AECMA PREN 2500-3-1995 Aerospace Series Instructions for the Drafting and Use of Metallic Material Standards Part 3 Specific Requirements for Heat Resisting Alloys Edition P 2《航空航.pdf

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1、j Edition approved for publication AECMA PRENu2500-3 75 1012311 0009342 b42 C 5 Chairman Comments should be sent within SIX months after the date of publication to AECMA STANDARD NORME AECMA AECMA NORM prEN 2500 Part 3 Edition P 2 May 1995 EDIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL

2、 AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes Issue P 1 July 1992 ICs : 9 Descriptors : ENGLISH VERSION Aerospace series Instructions for the drafting and use of metallic material standards Part 3 : Specific requirements

3、 for heat resisting alloys Srie arospatiale Instructions pour la rdaction et lutilisation des normes de matriaux mtalliques Partie 3 : Exigences spcifiques aux alliages rsistant chaud Luft- und Raumfahrt Regeln fr die Erstellung und Anwendung von Normen ber metallische Werkstoffe Teil 3 : Besondere

4、Festlegungen fr hochwarmfeste Legierungen This “Aerospace Series “ Prestandard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It IS published on green paper for the needs of AECMA-Members. It has been technically approved by the e

5、xperts of the concerned Technical Committee following comment by the Member countries. 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

6、. After examination and signature of the AECMA Standard Checking Centre 1NP.S) and formal agreement of the Official Services of the Member countries it will be submitred as a draft European Standard to CEN (European Committee for Standardization) for formal vote. 1995-05-31 AECMA Technopolis - 175,

7、rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE M. Odorico I I aecrna 199 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 PR

8、EN*2500-3 95 9 LOL23LL 0009343 589 = Page 2 prEN 2500-3 : 1995 Contents list Page 1 Scope 3 2 Normative references . 3 3 Definitions 3 4 The use of metallic material EN aerospace standards 3 5 Instructions for drafting of metallic material EN aerospace standards . . . . . . . . 3 Copyright Associati

9、on Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-! Page 3 prEN 2500-3 : 1995 1 Scope This standard specifies the specific requirements for the drafting and use of heat res

10、isting alloy material standards for aerospace applications. This standard shall be used in conjunction with EN 2500-1. 2 Normative references This Standard incorporates by dated or undated reference provisions from other publications. These normative references are cited at the appropriate places in

11、 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 the latest edition of the publication referred to applies

12、. “I EN 2500-1 EN 10083-1 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 1 : General requirements 1 Quenched and tempered steels - Part 1 : Technical delivery conditions for special steels BS 5046 : 1974 Method for the estimation of equivalent diameter

13、s in the heat treatment of steel 2, 3 Definitions See EN 2500-1 for steels, the equivalent diameter De for determining the limiting dimensions is obtained as follows : - for uniform single shapes, use the information given in EN 10083-1 : 1991, or BS 5046 : 1974 - for non-uniform shapes, use the pro

14、cedure given in EN 10083-1 : 1991 or the formulae given in BS 5046 : 1974 4 See EN 2500-1. The use of metallic material EN aerospace standards 5 Note: examples given below are only intended to illustrate the rules and may not correspond to real standardized EN products. Instructions for drafting of

15、metallic material EN aerospace standards Technological development may require the use of terms additional to those listed. 5.1 See EN 2500-1 and example 1 of this standard. The following are examples of descriptions which shall be used. 5.1 .I Method of melting Complete in accordance with EN 2500-1

16、 using one or more of the following terms : Page 1: Title of the material standard - air melted, - vacuum melted, - vacuum refined, - vacuum arc remelted, - electro-slag remelted, - consumable electrode remelted, - vacuum arc melted, - inert gas atomized, - rotating electrode atomized, - rotating cr

17、ucible atomized, - water atomized. 1) Published as AECMA Prestandard at the date of publication of this standard 2) This standard is published by : British Standard Institute (B.S.I.) 389, Chiswick High Road, London W44AL, UNITED KINGDOM Copyright Association Europeene des Constructeurs de Materiel

18、Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN*2500-3 95 m L0123Ll 0009345 35L Page 4 prEN 2500-3 : 1995 5.1.2 Form entries a) sheet, strip, plate The term may be qualified with one of the following te

19、rms : - rolled, : cold rolled, -? hot rolled. bl bar The term may be qualified with one or more of the following terms : - hot rolled, - cold rolled, - drawn, - extruded. c) section The term may be qualified with one or more of the following terms : - extruded, - hot rolled. d) tube The term may be

