1、Designation: E399 123Standard Test Method forLinear-Elastic Plane-Strain Fracture Toughness KIcofMetallic Materials1This standard is issued under the fixed designation E399; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the year
2、of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon () indicates an editorial change since the last revision or reapproval.This standard has been approved for use by agencies of the U.S. Department of Defense.1NOTE3.1.3 was editorially revised in May
3、 2013.2NOTENote 2 of Fig. A2.2 was editorially revised in October 2013.3NOTEEq A3.2 was editorially corrected in December 2013.1. Scope1.1 This test method covers the determination of fracturetoughness (KIc) of metallic materials under predominantlylinear-elastic, plane-strain conditions using fatig
4、ue precrackedspecimens having a thickness of 1.6 mm (0.063 in.) or greater2subjected to slowly, or in special (elective) cases rapidly,increasing crack-displacement force. Details of test apparatus,specimen configuration, and experimental procedure are givenin the Annexes.NOTE 1Plane-strain fracture
5、 toughness tests of thinner materials thatare sufficiently brittle (see 7.1) can be made using other types ofspecimens (1).3There is no standard test method for such thin materials.1.2 This test method is divided into two parts. The first partgives general recommendations and requirements for KIctes
6、ting. The second part consists of Annexes that give specificinformation on displacement gage and loading fixture design,special requirements for individual specimen configurations,and detailed procedures for fatigue precracking. Additionalannexes are provided that give specific procedures for beryl-
7、lium and rapid-force testing.1.3 General information and requirements common to allspecimen configurations:SectionReferenced Documents 2Terminology 3Stress-Intensity Factor 3.1.1Plane-Strain Fracture Toughness 3.1.2Crack Plane Orientation 3.1.4SectionSummary of Test Method 4Significance and Use 5Sig
8、nificance 5.1Precautions 5.1.1 5.1.5Practical Applications 5.2Apparatus (see also 1.4) 6Tension Machine 6.1Fatigue Machine 6.2Loading Fixtures 6.3Displacement Gage, Measurement 6.4Specimen Size, Configurations, and Preparation (seealso 1.5)7Specimen Size Estimates 7.1Standard and Alternative Specime
9、n Configurations 7.2Fatigue Crack Starter Notches 7.3.1Fatigue Precracking (see also 1.6) 7.3.2Crack Extension Beyond Starter Notch 7.3.2.2General Procedure 8Specimen MeasurementsThickness 8.2.1Width 8.2.2Crack Size 8.2.3Crack Plane Angle 8.2.4Specimen TestingLoading Rate 8.3Test Record 8.4Calculati
10、on and Interpretation of Results 9Test Record Analysis 9.1Pmax/PQValidity Requirement 9.1.3Specimen Size Validity Requirements 9.1.4Reporting 10Precision and Bias 111.4 Specific requirements related to test apparatus:Double-Cantilever Displacement Gage Annex A1Testing Fixtures Annex A2Bend Specimen
11、Loading Fixture Annex A2.1Compact Specimen Loading Clevis Annex A2.21.5 Specific requirements related to individual specimenconfigurations:Bend Specimen SE(B) Annex A3Compact Specimen C(T) Annex A4Disk-Shaped Compact Specimen DC(T) Annex A5Arc-Shaped Tension Specimen A(T) Annex A6Arc-Shaped Bend Spe
12、cimen A(B) Annex A71This test method is under the jurisdiction of ASTM Committee E08 on Fatigueand Fracture and is the direct responsibility of Subcommittee E08.07 on FractureMechanics.Current edition approved Nov. 15, 2012. Published January 2013. Originallyapproved in 1970. Last previous edition a
13、pproved in 2009 as E399 092. DOI:10.1520/E0399-12E03.2For additional information relating to the fracture toughness testing of alumiinum alloys, see Practice B645.3The boldface numbers in parentheses refer to the list of references at the end ofthis standard.Copyright ASTM International, 100 Barr Ha
14、rbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States11.6 Specific requirements related to special test procedures:Fatigue Precracking KIc Specimens Annex A8Hot-Pressed Beryllium Testing Annex A9Rapid-Force Testing Annex A101.7 The values stated in SI units are to be regarded as t
15、hestandard. The values given in parentheses are for informationonly.1.8 This standard does not purport 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 a
16、pplica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:4B909 Guide for Plane Strain Fracture Toughness Testing ofNon-Stress Relieved Aluminum ProductsB645 Practice for Linear-Elastic PlaneStrain FractureToughness Testing of Aluminum AlloysE4 Practices for Forc
17、e Verification of Testing MachinesE8/E8M Test Methods for Tension Testing of Metallic Ma-terialsE177 Practice for Use of the Terms Precision and Bias inASTM Test MethodsE337 Test Method for Measuring Humidity with a Psy-chrometer (the Measurement of Wet- and Dry-Bulb Tem-peratures)E456 Terminology R
