used for all tests. Center and quarter-thick- For A212B, A542 and A543, the largest diference ss specimens of all four steels at both cooling in either yield or tensile strength observed between tes were tested at room temperature and 200* F. the two cooling rates for a given position was mter thickness specimens of both cooling rates about 3 ?o increase in strength for the 6-in. material are tested at 400* F,800* F, and 1000* F, while while for a majority of the cases this dif-tarter. thickness specimens of both cooling rates ference was even smaller. For A533 Grade B, are tested at 600* F,900* F and 1100* F. The mperature during the elevated temperature however, there was a difference of about 10Fo in yield strength and 5fo in tensile strength between g sts was controlled to within 35' F. At least the two conditions, the 6-in. material once again to specimens were tested for each condition at being the stronger. ch temperature and the results averaged. In terms of general strength level, the A212 The impact tests were standard Charpy V- Grade B is by far the weakest of the four. steels, itch and standard specimen type P-2 drop- with a yield strength less than half that of A542 right tests.' The Charpy test data were or A543, and a tensile strength about 65?o that of aluated for the 15 ft-lb energy transition tempera- A542 or A543. The A533 Grade B lies approxi-re, the 15 mil expansion transition temperature, mately in the mid-range between these two values. e 50?o shear fracture appearance transition It should be noted that when given either the 6-in. mperature and the upper shelf energy value. or 12-in. treatment, the A533 Grade B, A542 ae drop-weight test was evaluated for the nil and A543 all meet Class 1 specifications for these tctility temperature. All Charpy impact speci- grades while the A212 Grade B would be below ens were parallel to the plete rolling direction mimmum specifications in the quarter-thickness td were notched transverse to the plate sur- material fcr either thickness. ce. Each Charpy series consisted of from 15-30 In general, there was but little difference in ecimens. strength properties between the two plate posi-The low-cycle fatigue tests consisted of con- tions, reflecting the general uniformity of composi-Ant deflection bending tests (R - - 1) on tions shown in the chemical analysis of Table 1. 2ndard Lehigh cantilever-bend fitigue speci- For two steels, A533 Grade B and A542, the mid-ens. This specimen is 18 in. long by 2i/: in. thickness specunens were somewhat stronger,
- de by % in. in thickness in the test section. while for the other two, A212 Grade B and AS43, ae range of testing included total strain ranges the quarter-thickness specimens were stronger.
oducing failures between 1000 and 200,000 These differences were no more than about 5To in cles. Both the total strain ranges for the first yield strength and 3fo in tensile strength for any sible cracking of the specunen and for complete paration of the specimen were recorded. Be-of the steels. The only apparent segregation of alloy elements or carbon evident in Table 1 h ' use of the size of these specimens, it was neces- occurred in A543 where the quarter-section ry to run transverse rather than longitudinal chemistry is richer in nickel, chromium and ecimens in the fatigue portion of the study. molybdenum. t J* 6
- a. : -,;I,t Thick Section Steels 0004 011
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Tahie3-Aoem-and Devoted-Temperature Tensile Properties of the Heavy-Section Steels 0.2% Ultimate 0 offset yield Steel and condition point.ksi tensile elongo. reduc. strength- tion in tion of ksi 1 in. ana
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offset yleid Steel and condition point.ksi Ultimate tensile elonga- t strength- tion in t ksi 1 in. Room Temperature Room Temperature A212B A542 (Class I) 6 in. Quarter
- 39.6 67.6 40.5 64.9 6 in. Qvarter 94.2 111.4 20.0 6 in. Center 42.2 70.8 36.0 62.9 6 in. Center 94.2 112.2 21.0 12 in. Quarter
- 40.1 68.3 38.0 64.1 12 in. Quarter 92.9 110.5 21.0 12 in. Center . 42.6 71.6 35.5 60.7 12 in. Center 93.7 111.4 16.0 200*
- 200* F 6 in. Quarter 42.4 70.u 0 65.1 6 ia. Quarter 101.5 113.4 20.0 6 in. Center 43.7 71.8 29.0 64.7 6 in. Center 100.1 112.0 19.0 12 in. Quarter 40.7 69.2 28.0 66.9 12 in. Quarter 98.8 112.3 15.0 12 in. Center 41.7 70.7 29.0 64.8 12 in. Center 98.3 111.6 15.0 400* F 400* F 6 in. Center 30.9 64.1 29.5 63.6 6 in. Center 95.2 111.5 12 in. Center 13.0 i 30.5 60.9 33.0 64.5 12 in. Center 91.2 111.1 14.0 e 600* F 600* F 6 in. Quarter 23.3 63.6 33.5 61.0 6 in. Quarter 79.4 98 3 14.0 e 12 in. Quarter 24.4 66.6 24.0 62.5 12 in. Quarter 74.3 92.3 14.0 a 800* F 800* F 6 in. Center 23.4 53.5 35.5 71.6 6 in. Center 82.7 96.2 12 in. Center 16.0 i 21.7 49.0 45.0 78.2 12 in. Center 83.1 88.6 15.0 e 900* F 900* F 6 in. Quarter 20.5 39.5 41.0 83.2 6 in. Quarter 75.0 82.4 21.0 17.0 e 12 in. Quarter 40.8 38.0 79.9 12 in. Quarter 71.1 79.4 16.5 4 1000* F 1000* F 6 in. Center 18.6 31.7 39.0 80.9 6 in. Center 70.0 12 in. Center 74.7 22.0
- 18.6 30.8 43.0 85.0 12 in. Center 70.5 75.1 e 1100* F 1100* F f 6 in. Quarter 16.4 25.1 36.0 84.5 6 in. Qaarter 58 7 ;
(w 12 in. Quarter 16.3 25.9 37.0 82.5 12 in. Qu arter 58.4 63.3 60.7 21.0 19.0 i Room Temperature Room Temperature A533B (Class I) A543 (Clu a D 6 in. Quarter 70.0 88.7 28.0 69.5 6 in Qt.arter 86.5 6 in. Center 106.4 25.0 0 68.2 85.9 27.0 71.2 6 in. Center 86.3 103.4 28.0 f 12 in. Quarter 64.1 84.6 29.0 68.8 12 in. Quarter 86.3 12 in. Center 59.0 80.6 34.0 103.2 25.0 1 70.1 12 in. Center 84.0 101.2 27.0 f 200* F 200* F 6 in. Quarter 64.8 82.5 25.0 69.3 6 in. Quarter 83.0 6 in. Center 63.4 99.5 21.5 7 79.8 21.0 69.7 6 in. Center 85.0 12 in. Quarter 56.7 77.5 28.0 101.5 23.0 0 68.0 12 in. Quarter 75.4 91.0 21.0 7 12 in. Center 49.9 70.0 29.0 70.6 400* F 400* F 6 in. Center 75.9 93.5 21.0 1 6 in. Center 60.4 80.7 22.5 12 in. Center 12 in. Center 71.6 87.4 19.5 f 45.8 68.4 23.5 66.4 600* F 600* F 6 in. Quarter 72.3 89.5 20.0 E 6 in. Quarter 58.1 83.6 21.0 60.0 12 in. Quarter 72.5 48.5 92.0 20.0 6 12 in. Quarter 78.9 23.0 58.0 800* F 800* F 6 in. Center 68.1 92.3 20.0 6 6 in. Center 56.7 78.0 20.0 68.9 12 in. Center 12 in. Center 70.4 83.5 20.0 6 40.4 71.1 26.5 66.3 900* F 900* F 6 in. Quarter 62.6 72.2 25.0 7 6 in. Quacter 51.7 64.6 22.0 73.8 12 in. Quarter 64.1 41.4 58.4 72.7 24.0 7 12 in. Quarter 28.0 74.9 1000* F 1000* F 6 in. Center 57.0 62.0 32.5 8 6 in. Center 47.5 54.8 80.1 12 in. Center 12 in. Center 57.3 60.7 21.0 8 34.4 47.7 79.4 1100* F 1100* F 6 in. Quarter 48.2 52.8 27.0 8 6 in. Quarter O- 12 in. Quarter 44.2 36.1 45.5 39.S 26.0 38.0 81.4 82.6 12 in. Quarter 47.0 49.5 8
- Cooling rate 0.85* FMe, quarter thickness.
