1、AECMA PRENx2002 PARTx5 95 = 1012311 0009769 419 Edition approved for publication AECMA STANDARD prEN 2002 NORME AECMA Part 5 Edition P 2 October 1995 AECMA NORM PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32)
2、2 775 81 11 C5 Chairman Comments should be sent within six months after the date of publication to ICs : Supersedes Issue P 1 December 1993 Descriptors : ENGLISH VERSION Aerospace series Test methods for metallic materials Part 5 : Uninterrupted creep and stress-rupture testing b Srie arospatiale Mt
3、hodes dessais applicables aux matriaux mtalliques Partie 5 : Essai non interrompu de fluage et essai de rupture par fluage Luft- und Raumfahrt Prfverfahren fr metallische Werkstoffe Teil 5 : Kriech- und Zeitstandversuch unter konstanter Zugbeanspruchung This “Aerospace Series“ Prestandard has been d
4、rawn up under the responsibility of AECMA (Th European Association of Aerospace Industries). It is published on green paper for the needs o AECMA-Members. It has been technically approved by the experts of the concerned Technica Committee following comment by the Member countries. an extent that int
5、erchangeability is affected, physically or functionally, without re-identifica tio of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and forma agreement of the Official Services of the Member countries it will be submitted as a draf European Standard to CEN
6、 (European Committee for Standardization) for formal vote. Subsequent to the publication of this Prestandard, the technical content shall not be changed t J 1995-10-31 AECMA Gulledelle 94 8-1 200 BRUXELLES M. Odorico I I aecma 199E Copyright Association Europeene des Constructeurs de Materiel Aerosp
7、atial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN*ZOOZ PART*5 95 I 1012311 O009770 130 Page 2 prEN 2002-5 : 1995 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Contents list Scope References Principle Symbols Def
8、initions Specification of test requirements Testing equipment Proportional test pieces Non-proportional test pieces Preparation of test piece from sample Measurement of cross-sectional area Marking the original gauge length Heating of test piece Temperature control and observations Loading of the te
9、st piece Stress rupture test Creep strain test Test report Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I 1 i ! AECMA PREN*2002 PARTr5 95 H 10123Ll
10、0009771 077 Page 3 prEN 2002-5 : 1995 I Scope This standard applies to uninterrupted constant-load tensile creep strain and stress-rupture testing of metallic materials governed by aerospace standards. It defines the properties that may need to be determined and the terms used in describing tests an
11、d test pieces. It specifies the dimensions of test pieces and the method of testing. The duration of the creep strain and stress-rupture tests complying with this standard shall be less than 1 O O00 h and at temperatures not exceeding 1 1 OOOC. This standard may also apply to metallic materials for
12、test durations exceeding 10 O00 h and/or for test temperatures exceeding 1 1 OOOC providing that previous agreement has been reached between the manufacturer and the purchaser. 2 Normative references This Standard incorporates by dated or undated reference provisions from other publications. These n
13、ormative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this Standard only when incorporated in it by amendment or revision. For undated references
14、 the latest edition of the publication referred to applies. EN 10002-2 Metallic materials - Tensile testing - Part 2 : Verification of the force measuring system of the tensile testing machines EN 10002-4 Metallic materials - Tensile test - Part 4 : Verification of extensometers used in uniaxial tes
15、ting ASTM E 1 O1 2 Verification of specimen alignment under tensile loading ) 1 ) Published by American Society for Testing and Materials (ASTM), 191 6 Race Street, Philadelphia, PA 19103. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AE
16、CMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENm2002 PART*5 95 LOL231L 0009772 TO3 W Thickness of test section of test piece of rectangular cross-section Percentage elongation after rupture Percentage strain during testing Percentage total plastic str
17、ain Notch angle Width of test section of test piece of rectangular cross-section Diameter of test section of test piece of circular cross-section Diameter of test piece at root of notch Diameter of the parallel portion of a notched test piece of circular cross- section Theoretical stress concentrati