18、elating to Quality and StatisticsE691 Practice for Conducting an Interlaboratory Study toDetermine the Precision of a Test MethodE1820 Test Method for Measurement of Fracture ToughnessE1823 Terminology Relating to Fatigue and Fracture TestingE1921 Test Method for Determination of ReferenceTemperatur
19、e, To, for Ferritic Steels in the TransitionRange3. Terminology3.1 Definitions:Terminology E1823 is applicable to this testmethod:3.1.1 stress-intensity factor, K, KI,KII,KIIIFL3/2magnitude of the ideal-crack-tip stress field (a stress-fieldsingularity), for a particular mode of crack displacement,
20、in ahomogeneous, linear-elastic body.3.1.1.1 K is a function of applied force and test specimensize, geometry, and crack size, and has the dimensions of forcetimes length-3/2.3.1.1.2 Values of K for modes I, II, and III are given as:KI5limr0yy2r!1/2# (1)KII5limr0xy2r!1/2# (2)KIII5limr0yz2r!1/2# (3)w
21、here r is the distance directly forward from the crack tip tothe location where the significant stress is calculated.3.1.2 plane-strain fracture toughness, KIcFL-3/2thecrack-extension resistance under conditions of crack-tip planestrain in Mode I for slow rates of loading under predominantlylinear-e
22、lastic conditions and negligible plastic-zone adjust-ment. The stress intensity factor, KIc, is measured using theoperational procedure (and satisfying all of the validity require-ments) specified in Test Method E399, that provides for themeasurement of crack-extension resistance at the onset (2% or
23、less) of crack extension and provides operational definitions ofcrack-tip sharpness, onset of crack extension, and crack-tipplane strain.3.1.2.1 See also definitions of crack-extension resistance,crack-tip plane strain, and mode in Terminology E1823.3.1.3 crack mouth opening displacement (CMOD), VmL
24、crack opening displacement resulting from the total deforma-tion (elastic plus plastic), measured under force at the locationon a crack surface that has the largest displacement per unitforce.3.1.4 crack plane orientationidentification of the planeand direction of crack extension in relation to the
25、characteristicdirections of the product. A hyphenated code defined inTerminology E1823 is used wherein the letter(s) preceding thehyphen represents the direction normal to the crack plane andthe letter(s) following the hyphen represents the anticipateddirection of crack extension (see Fig. 1).3.1.4.
26、1 Wrought Productsthe fracture toughness ofwrought material depends on, among other factors, the orien-tation and propagation direction of the crack in relation to thematerials anisotropy, which depends, in turn, on the principaldirections of mechanical working and grain flow. Orientationof the crac
27、k plane shall be identified wherever possible. Inaddition, product form shall be identified (for example,straight-rolled plate, cross-rolled plate, pancake forging, and soforth) along with material condition (for example, annealed,solution treated plus aged, and so forth). The user shall bereferred
28、to product specifications for detailed processing infor-mation.3.1.4.2 For rectangular sections, the reference directions areidentified as in Fig. 1(a) and Fig. 1(b), which give examples forrolled plate. The same system is used for sheet, extrusions, andforgings with nonsymmetrical grain flow.L = di
29、rection of principal deformation (maximum grain flow)T = direction of least deformationS = third orthogonal direction3.1.4.3 Using the two-letter code, the first letter designatesthe direction normal to the crack plane, and the second letterthe expected direction of crack propagation. For example, i
30、nFig. 1(a), the T-L specimen fracture plane normal is in thewidth direction of a plate and the expected direction of crackpropagation is coincident with the direction of maximum grainflow (or longitudinal) direction of the plate.3.1.4.4 For specimens tilted in respect to two of the refer-ence axes a
31、s in Fig. 1(b), crack plane orientation is identified4For 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 website.E399 123
32、2(a) Rectangular SectionsSpecimens Aligned with Reference Directions(b) Rectangular SectionsSpecimens Not Aligned with Reference Directions(c) Cylindrical Bars and TubesL = direction of maximum grain flowR = radial directionC = circumferential or tangential directionFIG. 1 Crack Plane Identification
33、E399 1233by a three-letter code. The designation L-TS, for example,indicates the crack plane to be perpendicular to the principaldeformation (L) direction, and the expected fracture directionto be intermediate between T and S. The designation TS-Lmeans that the crack plane is perpendicular to a dire
34、ctionintermediate between T and S, and the expected fracturedirection is in the L direction.3.1.4.5 For cylindrical sections, where grain flow can be inthe longitudinal, radial or circumferential direction, specimenlocation and crack plane orientation shall reference originalcylindrical section geom
