1、STD.AECMA PREN 2403-ENGL 3778 = LDL23LL 0035258 3b8 D AECMA Gulledelle 94 1998-1 2-31 B-1200 BRUXELLES AECMA STANDARD NORME AECMA AECMA NORM Mr Evetts prEN 2403 Edition P 1 December 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+3
2、2) 2 775 81 1 O - Fax. (+32) 2 775 81 11 ICs: Descriptors: ENGLISH VERSION Aerospace series Heat resisting alloy NI-CH2601 (NiCrl9Fel9Nb5Mo3) Vacuum melted Solution treated and precipitation treated Precision casting a or DI 50 mm Srie arospatiale Alliage rsistant chaud NI-CH2601 (NiCrl9Fel9Nb5Mo3)
3、labor sous vide Mis en solution et prcipit Pices moules de prcision aouD150mm Luft- und Raumfahrt Hochwarmfeste Legierung NI-CH2601 (NiCrlSFel9Nb5Mo3) Vakuumerschmolzen Lsungsgegliiht und ausgehrtet Feingustiicke a oder D I 50 mm This lerospace Series“ Prestandard has been drawn up under the respons
4、ibility 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 experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this Pr
5、estandard, 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 signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of
6、the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jaques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX C5 Chairman I Edition approved fo
7、r publication Comments should be sent within six months after the date of publication to aecma 1998 Page 3 prEN 2403: 1998 O In trod ucti on 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 42
8、58. This standard has been prepared in accordance with EN 4500-3. 1 Scope This standard specifies the requirements relating to: Heat resisting alloy NI-CH2601 (NiCrl 9Fel9Nb5Mo3) Vacuum melted Solution treated and precipitation treated Precision casting a or DI 50 mm for aerospace applications. 2 No
9、rmative 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 dated references, subsequent amendments to or revisions o
10、f 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 2103-3 Aerospace series - Steel, nickel base and cobalt base alloy remelting stock and castings - Te
11、chnical specification - Part 3: Pre-production and production castings EN 4258 Aerospace 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
12、material standards - Part 3: Specific rules for heat resisting alloys 1) EN 4383 Aerospace series - Heat resisting alloy NI-CH2601 (NiCrl9Fel9Nb5Mo3) - Non heat treated - Remelting stock 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank - - STDaA
13、ECMA PREN 2403-ENGL 1778 = LOL23LL UL52b0 TLb Page 4 prEN 2403: 1998 Form Method of production Material designation I Heat resisting alloy NI-CH2601 (NiCrlSFel9Nb5Mo3) Casting Cast under vacuum from remelting stock EN 4383 Chemical composition % Delivery condition Heat treatment Delivery condition c
14、ode Method of melting Homogenized and solution treated O= 1 O90 C f 10 “C I1 h s t i 2 h /AC + 940C I er 980 “CI t = 1 hl AC W I Use condition Heat treatment Solution treated and precipitation treated Delivery condition + 8= 720 “C f 10 “C It = 8 h I FC at 8= 50 “CI h to e= 620 “C I 10 C It = 8 h I
15、AC Limit dimension(s) I rnm I aorDS50 I 8.1 8.2 Technical specification EN 21 03-3 I Test sampie(s) See EN 2103-3 Test piece(s) See EN 2103-3 9 10 1 i Dimensions concerned mm a or D 5 50 Thickness of cladding on 0/6 - each face Direction of test piece - Characteristics I8 19 Shear strength R, MPa -
16、Bending k- - 18.3 1 Heat tiatment Temperature I e Time I Use condition OC 650 h tR 2 23 C Ambient stress oa MPa - Elongation a% - Proofstress e 755 Strength Rm MPa 2 860 QJ MPa Elongation A% 25 I Reductionofarea Z % 28 ruptures stress Elongation at NptUE I OR MPa 620 A% - 27 Notes (see line 98) I 20
17、 I impact strength *) I - STD-AECMA PREN 2403-ENGL 1778 1012311 00152b1 952 licrostructure :epair by welding .xternal defects iternal defects Marking inspection Dimensional inspection Notes Typical use Page 5 prEN 2403: 1998 -1 See EN 2103-3 -1 See EN 2103-3 See EN 2103-3 1 Only dye penetrant detect
18、ion is required 7 See inspection schedule - See EN 2103-3 I X ray inspection 7 Grade 6 or according to inspection schedule _ See EN 2103-3 See EN 21 03-3 *) p.pm STD-AECMA PREN 2403-ENGL 1778 M LO123LL 00152b2 A77 Page 6 prEN 2403: 1998 Product qualification Qualification programme to be agreed between manufacturer and purchaser.