18、on factor of a notched test piece Parallel length Extensometer gauge length (Leo = initial ; Leu = final) Basis gauge length for elongation calculations Extension of extensometer gauge length Measurement gauge length Parallel length of the test piece containing the notch Shoulder gauge length for te
19、st without extensometer on the parallel length (Lso = initial ; Lsu = final) Total length of the test piece Final measurement length after rupture Transition radius Notch root radius Stress, based on room temperature cross-sectional area Original room temperature cross-sectional area of test section
20、 Minimum cross-sectional area of test section after rupture Time of the test under specified conditions for temperature and stress Continued Page 4 DrEN 2002-5 : 1995 3 Principle The test consists in maintaining a test piece at a uniform temperature and subjecting it to a constant tensile force at t
21、hat temperature in order to determine specified properties. 4 Symbols See table 1 and figures 1 to 5. Table 1 Symbol a A A f AP a. b d dn Dn rn 6 SO SU Unit I Designation mm % % % O mm mm mm mm mm mm mm mm mm mm mm mm mm mm mm M Pa mm2 mm2 h Copyright Association Europeene des Constructeurs de Mater
22、iel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENU2002 PARTUS 95 LOI12311 0009773 94T H Symbol tP tr QT Z Unit h h OC 96 5 Definitions 5.1 Test piece Page 5 prEN 2002-5 : 1995 3 Table 1 (concluded) De
23、signation Time to specified total plastic strain Time to rupture Test temperature Percentage reduction of area after rupture Portion of the test sample on which the creep strain or stress-rupture test is carried out (see figures 1 to 5). 5.2 Proportional test piece A test piece having an original ba
24、sis gauge length (Lo = Leos or L,.) which bears a specified relationship to the cross-sectional area. This ensures that comparable values for percentage elongation after rupture (A) are obtained from test pieces of different size but having the same relationship. The relationship Lo = 5,65 6o which
25、for test pieces of circular cross section gives a value of Lo = 5 do has been accepted by international agreement and is preferred in the use of this standard. The relationship is indicated in the symbol for percentage elongation after rupture (A) as a subscript, e.g. A, representing the ratio Lo/d.
26、 5.3 Non-proportional test piece In cases where the original basis gauge length has not the defined relationship to the cross-sectional area, a subscript shall be used with the symbol for elongation A to indicate the gauge length, .e. A40mm. 5.4 Gauge length A length of the test piece on which elong
27、ation is measured at any moment during the test. 5.4.1 Measurement gauge length (L,) e The measurement gauge length shall be defined as either the extensometer gauge length Leo for test pieces measured with extensometers gripping the parallel portion of the specimen or small annular ridges, when the
28、se are used, or the shoulder gauge length Ls for test pieces where extension is measured between points including the transition radii and/or gripping portions of the test piece. The measurement gauge length (Lm) is to be used only for the numerator in elongation calculations; that is, the change in
29、 length of that part of the test piece defined as Lm, whereas the basis gauge length, .e. Leo# or L,., is to be used for the denominator. 5.4.2 Extensometer gauge length (Leo) Where an extensometer is attached directly to the parallel portion of the unloaded test piece, the extensometer gauge length
30、 Leo is equal to the distance between the points of contact of the extensometer measured at room temperature, and shall also be used as the corresponding basis gauge length. Alternatively, the extensometer may be attached to annular ridges on the parallel portion. In these cases, the basis gauge len
31、gth to be used as the denominator in the elongation calculations shall be the equivalent gauge length, calculated as shown (see 5.4.3). Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permit
32、ted without license from IHS-,-,- AECMA PREN*Z002 PART*S 95 LOL23LL 0009774 BBb = Page 6 prEN 2002-5 : 1995 5.4.3 Basis gauge length for elongation calculations (Leo.or Ls a) The equivalent gauge length, .e. the parallel length which would give the same extension, including all loaded portions of th
33、e test piece between the measuring points, except the gripped ends. It shall be used as the denominator in all elongation calculations. For stress-rupture test pieces it is recommended that Leo -, or Ls be calculated from the following equation: Leo-or Ls- = Lc + 2 (do/di)2n x Li = 5,65 6o i= 1 Wher
