ASTM E2760-2010e1 Standard Test Method for Creep-Fatigue Crack Growth Testing《蠕变疲劳裂纹扩展试验的标准试验方法》.pdf

《ASTM E2760-2010e1 Standard Test Method for Creep-Fatigue Crack Growth Testing《蠕变疲劳裂纹扩展试验的标准试验方法》.pdf》由会员分享，可在线阅读，更多相关《ASTM E2760-2010e1 Standard Test Method for Creep-Fatigue Crack Growth Testing《蠕变疲劳裂纹扩展试验的标准试验方法》.pdf（19页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: E2760 101Standard Test Method forCreep-Fatigue Crack Growth Testing1This standard is issued under the fixed designation E2760; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in pare

2、ntheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.1NOTE3.1.19 was editorially revised in December 2011.1. Scope1.1 This test method covers the determination of creep-fatigue crack growth properties of nominally

3、homogeneousmaterials by use of pre-cracked compact type, C(T), testspecimens subjected to uniaxial cyclic forces. It concernsfatigue cycling with sufficiently long loading/unloading ratesor hold-times, or both, to cause creep deformation at the cracktip and the creep deformation be responsible for e

4、nhancedcrack growth per loading cycle. It is intended as a guide forcreep-fatigue testing performed in support of such activities asmaterials research and development, mechanical design, pro-cess and quality control, product performance, and failureanalysis. Therefore, this method requires testing o

5、f at least twospecimens that yield overlapping crack growth rate data. Thecyclic conditions responsible for creep-fatigue deformation andenhanced crack growth vary with material and with tempera-ture for a given material. The effects of environment such astime-dependent oxidation in enhancing the cr

6、ack growth ratesare assumed to be included in the test results; it is thus essentialto conduct testing in an environment that is representative ofthe intended application.1.2 Two types of crack growth mechanisms are observedduring creep/fatigue tests: (1) time-dependent intergranularcreep and (2) cy

7、cle dependent transgranular fatigue. Theinteraction between the two cracking mechanisms is complexand depends on the material, frequency of applied force cyclesand the shape of the force cycle. When tests are planned, theloading frequency and waveform that simulate or replicateservice loading must b

8、e selected.1.3 Two types of creep behavior are generally observed inmaterials during creep-fatigue crack growth tests: creep-ductileand creep-brittle (1).2In creep-ductile materials, creep strainsdominate and creep-fatigue crack growth is accompanied bysubstantial time-dependent creep strains near t

9、he crack tip. Increep-brittle materials, creep-fatigue crack growth occurs atlow creep ductility. Consequently, the time-dependent creepstrains are comparable to or less than the accompanying elasticstrains near the crack tip.1.3.1 In creep-brittle materials, creep-fatigue crack growthrates per cycl

10、e or da/dN, are expressed in terms of themagnitude of the cyclic stress intensity parameter, DK. Thesecrack growth rates depend on the loading/unloading rates andhold-time at maximum load, the force ratio, R, and the testtemperature (see Annex A1 for additional details).1.3.2 In creep-ductile materi

11、als, the average time rates ofcrack growth during a loading cycle, (da/dt)avg, are expressedas a function of the average magnitude of the Ctparameter,(Ct)avg(2).NOTE 1The correlations between (da/dt)avgand (Ct)avghave beenshown to be independent of hold-times (2, 3).1.4 The crack growth rates derive

12、d in this manner andexpressed as a function of the relevant crack tip parameter(s)are identified as a material property which can be used inintegrity assessment of structural components subjected tosimilar loading conditions during service and life assessmentmethods.1.5 The use of this practice is l

13、imited to specimens and doesnot cover testing of full-scale components, structures, orconsumer products.1.6 This practice is primarily aimed at providing the mate-rial properties required for assessment of crack-like defects inengineering structures operated at elevated temperatures wherecreep defor

14、mation and damage is a design concern and aresubjected to cyclic loading involving slow loading/unloadingrates or hold-times, or both, at maximum loads.1.7 This practice is applicable to the determination of crackgrowth rate properties as a consequence of constant-amplitudeload-controlled tests with

15、 controlled loading/unloading rates orhold-times at the maximum load, or both. It is primarilyconcerned with the testing of C(T) specimens subjected touniaxial loading in load control mode. The focus of theprocedure is on tests in which creep and fatigue deformationand damage is generated simultaneo

16、usly within a given cycle.1This test method is under the jurisdiction of ASTM Committee E08 on Fatigueand Fracture and is the direct responsibility of Subcommittee E08.06 on CrackGrowth Behavior.Current edition approved May 1, 2010. Published July 2010. DOI: 10.1520/E2760-10E01.2The boldface numbers