35、etry such that the L direction is alwaysthe axial direction for the L-R-C system, as indicated in Fig.1(c), regardless of the maximum grain flow. Note that this is ageometry based system. As such, the direction of maximumgrain flow shall be reported when the direction is known.NOTE 2The same system
36、is useful for extruded or forged parts havingcircular cross section. In most cases the L direction corresponds to thedirection of maximum grain flow, but some products such as pancake,disk, or ring forgings can have the R or C directions correspond to thedirection of maximum grain flow, depending on
37、 the manufacturingmethod.L = axial directionR = radial directionC = circumferential or tangential direction3.1.4.6 In the case of complex structural shapes, where thegrain flow is not uniform, specimen location and crack planeorientation shall reference host product form geometry and benoted on comp
38、onent drawings.3.1.4.7 Non-Wrought Productsfor non-wrought products,specimen location and crack plane orientation shall be definedon the part drawing.The result of a fracture toughness test froma non-wrought product shall not carry an orientation designa-tion.3.1.4.8 Discussionwhen products are to b
39、e compared onthe basis of fracture toughness, it is essential that specimenlocation and orientation with respect to product characteristicdirections be comparable and that the results not be generalizedbeyond these limits.3.2 Definitions of Terms Specific to This Standard:3.2.1 stress-intensity fact
40、or rate, K(FL-3/2t-1)change instress-intensity factor, K, per unit time.4. Summary of Test Method4.1 This test method covers the determination of the plane-strain fracture toughness (KIc) of metallic materials byincreasing-force tests of fatigue precracked specimens. Force isapplied either in tensio
41、n or three-point bending. Details of thetest specimens and experimental procedures are given in theAnnexes. Force versus crack-mouth opening displacement(CMOD) is recorded either autographically or digitally. Theforce at a 5 % secant offset from the initial slope (correspond-ing to about 2.0 % appar
42、ent crack extension) is established bya specified deviation from the linear portion of the record (1).The value of KIcis calculated from this force using equationsthat have been established by elastic stress analysis of thespecimen configurations specified in this test method. Thevalidity of the KIc
43、value determined by this test methoddepends upon the establishment of a sharp-crack condition atthe tip of the fatigue crack in a specimen having a size adequateto ensure predominantly linear-elastic, plane-strain conditions.To establish the suitable crack-tip condition, the stress-intensity factor
44、level at which specimen fatigue precracking isconducted is limited to a relatively low value.4.2 The specimen size required for test validity increases asthe square of the materials toughness-to-yield strength ratio.Therefore a range of proportional specimens is provided.5. Significance and Use5.1 T
45、he property KIcdetermined by this test method char-acterizes the resistance of a material to fracture in a neutralenvironment in the presence of a sharp crack under essentiallylinear-elastic stress and severe tensile constraint, such that (1)the state of stress near the crack front approaches triten
46、sileplane strain, and (2) the crack-tip plastic zone is smallcompared to the crack size, specimen thickness, and ligamentahead of the crack.5.1.1 Variation in the value of KIccan be expected withinthe allowable range of specimen proportions, a/W and W/B. KIcmay also be expected to rise with increasi
47、ng ligament size.Notwithstanding these variations, however, KIcis believed torepresent a lower limiting value of fracture toughness (for 2 %apparent crack extension) in the environment and at the speedand temperature of the test.5.1.2 Lower values of KIccan be obtained for materials thatfail by clea
48、vage fracture; for example, ferritic steels in theductile-to-brittle transition region or below, where the crackfront length affects the measurement in a stochastic mannerindependent of crack front constraint. The present test methoddoes not apply to such materials and the user is referred to TestMe
49、thod E1921 and E1820. Likewise this test method does notapply to high toughness or high tearing-resistance materialswhose failure is accompanied by appreciable amounts ofplasticity. Guidance on testing elastic-plastic materials is givenin Test Method E1820.5.1.3 The value of KIcobtained by this test method may beused to estimate the relation between failure stress and cracksize for a material in service wherein the conditions of highconstraint described above would be expected. Backgroundinformation concerning the basis for develo