34、e : Lc is the parallel length between the annular ridges or test piece ends, with a diameter do, k is the number of sections of length Li with increasing diameter of di at the two transition radii. The correct Lc shall be selected, so that the effective gauge length equals 5,65 .JS0. It is recommend
35、ed to use n = 6 as a basis for comparison, although the actual n for many aerospace materials is 6. This is based on the “power law“ creep relationship : 5.4.4 Shoulder gauge length Ls) Where the extension is measured at the test piece ends, or between reference marks on the enlarged ends of the tes
36、t piece, the shoulder gauge length (L,) shall be denoted. The basis gauge length shall be calculated as in 5.4.3 and based on room temperature measurements, including all loaded portions of the test piece between the measuring points, except the gripped ends. 5.5 Parallel length (L,) The length of t
37、he parallel portion of the test piece. For some test pieces, Lc will be less than Lm, the applicable original gauge length. 5.6 Extension (ALe) The increase of the extensometer gauge length from the initial length, Leo or Leo#, indicated at the test temperature before loading, to a value Le at a giv
38、en moment during the test. 5.7 Final measurement length after rupture (Lu) The measure of the applicable gauge length (Leu or Lsu) after the test piece has ruptured, measured at room temperature. This may include the unstressed test piece ends, if the total length is used as the gauge length. 5.8 Pe
39、rcentage elongation after rupture (A) The permanent increase in length (Lu - Lm) of the applicable measurement gauge length, expressed as a percentage of the original applicable basis gauge length (Leo or Ls e), for example: A= Lu-Leo x 100, all measurements being made at room temperature. Leo 5.9 P
40、ercentage extension during testing (Af) The increase of the applicable gauge length, at a given time under full load, expressed as a percentage of the original applicable gauge length. The initial plastic strain during loading shall not be included in Af, just the elongation after attainment of full
41、 load (see figure 61. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PRENx2002 PARTxS 95 10123LL 0009775 i12 I 1 Page 7 prEN 2002-5 : 1995 5.1
42、O The total plastic extension of the original applicable measurement gauge length (Leo or Ls) inclusive of any plastic extensions during loading (.e. the total extension excluding elastic extensions, expressed as a percentage of the original applicable basis gauge length (see figures 6 and 7). Perce
43、ntage total plastic strain (Ap) 5.1 l Original section (So) The cross-sectional area of the gauge length of the test piece, determined before testing. 5.12 Final section (Su) The minimum cross-sectional area of the test piece, after rupture. 5.13 Percentage reduction of area after rupture (2) The ma
44、ximum decrease of the cross-sectional area (So - Su) expressed as a percentage of the original cross-sectional area (So), .e. Z = so - su x 100 SO 5.14 Stress (a) The force on the test piece divided by the original cross-sectional area of the parallel portion. It should be noted that the thermal exp
45、ansion of the test piece during heating increases the effective cross- sectional area. The effective stress is therefore slightly less than 0, which is based on room temperature. 5.15 Rupture Complete fracture of the test piece within the original gauge length under constant force and at constant te
46、mperature. 5.16 Time to rupture (t,) The total time, at the test temperature and the test force, to the rupture of the test piece (see figure 7) 5.17 Time to specified total plastic strain (t,) The total time, at the test temperature and including the portion of the loading time after the loading cu
47、rve deviates from an extension of the linear-elastic modulus line, until the specified total plastic strain (Ap) is reached (see figure 6). 5.1 8 Theoretical stress concentration factor (KJ The ratio of the greatest stress in the region of a notch as determined by the theory of elasticity to the cor
48、responding nominal stress. In formula : Kt=- Opeak Onom. Where : Kt speak is the peak stress by notch Onom. is the nominal stress is the theoretical stress concentration factor Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for R
49、esaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN*2002 PART*5 75 LOL231L 0007776 659 Page 8 prEN 2002-5 : 1995 6 Specification of test requirements The material standard shall state the following : - type of test piece see 8 and 9) ; - specified test temperature (0,) ; - specified test stress (o) ; - time the test piece shall be simultaneously under the specified conditions of temperature and st
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