20、qualified with one or more of the following terms : - rolled, - drawn, - extruded, - seamless, - welded. e) wire The term may be qualified with one or more of the following terms : - drawn, - hot rolled. f) forging stock gl forgings The term may be qualified with one or more of the following terms :

21、 - die, - hand. hl remelting stock i) castings The term may be qualified with one or more of the following terms : - sand; - investment, - centrifugal, - precision, - hot isostatically pressed (hipped). - chill, Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IH

22、S under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENx2500-3 95 W LO1231L O007346 278 Page 5 prEN 2500-3 : 1995 5.1.3 Form entries for powder metallurgy - powder, - compacted material, - part. (The term may be qualified with one or mo

23、re of the following terms : - hot isostatically pressed (hipped), - extruded, - forged. 5.1.4 Additional information entries - for structural applications, - for pressure applications, - for rivets, - for forged fasteners, - for forged rings, - for machined fasteners, - for welding. 5.2 Page 2 See E

24、N 2500-1. 5.3 Page 3 See EN 2500-1 and example 2 of this standard. 5.4 Page 4 5.4.1 Page 4, line 1 : Material designation See EN 2500-1 and example 3 of this standard. 5.4.2 Page 4, line 2 : Chemical composition The chemical composition shall be written in accordance with EN 2500-1 and the order of

25、presentation of elements shall conform to the following rules : - C, Si, Mn, P, S, - alloying elements in alphabetical order using their chemical symbol, - ratio and/or total of above elements, - trace elements. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IH

26、S under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 AECMA PREN*2500-3 95 LOL23LL 0009347 124 Page 6 prEN 2500-3 : 1995 5.4.3 Page 4, line 3 : Method of melting See EN 2500-1 and example 3 of this standard, using the terms listed in 5.1.1. 5.

27、4.4 Page 4, line 4 : Form, Method of production, Limit dimensions See EN 2500-1, end example 3 of this standard. Use the same terms as used in 5.1.2 and 5.1.3. 5.4.5 Page 4, line 5 - Line 5.1 : Technical specification See EN 2500-1. - Line 5.2 : Dimensional standards See EN 2500-1 5.4.6 Page 4, line

28、 6 - Line 6.1 : Delivery condition and heat treatment See EN 2500-1 and example 3 of this standard. Use one or more of the following terms : - not heat treated, - annealed, - solution treated, - precipitation treated, - tempered, - cold worked, - hot isostatically pressed (hipped), - descaled, - mac

29、hined, - ground, - as cast, - as forged. - Line 6.2 : Delivery condition code See EN 2500-1 and example 3 of this standard. 5.4.7 Page 4, line 7 : Use condition and heat treatment See EN 2500-1 and example 3 of this standard. Use the terms given in 5.4.6 or state : - Delivery condition. 5.4.8 Page 4

30、, line 8 : Sample, Test piece, Heat treatment See EN 2500-1 and example 3 of this standard. 5.4.9 Page 4, line 9 : Dimensions concerned See EN 2500-1 and example 3 of this standard. 5.4.10 Page 4, line 10 : Thickness of cladding on each face See EN 2500-1 5.4.1 1 Page 4, line 11 : Direction of test

31、piece See EN 2500-1 and example 3 of this standard. i 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 7 prEN 2500-3 : 1995 5.4.12 See EN 2500-1 an

32、d example 3 of this standard. 5.4.13 See EN 25bO-i and example 3 of this standard. 5.4.14 See EN 2500-1 and example 3 of this standard. 5.4.1 5 See EN 2500-1 and example 3 of this standard, 5.4.16 See EN 2500-1 and example 3 of this standard. 5.4.17 See EN 2500-1 and example 3 of this standard. 5.4.