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. 3-The influence of temperature on the elongation and re- Fig. 5-The influence of temperature on the elongation and re-duction of area of quenched and tempered A2128 duction of area of A5338 The room tett; erature tensile ductilities of the compared to room temperature. The loss in tr steels redect, inversely, the tensile properties yield strength at this temperature is about 407, the steels. Those materials and conditions for the A212 Grade B and about 209, for A533
- h the lowest strength generally had the highest Grade B. For A542 and A543, the tensile strength isile ductility. The variations in ductility in loss at 600* F is somewhat greater, about 15?o, i same steel with diferent conditions of treat. but the initial room temperature strength of these nt were amall compared to those between steels is high enough to more than offset the in-els. The dutility of the A212 Grade B was creased loss. The loss in yield strength of A542 nost twice that of the A542 while A533 Grade and A543 at 600* F is also about 15Fe. Above tnd A543 were intermediate. 800* F the yield and tensile strengths of all of the The elevated temperature tensile properties of steels appear to decrease sharply to values at a steels, found in Figs. 2 to 9, show that all of the 1100* F that are approximately 50Fo of the room g els tend to have aging reactions between room temperature values. These eight figures (Figs. W uperature and 800* F that cause their tensile 2-9) include data from both center- and quarter-ength curves to remain relatively high up to thickness specunens (as may be seen from Table 3)
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20- 20 - O 200 400 GCC 800 m gp o 200 400 600 800 Imo Testing Tenoegen,g = *F Testing Temperature *F Fig. 6-This influence of temperature on the yield and tensile Fig. 3-The in!!uence of temperature on the yield and t strength of A542 strength of A543 2 i . , . . , c , E
- So- ai * . go. UcMohon ,,
SC Reducnon of area l6 , , 80- ' " **' a s pr
;W , .
{
'i ;%/
$ 30- -
so. { 40 - . 4o. 30-
- 20
- g. .
3o. '~'N 20- t"E r' 10- io. o 4m 600 8 iCCD CD C o 2m 4co 6m em so:D f Test.ng Tencerature *F Tesang Tencerature *F Fig. 7-The influence of temperature on the elongation t'id re. Fig. 9-The influence of temperature on the elongatior duction of area of A542 reduction of area of A543 points are plotted without diferentiating them. Impact Properties Some diferences due to cooling rate are apparent. The summuized Charpy impact test results For A533 Grade B, and to alesser extent A542, the the drop-weight test results for the four steel diferences in strengths observed for the two found in Tables 4 and 5 and Figs.10 and 11. cooling rates are more pronounced at elevated Charpy impact test curves are found in temperatures. In these two cases the faster Al to A20. The Charpy impact tests re cooled (6-in. thick) plate holds some strength generally ceaurm the tension test results advantage. For the A543 and to a lesser extent respect to the influence of section loca A212, the agin'g characteristics of the two diferent There was little or no efect in A212 Grade cooling conditions are somewhat diferent but A533 Grade B, while for AS42 and A543 a dect neither condition holds a distinct advantage. of about 10* F in Charpy V-notch 15 ft lb or 1: The elevated. temperature ductilities continue to transition temperature for the quarter-sei l redect inversely the trends observed in the streng6h location was noted. For A212 Grade B and 4 curves. The ductilities generally continue to Grade B there was also little influence of co.
^j remain ranked in the same order as at room rate on toughness. For A542 and A543 a me:
temperature. while aging peaks in the strength able improvement in 15 ft.lb or 15 mil trans curves are mirrored by ductility minima in the temperature exists in the 6-in. plate as comp same temperature range. to the 12-in. plate. In A542 this amount i .. . Thick Section .Steela c'o " M..s.... . 0004 014
Table 4--Charpy V-Notch impact Test Data Table 5-Drop-Weight Test Det. NDT NDT (*F)-
-Trans. temp. *F~ fnx Shelf Energy -6 in. Plates- -IP sn. Plates Chemistry and 15 15 50*b energy energy required Center Quarter Gnter Quart, cooling rate (t.lb mils shear (t-lb (t.lb Steel chem.
(ft.lb) chem. chem. chem
.212 Grade B A212 Grade B 285 0 0 + 10 + 1f 6 in. Plate center * + 28 0 + 90 9 61 A533 Grade B 333 - 20 - 10 - 10 - it
' 6 in. Plate RC A542 380 - 30 - 40 - 20 - 3( center + 22 - 10 + 90 ... ... A543 380 - 110 - 110 - 110 - lit 6 in. Plate quarter * + 28 -2 +108 9 '77 6 in. Plate RC quarter + 24 - 10 + 90 ... .. 12 in. Plate center + 32 -4 + 90 10 61 e tr 12 in. Plate quarter
+ 28
+32
+2 + 94 ... ... i UE %N NN NN *EE Nik
-2 + 105 10 74 j o ..f *" """"""."""'7" C;;y4.-(gi; hh"- ..
12 in. Plate F.C g , ,d y . .;;;; ::3j quarter + 16 * - 14 +84 g ..o,
"-" '. p ggjg Eg : .533 Grade B a I g E: j '
3 s,3 6 in. Plate center 6 in. Plate RC
- 28 - 56 + 34 17 88 9-coh i < ca Z" dg* j ' gj Cb :.::
- 28 - 60 3%5 s j center + 54 ...
