AECMA PREN 2002-2-2003 Aerospace Series Metallic Materials Test Methods Part 2 Tensile Testing at Elevated Temperature Edition P 3《航空航天系列.金属材料测试方法.第1部分 环高温拉伸试验P3版》.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 15 November 2003 prEN 2002-2 Edition P 3 November 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Aerospace series Metallic materials Test methods Part

2、2: Tensile testing at elevated temperature Supersedes edition P 2 March 1996 Srie arospatiale Luft- und Raumfahrt Matriaux mtalliques Metallische Werkstoffe Mthodes dessais applicables Prfverfahren Partie 2: Essais de traction temperature leve Teil 2: Zugversuch bei Hochtemperatur This “Aerospace Se

3、ries“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is published for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member

4、comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of AECMA-STAN it

5、 will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by withdr

6、awing any national standards conflicting with the EN. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license fr

7、om IHS-,-,-Page 2 prEN 2002-2: 2003 Foreword This standard was reviewed by the Domain Technical Coordinator of AECMA-STANS Metallic Material Domain. After inquiries and votes carried out in accordance with the rules of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has rece

8、ived approval for Publication. Contents Page O In trod uction . 3 1 Scope 3 2 Normative references . 3 3 Definitions . 3 4 Health and safety 6 5 Principle 6 6 Testing requirements . 6 7 Test report 12 AnnexA(normative) Types of test piece to be used for sheet and strip with thickness less than 8 mm

9、14 Annex B (normative) Types of non-machined test piece to be used in the case of bar, section and wire with a diameter or thickness less than or equal to 8 mm Annex C (normative) Types of machined test piece to be used in the case of bar, section, plate and wire with diameter or thickness greater t

10、han 8 mm and for forgings and castings . Annex D (normative) Types of test piece to be used in the case of tubes 16 17 20 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without li

11、cense from IHS-,-,-Page 3 prEN 2002-2: 2003 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is described in EN 4258. 1 Scope This standard specifies the requirements for the tensile testing of me

12、tallic materials at elevated temperature for aerospace applications. It shall be applied when referred to in the EN technical specification or material standard unless otherwise specified on the drawing, order or inspection schedule. 2 Normative references This European Standard incorporates by date

13、d or undated reference provisions from other publications. These normative 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 the publications apply to this European Standard only

14、 when incorporated in it by amendments or revision. For undated references the latest edition of the publications referred to apply. EN IS0 7500-1 EN IS0 9513 EN 4258 EN 4259 EN 10002-4 EN 60584-2 ASTM E-I012 Metallic materials - Verification of static uniaxial testing machines - Part I: Tension/ co

15、mpression testing machines - Verification and calibration of the force measuring system Metallic materials - Calibration of extensometers used in uniaxial testing Aerospace series - Metallic materials - General organization of standardization - Links between fypes of EN standards and their use Aeros

16、pace series - Metallic materials - Definitions of general terms 1 ) Metallic materials - Tensile test - Part 4: Verification of extensometers used in uniaxial testing Thermocouples - Part 2: Tolerances Standard practice for verification of specimen alignment under tensile loading 2) 3 Defini ti ons

17、For the purposes of this standard, the following definitions apply: 3.1 General terms See EN 4259. 1) Published as AECMA Prestandard at the date of publication of this standard 2) Published by: American Society for Testing and Materials (ASTM), 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959

18、, USA 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-,-,-Page 4 prEN 2002-2: 2003 3.2 Other terms Other terms are given in Table 1 Table 1 - Definitions -

19、 Other terms Symbol Unit Term Definition Test piece The portion of the test sample on which the tensile test is carried out. Proportional test pieces A test piece with an original gauge length (Lo) having a specified relationship to the square root of the cross- sectional area (.So). The proportiona

20、lity coefficient, K, has the internationally recognised value of 5,65 for test pieces of circular cross-section. The gauge length of a proportional test piece is therefore equal to 5,65 - Lengths at least equal to that of the grips and may project beyond the grips for a maximum length equal to the e

21、xternal diameter of the tube; - A shape that shall have no effect on the deformation of the gauge length. 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-,