33、18 See EN 2500-1 and example 3 of this standard. 5.5 Page 5 5.5.1 Page 5, line 28 See EN 2500-1. 5.5.2 See EN 2500-1 and example 4 of this standard. 5.5.3 The relevant lines shall be completed in accordance with EN 2500-1, see example 4 of this standard. 5.5.4 Page 5, line 97 : Designation See EN 25

34、00-1 and example 4 of this standard. 5.5.5 See EN 2500-1 and example 4 of this standard. 5.5.6 Page 5, line 99 : Typical use See EN 2500-1 and example 4 of this standard. 5.6 See EN 2500-1 and example 5 of this standard. Page 4, lines 12 to 16 : Tensile (TI Page 4, line 17 : Hardness Page 4, line 18

35、 : Shear strength Page 4, line 19 : Bending Page 4, line 20 : Impact strength Page 4, lines 21 to 26 : Creep (Cl Page 4, line 27 : Notes (see line 98) Page 5, line 29 : Reference heat treatment Page 5, lines 30 to 96 Page 5, line 98 : Notes Page 6, line 100 : Qualification Copyright Association Euro

36、peene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECIA PRENX2500-3 95 W 10123LL O009349 TT7 W Page 8 prEN 2500-3 : 1995 Example 1 Completion of title Aerospace series Heat resist

37、ing alloy NI-PH2601 Vacuum melted and vacuum arc remelted Solution treated and precipitation treated Forgings De I300 mm Srie arospatiale Luft und Raumfahrt Alliage rsistant chaud NI-PH2601 Elabor sous vide et refondu sous vide par arc Mis en solution et prcipit Pices forges et pices matrices De 5 3

38、00 mm Hochwarmfeste Nickellegierung NI-PH2601 Vacuumerschmolzen und vacuumlichtbogenumgeschmolzen Lsungsgeglht und ausgelagert Gesenk- und Freiformschmiedestcke De 5 300 mm Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Resal

39、eNo reproduction or networking permitted without license from IHS-,-,-Page 9 prEN 2500-3 : 1995 Example 2 Completion of page 3 O introduction For the use of this standard, see EN 2500-3 1 Scope This standard specifies the requirements relating to sheet and strip, a I3 mm, solution treated in heat re

40、sisting alloy CO-PH 1402 for aerospace applications. 2 Normative references This European Standard incorporates by dated 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

41、dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 2500-3 Aerospace series - Instructions for

42、the drafting and use of metallic material standards - Part 3 : Specific requirements for heat resisting alloys ) EN 3235-2 Aerospace series - Heat resisting alloy wrought products - Technical specification - Part 2 : Plate, sheet and strip ) 1) Published as AECMA Prestandard at the date of publicati

43、on of this standard 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 PREN*2500-3 75 W 1012311 0009351 655 = 51 5.1 Technical specification 7 1 2 3

44、 Page 10 prEN 2500-3 : 1995 Material designation Chemjcal Element composition YO rnax. Method of melting Example 3 Completion of page 4 0,050 ! Heat resisting alloy CO-PH1402 - I 0,20 - - 20,O - 0,020 20,O 13,O - 4 CI Si IMn) P I SI Cr I Fe 1 La I Ni I W 1 B 1 Co ! Form Method of production Limit di

45、mensions irnm) Use condition and heat treatment Sample Test piece Heat treatment Separately cast - See line 29 Dimensions concerned Thickness of cladding on each face mm - ob - Direction of test piece L Temperature 6 OC Ambient T Strength R, MPa 2 1275 Elongation A X 25 2 15 Reduction of 2 Oh area H

46、ardness 350 HB450 C Stress o, MPa - 300 Elongation a% - I0,2 Rupture stress OR MPa 400 - i Elongation at A % 25 - rupture Notes (see line 98) - 0.15 10.50 1 1,25 10,02010,0151 24.0 13.00 10.12 124.0 I 16.0 10,0151 1 Vacuum melted and consumable electrode remelted Sheet and strip Hot rolled 1.55a53 E

47、N 3235-2 ! 5.2 Dimensional standards EN 2366 Solution treated and precipitation treated 6.1 Delivery Condition and heat treatment 955 “C It = 2 h I AC + 720 OC It = 8 h I Cool at 50 OC per h to 620 OC I t = 8 h I AC 6.2 Delivery condition code 1 U Delivery condition - I Proof stress IRp0,21MPa 2 103

48、5 Shear strength I 7 /“ Bending - 0.75; a = 180 KU = 300 J/cm2; Direction L Impact strength I 700 700 I 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-,-,

49、- 29 Reference heat treatment Page 11 prEN 2500-3 : 1995 - Solution heat treated and precipitation treated 955OClt = 2hlAC + 72QOCIt = 8hICoolat5OoCperhto62O0CIt =8hlAC EN 2950 Annex B Microstructure references 1 Carbides, barbonitrides borides 1.1 1.2 1.3 1.4 2 Incipient melting 3 Delta phase precipitation 3.1 3.2 3.3 4 Aluminium silicate