6 in. Ptate quarter - 2S - 46 3 -eor; '[t.~,,e,,,a,* m
+ 38 15 SO 3 i-ma m- ;l; - :
6 in. Plate RC 'y ..soh *
- 10'.",l',.*"
quarter - 24 - 48 + 56 ... f w 3 E
$ .,{
12 in. Plate center - 20 - 48 + 60 18 79 ' 12 in. Plate RC , arras assse assa as43 center - 24 - 56 + 54 ... ... 12 in. Plate quarter - 16 - 40 + 68 16 75 Fig.10-The Charpy V. notch impact test results for the four hees 12 in. Plate RC section steels quarter - 26 - 54 +60 [ 542 l 6 in. Plate center - 66 - 72 + 90 20 7n 6 in. Plate RC +20 - center - 44 - 48 + 110 . . ... *'?*' ))" *??
* )*? *;? * )*?
6 m. Plate quarter - 70 - 78 + 72 20 86 o .... k J,"' " 6 in. Plate RC v.bb p",~ d$ - y quarter - 50 - 54 + 90 ... S. M" d ]! I: ;8'fff
' dd
;g ;
12 in. Plate center - 26 - 38 + 102 16 53 k -2c
- - p 12 in. Plate RC
- 44 - 50
] 9 0 r'
conter +62 ... . g .4o . 4 , 12 in. Plate quarter - 36 - 48 + 80 16 93 5 :, , , ' 12 in. Plate RC '- ****
*,.'.N,,**"'"
quarter - 50 - 52 +44 f'O -
/ ' -
543 g ,r..c. 6 in. Plate center - 120 - 134 - 50 17 77 ]
^f *
, c".**3..%., 77;.sgl ,
;j 6 in. Plate RC center - 150 - 160 - 70 . . ...
-'00 '
I 6 in. Ptste quarter - 130 - 136 - 38 20 71
~
^ #
q arter - 180 - 192 - 86 . . . 12 in. Plate center 112 - 46 12 69 e rIter - 164 - 172 Fig.11-The drop weight test results for the four heavy f actio
- 58 ... ..
12 in. Plate quarter - 110 - 120 - 50 15 steels 70 12 in. Plate RC quarter - 176 - 184 - 96 observed, with the largest improvements occut Center thicknene position. ring in the 12.in. plate specimens. The re
- Quarter thicknese position. sponse of A542 to the rapid cooling treatment fror RC - Cooled at 240*
mied at 40' F hr.: 12 m,F/hr . plate from cooledstress relief-at 0.25 F, see allfrom others stress relief was mixed while for the other steels astenitizing 6 in. plate cooled at 0.85* F/sec from musteni. very slight improvement was noted. sing. In general, the A543 has markedly superio notch toughness to any of the other steels in th bout 35' F, while for A543 it amounts to about program and A212 Grade B had the poorest tough 0
- F. ness of the four steels. A difference in transitio The use of a rapid cooling treatment from stress-alief is seen to substantially improve the impact temperature of over 100* F separates these tw extremes while A533 Grade B and A542 are in th h
i sistance of only one steel-AS43. For this steel, intermediate range. Both of these latter steel ecreases in the 15 ft.lb or 15 mil transition have transition temperatures more than 40* 1 imperature of between 6' F to 70* F were lower than the A212 Grade B. 0004 015
, b.
e m ru s,cuo,t su,u
,4. .
The drop-weight test data, presented in Table 5 consists predominantly of a mixture of upper and Fig.11, show no response to section location lower . bainite, with little apparer,t differ C or cooling rate from austenitizing for A533 Grade between the microstructures of the specir B and A543 steels. Only A542 steel shows much cooled at the 6 in. and 12 in. cooling rates. influence of cooling rate or location, as the 6-in. microstructure of the A543 seel (Fig.15) apt thickness materialis superior to the 12-in. and the to consist predonunantly of lower bainite, quarter section is superior to the center section. some upper bainite, although the amount of ti The results of the drop-weight testa confirm the formation to upper bainite is significantly over-all results of the Charpy impact tests as the than occurred in the A542 steel. The occurr steels show the same relative behaviorin both tests. of substantial spheroidization during tempe The NDT temperatures are slightly higher than and stress relieving is apparent from the m the Charpy 15 ft-lb transition temperature for structures of the three alloy steels, but differe A533 Grade B, A542 and A543, as indicated by the in microstructure between the specimens sl. higher NDT "fix" energy listed in Table 4, while cooled and rapidly cooled from stress relie , for A212 Grade B the NDT temperature is lower are not revealed by the light microscope, . than that for the 15 ft-lb criterion in the Charpy though a substantial difference in Charpy im test- behavior exists for these two conditiens. Fatigue Tests Cornparison of Ught.and Heavy-Section Behavior The fatigue test data obtained for the four steels It may be helpful to compare the propertii e are found in Table 6 and Figs. A21 to A24. The the four steels m the heavy-section sizes stu response of the four steels to fatigue conditions *".the program with the properties which were follows the pattern normally expected oflow-alloy tamed in previous programs for these steel gr high-strength steels. The higher-strength steels treated to represent quenched and tempered, have superior fatigue resistance in the 100,000 n rmalized and tempered, plates of relatively cycle failure region, while the lower-strength but section- Figures 16 and 17 summarize the te more ductile steels are superior in the low-cycle and Charpy test properties representative of p_ regiota. The levels of fatigue life attained in ranging from less than 1-m. to lo-m. thicknes these tests are comparable to those found in equal- the basis of cooling rate from austenitizmg. I strength lighter-section plate. the most part the tensile properties show a gra i loss of strength as thickness is mereased. m restructures notch toughness uniformly decreases with gre thickness; but A212 and A543 show a progree Tre microstructures of the four project steels loss, while A533 and A542 sustain most of the are ssen in Figs.12 to 15. The A212 Grade B steel of toughness as sections are increased to abo-(Fir,.12) consists of fairly coarse aggregates of in., above which relatively little change is incu: fer ite and pearlite, with the difference in cooling rate from austenitization resulting in no significant difference in microstructure. Tempering and Summary stress relieving resulted in some spheroidization of The results of the study of the four he. the pearlitic carbides. The microstructure of the section steels can be summarized as follows: A533 steel iFig.13) consists largely of ferrite and 1. There were no important changes in strer. low temperature transformation products. re- notch toughness, or fatigue resistance produce, flecting the microsegregation occurring during the reduction of cooling rate during quenc. cooling, with the enriched austenite remaming when the section size is increased from 6 in. te l after the ferrite precipitates finally transforming to in. in A212 Grade B, A533 Grade B, A542 I areas of high-carbon high-alloy martensite or A543 steels tested in the quenched, tempered bainite. The ferrite precipitation and resulting stress relieved condition. microsegregation is markedly more pronounced at 2. The property most affected by increase o: the 12-in cooling rate than at the 6-in. cooling rate. section thickness from 1-in. to the 6 to 12 in. r: The microstructure of the A542 steel iFig.14i is notch toughness. Rises of 50 to 100* F in tr: Table 6-Mastic Fatigue Resistance of the Heavy-Section Steels Total semin mngeJe O
, in. Crack Failu.=
Ster! Condttion 5000 cc 10.000 cc 50.000 cc 5000 ne 10.000 cc 100.00C A212B 12 in. Center and quarter chem. 0 75 0 60 0.36 1.00 0 92 0 3E A333B 6 in. and 12 in. eenter and quar:er chem. 0 71 0 59 0 37 0 52 0 68 0. 4: A542 12 in. Center and quarter chem. 0 50 0 69 0 50 0 95 0 79 05 j A543 12 in. Center and quarter chem. O ~9 0 65 0 50 0 96 0 TS 0 45 i y ... m s - ., s... o 0004 016
l i p n ei . ca.n ri .! aaus u n , .c. co.as rt .: a s n ,s <o.asari .) assa ta i m .t <e.as*ri .) f5 J4 I' W '~. M
" arI y f,' .