17、 in parentheses refer to the list of references at the end ofthis standard.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.It does not cover block cycle testing in which creep and fatiguedamage is generated sequentially. Data which m

18、ay be deter-mined from tests performed under such conditions may char-acterize the creep-fatigue crack growth behavior of the testedmaterials.1.8 This practice is applicable to temperatures and hold-times for which the magnitudes of time-dependent inelasticstrains at the crack tip are significant in

19、 comparison to thetime-independent inelastic strains. No restrictions are placedon environmental factors such as temperature, pressure, hu-midity, medium and others, provided they are controlledthroughout the test and are detailed in the data report.NOTE 2The term inelastic is used herein to refer t

20、o all nonelasticstrains. The term plastic is used herein to refer only to time-independent(that is non-creep) component of inelastic strain.1.9 The values stated in SI units are to be regarded asstandard. The inch-pound units in parentheses are for informa-tion only.1.10 This standard does not purpo

21、rt to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:3E4 P

22、ractices for Force Verification of Testing MachinesE83 Practice for Verification and Classification of Exten-someter SystemsE139 Test Methods for Conducting Creep, Creep-Rupture,and Stress-Rupture Tests of Metallic MaterialsE177 Practice for Use of the Terms Precision and Bias inASTM Test MethodsE22

23、0 Test Method for Calibration of Thermocouples ByComparison TechniquesE399 Test Method for Linear-Elastic Plane-Strain FractureToughness KIcof Metallic MaterialsE467 Practice for Verification of Constant Amplitude Dy-namic Forces in an Axial Fatigue Testing SystemE647 Test Method for Measurement of

24、Fatigue CrackGrowth RatesE1457 Test Method for Measurement of Creep CrackGrowth Times in MetalsE1823 Terminology Relating to Fatigue and Fracture Test-ingE2714 Test Method for Creep-Fatigue Testing3. Terminology3.1 Terminology related to fatigue and fracture testingcontained in Terminology E1823 is

25、applicable to this testmethod. Additional terminology specific to this standard isdetailed in section 3.2. For clarity and easier access within thisdocument some of the terminology in Terminology E1823relevant to this standard is repeated below (see TerminologyE1823, for further discussion and detai

26、ls).3.1.1 crack-plane orientationdirection of fracture orcrack extension relation to product configuration. This identi-fication is designated by a hyphenated code with the firstletter(s) representing the direction normal to the crack planeand the second letter(s) designating the expected direction

27、ofcrack propagation.3.1.2 crack size, a Lprincipal lineal dimension used inthe calculation of fracture mechanics parameters for through-thickness cracks.3.1.2.1 DiscussionIn the C(T) specimen, a is the averagemeasurement from the line connecting the bearing points offorce application. This is the sa

28、me as the physical crack size, apwhere the subscript p is always implied.3.1.2.2 original crack size, aoLthe physical crack sizeat the start of testing.3.1.3 specimen thickness, B Ldistance between the par-allel sides of the specimen.3.1.4 net thickness, BNLthe distance between the rootsof the side-

29、grooves in side-grooved specimens.3.1.5 specimen width, W Lthe distance from a referenceposition (for example, the front edge of a bend specimen or theforce line of a compact specimen) to the rear surface of thespecimen.3.1.6 force, P Fthe force applied to a test specimen or toa component.3.1.7 maxi

30、mum force, PmaxFin fatigue, the highestalgebraic value of applied force in a cycle. By convention,tensile forces are positive and compressive forces are negative.3.1.8 minimum force, PminFin fatigue, the lowest alge-braic value of applied force in a cycle. By convention, tensileforces are positive a

31、nd compressive forces are negative.3.1.9 force ratio (also stress ratio), Rin fatigue, thealgebraic ratio of the two loading parameters of a cycle. Themost widely used ratio is as follows:R 5minimum loadmaximum load5PminPmax(1)3.1.10 force range, DP Fin fatigue loading, the alge-braic difference bet

32、ween the successive valley and peak forces(positive range or increasing force range) or between succes-sive peak and valley forces (negative or decreasing forcerange). In constant amplitude loading, the range is given asfollows:DP 5 Pmax Pmin(2)3.1.11 stress intensity factor, K, K1,K2,K3,KI,KII,KIII

33、FL-3/2the magnitude of the mathematically ideal crack tipstress field (a stress-field singularity) for a particular mode in ahomogeneous, linear-elastic body.3.1.11.1 DiscussionFor a C(T) specimen subjected toMode I loading, K is calculated by the following equation:K 5PBBN!1/2W1/2fa/W! (3)f 5F2 1 a

34、/W1a/W!3/2G0.886 1 4.64a/W! 13.32a/W!21 14.72a/W!3 5.6a/W!4! (4)3For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM websi

