1、 AECMA STANDARD prEN 4317 NORME AECMA Edition P 1 AECMA NORM February 2000 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 1 I ICs: Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 -
2、 199, rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX Comments should be sent within six months after the date of publication to 2000-02-29 AECMA Mr Evetts Gulledelle 94 Edition approved for publication C5 Chairman 6-1 200 BRUXELLES aecma20C - - Descriptors: ENGLISH VERSION Aerospace ser
3、ies Heat resisting alloy FE-PA2601 (XGNiCrTiMoV26-I 5) Non heat treated Forging stock a or Dr 200 mm Srie arospatiale Alliage rsistant chaud FE-PA2601 (XGNiCrTiMoV26-I 5) Non trait Produits destins la forge a ou D 5 200 mm Luft- und Raumfahrt Hochwarmfeste Legierung FE-PA2601 (XGNiCrTiMoV26-I 5) Sch
4、miedezustand Schmiedevormaterial a oder D I 200 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AECMA- Members. It has been technically approved by the exper
5、ts 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 stan dard. A
6、fter examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. prEN 4317: 2000 O Introduction This stan
7、dard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is described in EN 4258. This standard has been prepared in accordance with EN 4500-3. I Scope This standard specifies the requirements relating to: Heat resisting alloy F
8、E-PA2601 (XGNiCrTiMoV26-15) Non heat treated Forging stock a or D s 200 mm 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 te
9、xt and the publications are listed hereafter. For 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 appli
10、es. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excluding forgings and castings) 1) EN 2860-2 Aerospace series - Heat resisting alloys - Forging stock and forgings - Technical specification - Part 2: Forging stock 1) EN 4258 Aerospace
11、 series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4500-3 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 3: Specific rules for heat resisting alloys 1) I) Published as
12、 AECMA Prestandard at the date of publication of this standard STD-AECMA PREN 4317-ENGL. 2000 = LOL23LL 003787Li 880 m Page 4 prEN 431 7: 2000 2 Chemical Element C Si Mn P S AI B Cr Mo Ni Ti V I 1 I Material designation I Heat resisting alloy FE-PA2601 (XGNiCrTiMoV26-I 5) I Pb Fe 3 4.1 I composition
13、 min. - - - - - - 30) 13,5 1,OO 24,O 1,90 0,lO - Base % max. 0,080 1,OO 2,OO 0,020 0,015 0,35 loo*) 16,O 1,50 27,O 2,30 0,50 20) Method of melting Form Forging stock Consumable electrode remelted I - 14.2 I Method of production I 6.2 7 14.3 I Limit dimension(s) I mm I a or DI 200 l Delivery conditio
14、n code U Use condition Delivery condition I 5 I Technical specification I EN 2860-2 I 8.2 8.3 16. I 1 Delivery condition Test piece) See EN 2860-2 Heat treatment See line 29 Non heat treated 10 Il I Thickness of cladding % - - on each face - I I Heat treatment I I Temperature Proof stress Elongation
15、 Reductionofarea e “C Ambient Rpo,z MPa ;r 655 R, MPa z 960 A% 2 10 Z % 2 15 Il I I 19 20 21 -, 22 I I I Heat treatment Bending k- - Impact strength - Temperature e “C 650 Time h tR 2 23 Characteristics 18.1 Test sample(s) See EN 2860-2 I 9 I Kensians concerned -7mm 1 De I 75 75 De 100 I 1 1 I I Dir
16、ection of test piece 1 L I T I 17 I Hardness I 277 HB - 363 I 18 I Shear strength 1 R, (MPa I I23 I I Stress l I I 1241 I Elongation Ia % I I J I 27 I Notes (see line 98) I I STD-AECMA PREN 13L7-ENGL 2000 E 1OL23LL 0017875 717 M eference heat treatment xternai defects lacrostructure iternal defects
17、Marking inspection Dimensional inspection Notes Typical use I Page 5 prEN 4317: 2000 Solution and precipitation treated =980C I10 “CI t 2 1 h OQ or WQ + O= 720 “CI 10C (Heating from O= 550 “C to O= 710 “C in t 2 1 h) It = 16 h /AC -I -I See EN 2860-2 To be defined on the order See EN 2860-2 Class 2 See EN 2860-2 See EN 2860-2 -I - I *) p.p.m. STD-AECMA PREN 4317-ENGL 2000 = lifl12311 001787b b53 Page 6 prEN 431 7: 2000 Product qualification See EN 2043 Qualification programme to be agreed between manufacturer and purchaser.