', k,l Rfd 7' '
=
f'2M[MbN e E jL ' Q **'u.'L 'b o sa %
)
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' ' $ Y .Y 4 5,AM t$ t$a *R
- b.
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s' * *
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- ' k
, 7 ;. 4.I- ,9 g]- f' ~
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- v.wA.. k_. ._ 4
,- , 2 . ...,. Ei iMgjiK22 ' I N '.k$V zy -
1 -4 M;i .
; ;::c 7:::::r iN%(I[b3 e
&a -
,J ::"
, 0.y
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- n. ;
, . =in .
1
,d.<
iM g*; .- qQ M'.2:
-r FAW f f ' 71 . . 4 aw %
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- h. ., ; h. $..-
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-' d' h -* #
Fig.14-The microstructure of AS42 (Nital etch, X 500)
.12-The microstructure of A2128 (Nital etch. x 5J0)
,i . <o.n ri .) aus u i .i.. <e.u ri .: * == .i.a ca.u r,.a.) uo u i- iu. ( .u ri .-
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.13-The microstructure of A5338 (Nital etch. X 500) Fig.15-The microatructur ital . 500)
,y (, .') s'; ' Thick Section Steel.<
o
12 o
, 12 0 Co- " og y e c -
~ . s g ..
7,,,,3,,,,,.- %-
;.m- .
e_o % .o.~
;m 60- ~ w O . 60 g
g 40-20-
, fed Strongm_ _
a . - 40-20- AS43 0 A542 iP- o I
- f. e so- =j. . F 4 30. l ..
- p .
4 of. 8 - 3 . g.-oo. h : 42r2 a,.co s [ 23n **
. .Temoared an c co. .../ .e. .croces croes 4 ; -'5
" 7~'~
0 2 4 6 8Quencned C I2 m 0 2 4 6 e o r2 m 16 ed Tempered Pictslhonees-m "b 2 4 6 8 to 12 m o 2 4 6 a k r2 Queneted ed rampered Plare Thdness-in Fig.16--The strength and toughness of A2128 an,2 A533 as in. Fig.17-The strength and tougnness of AS42 and AS41 fluenced by simulated plate thickness. fluenced by simu!ated plate thickness tion temperature were observed in these steels. Acknowledgment Fortunately, the alloy steels display transition temperatures below -10* F even in heavy sec- The authors are grateful to the members ( tions. The notch toughness of the A543 steel hiaterials Division of the Pressure Vessel Res was rnarkedly superior to that of the other steels Committee for their advice and guidance, a: treated at coch,ng rates correspondmg to the thick- PVRC for support of the investigation. nesses of either 6 or 12 m. wish also to express their appreciation to the Fi
- 3. The fatigue properties of the steels matched Wheeler Corp. which contributed extensive those of steels with similar tensile properties vices in the preparation of the test plates.
developed in lighter sections. The allowable strain range for a fatigue life of 100,000 cycles
/
s
} correlated well with tensile strength, while the strain range for 5000 cycles appeared to be related principally to the ductility of the steel (as observed in previous work). References
- 4. The elevated-temperature tension tests indi- n. G,
- e. J. H., and Sht. R. D "The Performance of High4 cated about the same characteristics in these steels $1s"d V M f,s"""
8*""" ' ""' '" 8' '' " as those observed in thin-gage steels, including the 2 G'a's. J. H and Stout. R. D.. "Pmporties and W.idability o strength Pressure.Vesses Steele a H.evy Sections." Duf.,36 (3) R strain-aging p. enornena in the 400-800* F tempera- suppi tst io ist 1967 ture range. For A533 Grade B and A54o., the 3. Green. J. H., Katteamp. E. H., and stout. R. D "Efrees o T,.tment on th. w,,, t,uem,e .nd e,o,., time of e,s , ve en 6-in. thick plate material was superior to the 12-in. plate material at elevated temperatures to 1000* F.
"pf',;*i8j;T".8"p6 9,t*,11792 "8;,, ,,, 7,,,,,
rme,mment m em, rtie. of I.ow AUoy Steels m Heavy Thicknee
- o. hietallographic examination generally sub- Weidad Construction." nut 41 (lot. Ramsarek Suppi 433-e to 447-e
- s. xottcome, s. H c.nonico. D. A. and Stout. R. D " Prediction stantiated the small differences in properties ob- - Dr,d.'3e"">.'R.' '*** " * *
""h s"u ll*"$~"o 3s2* 1,'"2. " *"' '
served between specimens cooled at the rate to be 6. Smt. R. D.. "Hish.e4trength St.eis for Weided4tructures/ Se m. Rennerer suppi., 273.e to 283- 1960. expected m. a 6-in. section and those cooled to
- 7. e====. P. P.. .nd reuini. w. s "st.nd.rd u. shod to, sRt match a 12 .m. section. Weight Test." NRL Report s431.1962 Uruted states Naval Re taboruory, w..hmeton. D. c.
0004 018 O
- e. q r Thick Section Steels 9!
2 ... [
~
' i I
~ l ! i I f
" ~~T l i i j I i i l l -- l l
l l
#M n a-j l l l I
l l . ';
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, ... I- 1 1/M i li
//ydn.
i 1 e l . - -. , ,0,= l l - - l' l . '.f* I l , I l
' I I i . N '/S I i_3a. iaf.
i ,, ' /W I l A ,, i _jL' s'n . _ _ _ _ _ l y'if
- l .. .