35、te.E2760 10123.1.12 maximum stress intensity factor, KmaxFL-3/2infatigue, the maximum value of the stress intensity factor in acycle. This value corresponds to Pmax.3.1.13 minimum stress intensity factor, KminFL-3/2infatigue, the minimum value of the stress intensity factor in acycle. This value cor

36、responds to Pminwhen R 0 and is takento be 0 when R # 0.3.1.14 stress-intensity factor range, DK FL-3/2in fa-tigue, the variation in the stress-intensity factor during a cycle,that is:DK 5 Kmax Kmin(5)3.1.15 yield strength, sYSFL-2the stress at which thematerial exhibits a deviation from the proport

37、ionality of stressto strain at the test temperature. This deviation is expressed interms of strain.3.1.15.1 DiscussionFor the purposes of this standard, thevalue of strain deviation from proportionality used for definingyield strength is 0.2 %.3.1.16 cyclein fatigue, one complete sequence of valueso

38、f force that is repeated under constant amplitude loading. Thesymbol N used to indicate the number of cycles.3.1.17 hold-time (th)in fatigue, the amount of time in thecycle where the controlled test variable (for example, force,strain, displacement) remains constant with time.3.1.18 C*(t)integral, C

39、*(t) FL-1T-1, a mathematical ex-pression, a line or surface integral that encloses the crack frontfrom one crack surface to the other, used to characterize thelocal stress- strain rate fields at any instant around the crackfront in a body subjected to extensive creep conditions.3.1.18.1 DiscussionTh

40、e C*(t) expression for a two-dimensional crack, in the x-z plane with the crack front parallelto the z-axis, is the line integral (4, 5).C*t! 5*GSW*t!dy T uxdsD (6)where:W*(t) = instantaneous stress-power or energy rateper unit volume,G = path of the integral, that encloses (that is,contains) the cr

41、ack tip contour,ds = increment in the contour path,T = outward traction vector on ds,u= displacement rate vector at ds,x, y, z = rectangular coordinate system, andT uxds 5= the rate of stress-power input into the areaenclosed by G across the elemental lengthds.3.1.18.2 DiscussionThe value of C*(t) f

42、rom this equationis path-independent for materials that deform according to aconstitutive law that may be separated into single-value timeand stress functions or strain and stress functions of the forms(1):5 f1t!f2s! (7)5 f3!f4s! (8)where, f1f4represent functions of elapsed time, t, strain, and appl

43、ied stress, s, respectively and is the strain rate.3.1.18.3 DiscussionFor materials exhibiting creep defor-mation for which the above equation is path-independent, theC*(t)-integral is equal to the value obtained from two, stressed,identical bodies with infinitesimally differing crack areas. Thisval

44、ue is the difference in the stress-power per unit difference incrack area at a fixed value of time and displacement rate, or ata fixed value of time and applied force.3.1.18.4 DiscussionThe value of C*(t) corresponding tothe steady-state conditions is called C*s. Steady-state is said tohave been ach

45、ieved when a fully developed creep stressdistribution has been produced around the crack tip. Thisoccurs when secondary creep deformation characterized by Eq9 dominates the behavior of the specimen.ss5 Asn(9)3.1.18.5 DiscussionThis steady state in C* does notnecessarily mean steady state crack growt

46、h rate. The latteroccurs when steady state damage develops at the crack tip.3.1.19 force-line displacement due to creep, elastic, andplastic strain V L the total displacement measured at theloading pins (VLD) due to the initial force placed on thespecimen at any instant and due to subsequent crack e

47、xtensionthat is associated with the accumulation of creep, elastic, andplastic strains in the specimen.3.1.19.1 DiscussionThe force-line displacement associ-ated with just the creep strains is expressed as Vc.3.1.19.2 DiscussionIn creeping bodies, the total displace-ment at the force-line, VFLD, can

48、 be partitioned into aninstantaneous elastic part Ve, a plastic part, Vp, and a time-dependent creep part, Vc(6).V Ve1 Vp1 Vc(10)The corresponding symbols for the rates of force-linedisplacement components shown in Eq 10 are given respec-tively as V, Ve, Vp, Vc. This information is used to derive th

49、eparameters C* and Ct.3.1.20 Ctparameter, CtFL-1T-1parameter equal to thevalue obtained from two identical bodies with infinitesimallydiffering crack areas, each subjected to stress, as the differencein stress power per unit difference in crack area at a fixed valueof time and displacement rate or at a fixed value of time andapplied force for an arbitrary constitutive law (5).3.1.20.1 DiscussionThe value of Ctis path-independentand is identical to C*(t) for extensive