22、-,-Page 7 prEN 2002-2: 2003 e I o00 OC 6.1.1.4 Heating device The heating device for the test piece: - shall be such that the test piece can be heated to the specified temperature (O); - shall be able to maintain an indicated test temperature (Oi), which at any time throughout the duration of the te

23、st and at any point within the gauge length, shall not deviate from the specified temperature (O) by more than the values shown in Table 2; +3“C +4“C +5“C +I% Table 2 - Tolerances on test temperature Test temperature I Tolerance The permitted deviation in temperature along the original gauge length

24、(io) shall comply with the above at least until the point corresponding to the proof stress of non-proportional elongation is reached. The heating characteristics of the furnace and temperature control system shall prevent the limits specified above being exceeded during the heating of the test piec

25、e. 6.1 .I .5 Temperature measurements Platinum/platinum-rhodium thermocouples of type R or type S to Class 1 according to EN 60584-2 shall be used. They shall be verified over the working temperature range by a method traceable to the international unit (SI) of temperature, at intervals not exceedin

26、g one year. 6.1.1.6 Recording A recordeddata logger, accurate to + 1 ,O “C and with a resolution of 0,5 OC, shall be verified at intervals not exceeding 12 months. Verification shall be performed using a thermocouple measuring/simulating instrument, accurate to + 0,5 “C and with a resolution of 0,2

27、OC, it self verified at intervals not exceeding 12 months. Verification errors shall be recorded in a report. 6.1.2 MateriaWeagents Materialdreagents may include suitable: - degreasing fluids; - recording paper; - means of electronic recording, if appropriate; - marking inks. - refractory materials

28、6.1.3 Qualification of personnel Testing to the requirements of this test method shall only be undertaken and/or supervised by personnel who have demonstrated their competence by a suitable education or appropriate training and experience. Such competence shall be documented in an appropriate form.

29、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-,-,-Page 8 prEN 2002-2: 2003 Sheet and strip 8 mm and for forgings and castings Tu be Type of product I Cor

30、responding annex C D 6.2.3 Preparation of test pieces Machining, if required, shall be carried out at ambient temperature in accordance with a machining procedure. Precautions shall be taken to minimize superficial cold working, appreciable heating of the part or surface irregularities that could af

31、fect the results of the test. The surface finish of the parallel length shall have a Ra value not exceeding 0,8 pm. The parallel length shall be free of any visible scratches, especially circumferential marks. In the case of material with an elongation specified in the material standard to be less t

32、han 10 %, tensile test pieces of other than circular cross-section shall have the edges along the parallel length and the transition radii slightly rounded and lengthwise polished. The reduction of the cross-sectional area by this treatment shall be negligible. The test piece shall be protected from

33、 damage or contamination until the start of the test. 6.3 Testing procedu re 6.3.1 6.3.1 .I The original cross-sectional area shall be calculated from measurement of the appropriate dimensions, with an accuracy of 0,2 % or 0,005 mm, whichever the greater value, for each dimension. In the case of a l

34、ength of tube, the original cross-sectional area (So) shall be calculated as follows: Determination of the cross-sectional area. Determination of the original cross-sectional area (So) So = na (D -a) Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under lice

35、nse with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 9 prEN 2002-2: 2003 When using test piece consisting of a longitudinal strip cut from a tube, the original cross-sectional area shall be calculated according to one of the following equations: 6 D (

36、D -2 a) b 0,17 d r rl 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-,-,-Page 20 prEN 2002-2: 2003 Annex D (norm a tive) Types of test piece to be used in

37、 the case of tubes D.l Shape of the test piece The test piece consists either of a length of tube or a longitudinal strip cut from the tube and having the full thickness of the wall of the tube, or of a test piece of circular-cross-section machined from the wall of the tube. (See Figures D.l and D.2

38、) D.2 Dimensions and tolerances of the test piece Machined longitudinal test pieces are described in: a) Annex A for tube of wall thickness less than or equal to 8 mm; b) Annex C for tube of wall thickness greater than 8 mm. A test piece consisting of a length of tube shall conform to annex B. Where

39、 a tube is fitted with plugs to assist gripping, the free length between a plug and the closest gauge mark shall be greater than D/4. Figure D.l -Test pieces comprising a length of tube before and after fracture Figure D.2 - Example for test piece cut from a tube before and after fracture 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-,-,-