.. . . =--- - -
m - m
%1-Charpy V-notch impact data for code stress relieved Fig. A4-Charpy V-notch impact data for code stress relieved A2128,6 in. plate, quarter location A2128,12 in. plate, center location
~
j ! l I l [ l ! I I I I f I i ! t i
~
- ~
i l[ l l ~/l l
- l ,I I j < i i l I. .
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l l ' /N . I I I/ i I, 2 i t/r 1 i il
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p^~~ i l' l~ i,' I l l
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. ## d _._. i ,, /M i e t- .
- ~__ _ _ _ l . M" .
I M* l . .-._ m - m A2-.Charpy V notch impact data for code stress relieved Fig. AS-Charpy V notch impact data for code-stress relieved A2128,6 in plate, center tocation A5338,6 in. plate. quarter location I
' ~
! l I l l --l . -.. I -.
i 1 l
= .
e i / ,,, I i ! I is: ti!*- ? 't i /l A j _ _ . . _ _ 1 / * < ?'l I 1 I ' Y' i g ,, [f I i l l l l W/ I 8
. /{ . - . l I l En' i ,, .# 1 i I
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.A ) { ,,._.._ ___ f6 l l l t
- ,xV. -
J _ . . J . H 1 se.' l l ri . _ __. , l gl.. l . _ _ _ _ m ~- m A3-Charpy V. notch impact data for code stress-relieved Fig. A6-Charpy V-notch impact data for code-stress-relieved A2128,12 in. plate, quarter location A5338. 6 in. plate, center location Thick Section Steels 0004 019
" ~
i l I i
.(.
~
, _ p. . _ _..
~
l ' I _i ! hg ,, i i i
,, i I
I i ./ i A j I /._' = j _ ._ _ fe 1 i er i I .
~ i, X I s. t [. . L.- i
,p . i . e.,v i ._ i us k
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. '.YsVn :
29 i I 1 I l .> &*> :- __ _ J _. . . _ __ , plt"'f/
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, . ._ , .- t . _
m ---c., Fig. A7-Charpy V. notch impact data for code. stress. relieved Fig. A10-Charpy V. notch impact data for code. stress.i A5338.12 in. plate, quarter location A542,6 in. plate, center tocation
~
~
l I
..{ -
f i
. V, _. ..- ..
. _ . ',/.~-. .
a- ' t- - J .__ . _ _ ._
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, 57 4dV _ *- ,, _ _ _ ! _
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_m - m I Fig. A8-Charpy V. notch impact data for code. stress.retieved Fig. All-Charpy V. notch impact data for code. stress-r [A5338.12 in. plate, center location A542,12 in. plate, quarter location
~
~
t l l 1 l l l l I I I i i i i i i I . l ( l ' I / I . i i /
.. .- i .I j -
. , . _ _ . . V7 I I J .J l /l g,
4' I i I I /I { ,, l
/ '* I
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i ___ ___.
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.- ' _ . _ - - i
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. i . . -._
m - m 1 Fig. A9-Charpy V notch impact data for code stress relieved Fig. A12-Charpy V notch impact data for code. stress.r 1 AS42,6 in. plate, quarter location A542.12 in. plate, center location t Thick Sectie Steels j . is,. t w 0004 020 t
_ ___ .. .. .[ ! !
._.. . . _ . l l l s{ i l 'l I __
i
- a. '
. _ - .. . l..l . N
- I .] .
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.. , l . = - . -
. . . o. . .= .. .
. = n e- -
.m -
m j A13-Charpy V. notch impact data for code stress relieved Fig. A16-Charpy V. notch impact data for code. stress. relieved j AM3. 6 in. plate, quarter location A543,12 in, plate, center location
} l '
l l I _ _ . ._ . . . _. . _ . _ . [.._ l
' I i V I l t .
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. . . . l j.- .- _ -
,j j i. =._
m - m A14.-Charpy V. notch impact data fer code. stress-relieved Fig. A17--Charpy V. notch impact data for stress relieved and air A543, 6 in. plate, center location cooled AS43 6 in. plate, quarter location f l
._ _ . . _ . l l i l 1 l
/ l l l e I .
- l / '
l ( I '
/. I
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.: 9 l l , 'e g*g
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- ... .. . - . _ _ _ _ J
.s-' _ _ .
I .. - - i .. . . .. . . .. s =. - m - m l A15-Charpy V. notch impact data for code-stress. relieved Fig. A18-Charpy V notch impact data for stress relieved and A543,12 in. plate, quarter le stion air cooled A543 6 in. plate, center tocation
" 3"""3"*
cs.. Mg 0004 021
- i. 6 . . . , . . , . .,,1 ..
, , p , ,.
, 6 ,,, . . , , ,
. ,, 2 i , . . o_
l Ill Ij i I lli liilli i O ..
/
Fl l l l l I 1 l u. i' +5J 'e - w< I
' ili ! 'lilii '
j *..-
,l. .
.- i ! i i
,4, 4 .o , ,m:
....m.,....,,m.,
a gj g j ; 3 ,; , . . i n ii 4 i i+.tn i enu i, f j j i j ,. II I I t illi i I i i ilill lI l i PSIIP i
. , . . , ,n . ., , . , ,
./hp i I ! ll f
& ,, pn j j Il , ,! l
,, i i
; i l il ji j 8
i II l1 Il ll I t ll l Il l i I *' P8,5*
- M l
j _ji .' '-* _- [- I ll.. . ll. . l. l l ll ll ll I l
.. -_ . .2. , . . . .
- <,4 ._ . .. . _ .._,
Fig. A19-Charpy V. notch impact data for stress relieved and air * * .'~~ U U. ~ cooled AS4312 in, plate, quarter focation Fig. A22-Rastic fatrgue data for heavy.section A533E l
~
_.. ._ __L i l , ' ! , , m; {. l i; t;li; ; ,ii4 , lilillF , n .,l h, i I llilii I i i ill li : l
/' l I
I ll!Illi U . l l lllll l I l lllll11 I j p . i i i ' - -
- tw ,
i +1 i i i
, ,,,i,
. . . - .. ...,.e . r m .,
^ L /* I " ' "' '"" ' "''
=
I '- 1'i i lii li lil ni i i l t ilii I ( M, I
. . . . . . . i , . . . .
s m' " 1 _ . . .. b.p y
. . l ..._
lli i 4 ' iii lI i 11 11 i 1 io" 11ll1 i i 1,- ye
+
- 1 l l ll I ilIllo ll I
llll11 i
..s Fig. A20-Charpy V notch impset data for stress reiieved and air ' ' " * " " " ' " " *"'" ~~
cooled 54312 in. plate. center location Fig. A23--Pfastic fatigue data for heavy section AS4: b iiiN i i i ,6 ,i i i e i ,i k i !!.i . ' i i i ..t..a . l IN. _ lll M Il!! Il l lll! ll l ' I l III Il I I I I I Iil Hl I
- i..
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*l
- li l l lilli i l l l1I 11 i1 l Niilli' !ii } ll I IIllI ll l l 111H II l I f ilill I
, , , i . .j i,o , . . .
...i. . , ...i i! i iiiin i e i 16 si i I s t li! ti .. ' ' I I !' h' 8 ' ! ' ii h I i 1 8 ' ! !' '
ll l l lilii l I l ll Il i i !ill! Ii l ! I l II il II i i lill I !I 'llit f f ! lIlllll l 1 l ll III l lllllb I! !! ! II Ib l I!. ! O - - c :.=- .- - u = =. 'm = := = =.
- = =
i Fig. A21-P!astic fatigue data for heavy section A2128 Fig. A24--Plastic fatigue data for heavy section AS4: Thick Section Steels l 0004 u22 1 l
Docket 50-289 Supplement No. 2 November 6, 1967 APPENDIX 3 B&W DATA TYPICAL NDTT DATA FOR SA-302 B PLATE MODIFIED TO CODE CASE 1970 P ARAGRAPH 1
- 1. Material from Shell plate 6-1/4" thick l Aust, Chemistrv ;
C .18 1675-1725F, 6-1/4 hours, B.Q.6-1/4 hours, Aust. 1600-1650F, Mn B.Q.1.08 Temper 1175-1225F, 6-1/4 hours, B.Q. P .005 i Lab S.R. 1100-1150F, 18 hours, F.C. S .012 i Si .24 Cr .16 Ni .44 , s All specimens longitudinal to final Mo .45 _) rolling direction. Cu .17 1 i A. As Tenrered Procerties - Surface Charry Tests Test Temo. Ft-Lbs 'at. Ext.. Mils Est. T S OF 65 70 50 51 30, 30,
-30F 61,100,,100 52, 48, 39, 62,, 68 25,100,1
-30F 69, 85, 94 50 60, 61 25, 80,
-60F 53, 67 38, 47 13, 30
-90F 19, 33, 48 15, 27, 33
, 3, 5, i B. As Temuered - Just Below 1/kT Procerties Charry Tests Test Temo. Ft-Lbs Lat. Err., Mils Est. T5
+40F 48, 63 69 40, 54 30, 40 I
+10F 55, 56 60 43, ,47, 25, 25,,
-20F 30, 33 34 25, 3 26 5, -
)
t
-40F 10, 20, 30 7,17,21 0, -
(2) 0004 023 31
O
- 2. Material.from Shell plate 9-3/4" Thick Mn-Mo-Ni Plate (A533B)
Air Cool from 1675-1725F Quenched from 1675-1725F Tempered from 1200-1225F, Air Cool . Stress Relieved 60 hours 1100-1150F, Furnace Cooled A. As Temuered Procerties - Surface Charov Tests Test Temo. Ft-Lbs
-80F 7, 9,
-50F 10 22 37
-20F 28,, 45,, 45
+10F 35, 60, 62
+40F 70
+300F 134,83134 B. As Temeered - Just Below 1/bT Procerties h;
Charov Tests Test Temo. Ft-Lbs.
-40F 16
-20F 11, 14, 29 0F 18, 20, 28
+10F 25, 32, 37, 38, 42, 42
+40F 47, 50 55
+300F 130,13l i
C. A_e Temuered - Just Below 1/2T Procerties Charov Tests , Test Temu. Ft-Lbs. l
-40F 11 l -20F 13, 16, 18 l +10F 21 33 35 1 +40F 38, 46,,. 48, 35, 40, 42 m
l; '{
; i; ;,, ,
+300 F 127,120 W
/
0004-024
Docket 50-289 Supplement No. 2 November 6,1967 QUESTION An estimate of the effect of an initial vessel temperature higher 11.3 than that assumed in the analysis on the extent! of yielding and de-formation of the vessel. ANS*JER The analysis used an initial vessel vall temperature of 603 F. I sensitivity analysis considering various initial vall temperatures, up to 1,500 F, has also been ecmpleted. The results indicate that 31 per cent of the material in the inner portion of the vessel vall thickness has yielded at 1,500 F. The analysis with an initial vall temperature of 603 F indicated that l!4 7 per cent of material in the inner portion of the vessel vall thickness had yielded. Thus, the sensitivity analysis !.ndicated an increase in the ductile yielding of 16.3 per cent when the initial vall temperature was assumed to be 1,500 F. 0004 025 (O O 11.3-1
Docket 50-289 Supplemenc No. 2 November 6,1967 QUESTION An estimate of the maximum allowable pressure stress, when combined 11.4 with other stresses present in the vessel, which could be tolerated without failure. AEWER The maximum pressure that 38M considered was 600 psi. This is based on the fact that the core floodin6 tanks vill not operate until the reactor vessel pressure is at or belov 600 pai. This internal pres-sure would only increase the depth of ductile yielding from 14 7 to 17 5 per cent of the wall thickness. 0004 026 (O O u.4-1
() Docket 50-289 Supplement No. 2 November 6,1967 QUESTION An estimate of the maximum neutron flux exposure (nyt) of the vessel 11.5 that could be tolerated without vessel failure. AN.SWER The analysis considering the brittle fracture mode assumed the con-servative approach in that the material would behave in a ecmpletely brittle manner, and thus the lower threshold stress was used for comparison with the imposed stresses. Therefore, the analysis as performed by B&W is insensitive to increased flux levels. 0004 027 ((13) v i l \~ > 11.5-1 l L
l Docket 50-289 l O Supplement No. 2 November 6,1967 l QUESTION The effect of potential local penetrations present in the vessel ' 11.6 cladding, exposing the base metal to the coolant, en the results of the analysis. ANSWER Our analysis did not consider the beneficial effect of cladding. In. - regions where local penetrations in the clad surface are postulated to be potential occurrences, the actual temperature profile across the thickness vill be virtually unchanged (because of the small dif-ference in conductivity and the small thickness of clad), and the stresses at these points will be as they were originally calculated. i 1 0004 028 O . (::) 11.6-1
Docket 50-289 Supplement No. 2 November 6,1967
- QUESTION The number of thermal shock cycles, induced by ECCS operation, that 11.7 the vessel could withstand at the end of its fatigue life.
ANSWER B&W does not consider the ECCS operation as a cyclic occurrence. However, plastic deformation (ductile yielding) might safely be re-pested without the integrity of the vessel being violated. If ECCS operation should occur when the vessel is in the brittle region, then further operation of the unit would be prohibited until an ex-haustive examination of the vessel has been completed. 0004 029 (O l l O 11.7-1 l 1 i l
Docket 50-189
'O- Suppleme t No. 2 November ;,1967 QUESTION Experimental data on the thermal shock effects in thick plates unc 11.8 stress, tested below the NDT temperature.
ANSWER The demonstration of the adequacy of the reactor vessel to accomme the thermal gradients, developed upon injection of emergency coola following a loss-of-coolant accident, is a unique application of f i ture mechanies and analysis involving stressed plates, thermal gra ents, crack triggering by quenching, transition temperature gradie and notch geometries. Data relative to the individual parts of this problem are availabi This data exists in the form of the Robertsen Gradient Tests, rout practice in quenching heavy section shell forgings, and the transi temperature correlation verk carried out by Pellini and Pu:ak at E Also there is extensive work which is being conducted in the fract-mechanics field by such research establishments as CRNL, Westingho-Research, and Universities. All of this data was valuable in deve. ing the conservative methods which were used in the analysis as pr. i sented. i O 0004 030 0 11.8-1
Docket 50-289 O Supplement No. 2 November 6,1967 QUESTION An evaluation of the capability of the safety injection nozzles and 11 9 accumulator piping to withstand the transient. ANSWER B&W is considering the effect of ECCS operation in the analysis of the safety injection nozzle and accumulator piping. As socn as this analysis is completed, the results of the analysis will be presented. i 1 0004 031
.O I
l l O 11.9-1
\ \ l i ! Docket 50-289 Supplement No. 2 November 6,1967 4tESTION An evaluation of the effects of this transient on the core barrel I 11.10 and other internals with regard to assurir4 that distortion vould not restrict the flow path of the emergency core coolant. AM5WER A detailed analysis of the effects of emergency core coolant flow or the reactor internals has not been perfomed. However, preliminary analysis and previous similar experience indicate the following: 1 The reacter internals are constructed of Type 304 stain- I less steel, and therefore are not subject to brittle fracture at temperatures of. interest (some less of im-pact strength has been observed at about -320 F). Further, the material is sufficiently ductile that many quenches of the expected magnitude can be withstood without ini-tiation of a crack, or propagation of an assumed existing crack. Consequently, thermal shock fracture of { the internals is not considered credible. ) The reactor internals are being designed to conservative stress and deflection limits, so that failure or large deforr;ations of the in-ternals due to blevdown loadings vill not occur. A further degree of conservatism is provided by coolant inlet flov
.O. deflector vanes in the region of the emergency coolant inlets.
These vanes are attached to the core support shield, and vill pre-vent that shield frem apprcaching within about 5 in. of the vessel ID in the region of the emergency coolant inlets. , 0004 032 O 11.10-1
Docket 50-289 Supplement No. 2 November 6,1967 l QUESTION FISSION PRODUCT RELEASE FROM FUEL 12.0 12.1 Provide the details of the method of calculating the primary coolant activity levels for the one percent failed fuel case, including pur-ification cycling of primary system, fission product release as-sumptions frem the failed fuel, effects of burnup and fuel tempera-ture on fission product release from fuel, etc. Provide all formu-lae, assumptions, and justifications for same. Justify the cleanup system reduction factors stated in the PSAR. ANSWER Activity Levels Activity levels in the reactor coolant system resulting from fission product leakage through clad defects are determited with the use of escape rate coefficients. These coefficients represent the fraction of the activity in the fuel that is released, per unit time, to the coolant. Values of these coefficients, as derived from experimental data, are reported in the literature.(1-5) These experiments, in-volving purposely defected fuel elements in pressurized water loops, have been performed for a variety of fuel conditions. For a given isotope, the results yield a vide range of values for the escape rate coefficient even under sLnilar operating conditions. For the O' calculation of coolant activity levels, values of the escape rate coefficients ver': deternined from these data. In regard to fuel tem-perature and buruup, no assumptions were mada as to the location of clad defects within the core. The coefficients were conservatively chosen from the available data in an effort to account for the worst fuel conditions. The values are shown in Table 11-2 of the PSAR. Calculations of the coolant activity were performed with BURP,(6) a Babcock & Wilcox Company digital computer coda. This code so;ves ' the differential equations for a five-member radioactive chain for buildup and decay in the fuel, release to the coolant, removal frem the coolant by purification or leakage, and collection in a holdup system. The basic equation for the buildup of a radioactive nuclide, Ng, in { the fuel is ' l dK I g =RY+FA'Np-c$-AN7- aN g { 0004 033 s P t s, 12.1-1
Ng = concentration of a radioactive nuclide R = fission rate, fissions per sec ' Y = independent fission yield of N f A'Np=activityofprecursorinfuel, dis /sec ' F = fraction of precursor which decays to N g
~
09 = neutron capture rate in N g, sec A = decay constant of Ng , sec-1
~
a = escape rate coefficient of N g, sec The equation for a radioactive nuclide in the coolant, N , is giver by dN
= aN + FA'N' - AN - SN - yN f
A'N' = activity of precursor in coolant, dis /see t S = removal of N by purification, sec~1
~
y = removal of N by leakage of plate-out, sec In the purification or holdup system the activity of a nuclide, N , is given by P
/
dN dt = SNc + FA'N'p
- ANp- aN p A'N'E
= activity of precursor in purification or hold-up system, dis /see a = removal of N from purification or holdup sys-tem, see-1 P Using the above equations, activities can be computed for more than 200 radioactive fission products with as many as 100 consecutive re actor operating and shutdown periods. The activity of each nuclide in the fuel, coolant, and holdup or purification systems is compute l at each time step.
l In the coolant activity calculations, the assumptions regarding operating times, purification flow, and activity removal are given l on Page 11-1 of the PSAR. Activity concentrations in the coolant are shown in Table 11-3 of the PSAR. ti f :\fif. (,i. e a v $; 0004 034 9 12.1-2
- l l
ANSWER [leanun System Reduction Facters j As stated in Section 11.1.1.3 (page 11-24) the activity concentratio in the coolant, shown in Table 11-3 vere based on the centinuous
- purification or cleanup of one reactor coolant system volume per da
with zero removal efficiency for krypton, cesium, and xenon, and 99 l per cent removal efficiency for all other nuclides, Krypton and xenon, being noble gases, are not removed by ion exchange. The mixed resin bed in the purification demineralizer will normally op-erste in the potassium-borate forn since potassium hydroxide is use for coolant pH control and since boric acid is used for chemical shim control. Laboratory experiments (7) and operating experience (0 indicate that potassium-saturated resins vill not effectively re ~ move cesium. The referenced laboratory experiments also indicate that significant removal efficiencies can be obtained for strontium and barium, and it appears that a removal efficiency of 99 per cent should be reasonable for these nuclides. The referenced experiments further show that yttrium has low remova. efficiencies in potassium-saturated resins, and there is additional evidence that molybdenum has low removal efficiencies. Removal ef-ficiencies of 99 per cent vere assumed to establish the activity levels to yttrium and molybdenum in the reactor coolant activities listed in Table 11-3 of the PSAR. If no removal of yttrium and molybdenum is assumed, the activities in Table 11-3 vill increase. However, the effect on activity concentrations released in the cir-culating water discharge will be only a small increase in these val. ues. The referenced operating experience shows that borated resin O' is rery, effective in removing iodine, and that a 99 per cent remova; effidiencytforythis nuclide should be satisfactory. 0004 035 O
- , 12.1-3
REFERENCES (1) Frank, P. W. , ei ajl
~
Radiochemistry of Third PWR Fuel Material Test - X-Loop NRX Reactor, WAPD-TM-29, February 1957. (2) Eichenberg, J. D., e_t, t d., Offects of Irradiation on Bulk UO , WAPD-183, 2 October 195T. (3) Allison, G. M. and Robertson, R. F. S., The Behavior of Fission Product. in Pressurized-Water Syste=s. A Review of Defect Tests en UO2 Fuel Ele-ments at Chalk River, AECL-1338, 1961. (h) Allison, G. M. and Rce, H. K. , The Release of Fission Gases & Iodines From Defected UO2 Fuel Ele =ents of Different Lengths, AECL-2206, June 19 (5) Fletcher, W. D. and Picone, L. F. , Fission Products from Fuel Defect Tes-at Saxton, WCAP-3269-63, April 1966. (6) Perry, J. 3. and Alcorn, J. M., BURP - A Ccmputer Program for Calculatin, Buildup and Decay of Radicactive Fissica Products, BAW-TM hhh, November 1966. (7) Simon, G. P. , e,t_ aj_. , The Perfor=ance of Base-Form Ion Exchangers for pH Control and Removal of Fission Products from Pressurized Water Reactors, WAPD-CDA(AD)-528, April 1959 (8) Weisman, J. and 3artnoff, B. , The Saxton Chemical Shim Experiment , WCAP-2599, August 1964. < 0004 036 y t ,, , r,. . . .
.io:.
o 1 S 12.1 h
Docket 50-289 (~' Supplement No. 2 November 6,1967 QUESTION Provide a plot of fuel temperature versus the volumetric fraction of 12.2 the total fuel at that te=perature in the core at end-of-life condi-tiens. Describe the method of calculation, state all assumptiens, and provide typical radial pin profiles and the gross peaking factor used. ANSWER A plot of fuel temperature versus the volu=e fraction is shown in Figure 12.2-1 at 100 per cent power. A typical fuel cycle power dis tribution for equilibrium cycle, end-of-life conditions was used. The bundle average powers shown in Figure 12.2-2 vere used to obtain the fuel red heat rates. A sy= metrical ecsine axial power distribu-tion with a 1.5 max / avg value as shown in FSAR Figure 3-8 vas used t predict the axial distribution. It was assumed that 97.3 per cent c the pcVer is generated in the fuel. The fuel rods were divided inte ik axial and 10 rt. dial segments to obtain the temperature distributi for this analysis. The heat rate for every fuel red in the core was increased by a local peaking factor of 1.05 to account for uncertain ties in the calculation of local peaks. This has the bulk effect of raising reactor power to 105 per cent. The fuel temperature calculation model is outlined in PSAR Section 3.2.3.2.h g (page 3-h8). The fuel conductivity curve identified as OEAP-h62h in Figure 3-h2 vss used to provide censervative values for g- fuel conductivity in the hottest regions of.the core at the end of s life. The max.imum powers occurred in fuel assemblies with one and two cycles of operation as shown in Figure 12.2-2, and the assemblie with the highest burnup did not exceed 1.0h3 times the average power for the case analyzed. The calculation shown in Figure 12.2-1 was made by grouping all segments of fuel by temperature and assigning a conservative value for the fuel-to-clad heat transfer coefficient fc typical end-of-life conditions. This is illustrated by the tempera-ture profiles shown in Figure 12.2-3 Typical fuel-to-clad heat tra fer coefficients used were 25 ) and L80 Btu /hr-ft2-F for 6 and 10 kv/ heat rates respectively. The corresponding beginning-of-life coeffi 2 cients are about 630 and 9ho Btu /hr-ft -F at 6 and 10 kv/ft heat rat The temperature profiles are based on a uniform heat generation rate in the fuel. This is a conservative assumption since a larger frac-tien of power is generated at the outer periphery of the fuel than i the center region. 0004 037 12.2-1 i 1 I
O. 3,300 2,900 i 2,500 - 3 2 a
- i
% 2, 10 0 0 \
l,700 I,300 0 20 14 0 60 80 iOO Vol. Fraction of Total Fuel, f. (at or above Fuel Temperature) 0;
!.c 0004 038 l FUEL TEMPERATURE VERSUS TOTAL FUEL VOLUME FRACTION FO R E QU I L I B R I UM CY CL E AT EN D OF L F I G UR E _l 2.2 - 1
's
---3 --
-3 --2 --3 -
-2 ---3 ---3 '-l 0.780'- 0.830 0.839 0.836 1.043 0.986 0.995 1.008 Nr i 3 2 3 i !
s 3li 0.987'- 0. 7 38 0.79 4 1.054 1.00 5 1.311 0.976 l
\r3, 2 2 3 2 I 0 34' '.. 1.097 1.182 1.0 25 1.082 0.781 Ne 2 s 2 2 i 1.202 \ 1.148 1.09I l.034
\
\ s 3s i I l.043\ 1.218 0.798
'x
'&j# c Nurber Cycl e* Burned 2
0.3 I lh N Assembly P/P l l 9 rom. 0004 039 i ! (PICAL REACTOR FUEL A33EM8LY POER DISTRIBUTION S i END OF LIFE. EQUIL18RIUM CYCLE CONDITIONS FCR
'8 CORE.
FIGURE 12.2-2
Fu I
- Clad .
3,000 10 kw/ f t 2,600 s N 2,200 6 kw/ f t 1,800 I N l l,400 i 1.000 l 580 F Tavg Coolant i 0 .04 .08 .12 . 16 . 20 Fuel Rod Radius, in. l 0004 040 0 FUEL R00 TD4PERATURE PROFILE 6 ANO 10 KW/ FT FIGURE 12.2-3 1}}