1、AECMA PRENu2752 95 m LOL2331 0007822 369 m AECMA STANDARD prEN 2952 NORME AECMA Edition P 3 AECMA NORM October 1995 Edition approved for publication ICs : C5 Chairman Comments should be sent within six months after the date of publication to PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTR
2、IES (AECMA) Gulledelle 94 - 6-1 200 BRUXELLES - Tel. (32) 2 775 81 I O - Fax. (32) 2 775 81 11 Supersedes Issue P2 March 1994 Descriptors : ENGLISH VERSION Aerospace series Heat resisting alloy NI-PH2601 Solution treated and cold worked Bar for forged fasteners DI50mm 1270 MPa 5 Rm I i 550 MPa Srie
3、arospatiale Alliage rsistant chaud NI-PH2601 Mis en solution et croui Barres pour lments de fixations forgs DI50mm 1270 MPa I R, 5 1550 MPa Luft- und Raumfahrt Hochwarmfeste Legierung NI-PH260 1 Lsungsgeglht und kaltverfestigt Stangen zum Stauchen fr Verbindungselemente DI50mm 1270 MPa I R, I 1550 M
4、Pa 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 experts of the concerned Technical Committee following
5、 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. After examination and signature of the AECMA Standa
6、rd 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. 1995-10-31 AECMA Gulledelle 94 6-1 200 BRUXELLES M. Odorico I aecma 199! Copyright Associa
7、tion Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENx2952 95 I LOL23LL 0009824 131 Page 3 prEN 2952 : 1995 O Introduction For the use of this standard, see EN 250
8、0-3. 1 Scope This standard specifies the requirements relating to bar for forged fasteners, D 5 50 mm, solution treated and cold worked, in heat resisting alloy NI-PH2601, 1270 MPa s Rm a 1550 MPa, for aerospace applications. 2 Normative references This European Standard incorporates by dated or und
9、ated 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 these publications apply to this European Standard only when
10、incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 2002-16 Aerospace series - Test methods for metallic materials - Pari 16 : Penetrant inspection 1) EN 2500-3 Aerospace series - Instructions for the drafting and use of m
11、etallic material standards - Part 3 : Specific requirements for heat resisting alloys 2) EN3235-3 Aerospace series - Heat resisting alloys - Wrought products - Technical specification - Pari 3 : Bar and section 2) 1) In preparation at the date of publication of this standard 2) Published as AECMA Pr
12、estandard at the date of publication 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 PRENx2952 95 I LOLZ3LL 0007825 078 5 Page 4
13、 prEN 2952 : 1995 5.1 Technical specification EN 3235-3 Heat resisting alloy NI-PH2601 5.2 Dimensional standards I I Limit dimensions (mm) Vacuum induction melted and consumable elecrode remelted (vacuum or slag) and heat treatment Bar for forged fasteners Cold worked, straightened and ground O150 -
14、 8 II I Sample Test piece Heat treatment I 6.1 Delivery condition and heat treatment Solution treated and cold worked 930C I 8s 1010C It = 1hlAC or faster + 15 % 5 cold worked I30 96 at I 650 “C Cut from bar Delivery condition - Cut from bar Reference heat treatment : see line 29 - I impact strength
15、 - - Temperature I 0 “C - 650 TillM h - tR 2 23 - - Stress a, MPa C Elongation a% - - Ebngaonat A % - 25 Rupturestress MPa - 690 2) 3) rupture Notes (seeline 98) *I 1) 2) 3) Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Resa
16、leNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN*2952 95 I LOL231L 0009826 TO4 R Page 5 prEN 2952 : 1995 Reference heat treatment Grain size Macmsructure Internaldefects Designation NObS Typical use Solution treated and precipitation treated Delivery condition + O=
17、955 C It = 1 h I AC or faster + O= 720 “C It = 8 h I FC at O= 50 C per h to 6= 6MC It = 8 h /AC L and LT 4 or finer - Isoiated grains up to 2 - No duplex structure See EN 32353 EN 2oM-16 See EN 3235-3 OWperbatdi See EN 3235-3 class5 *) p.p.m. 1) The product cannot be rejected on the sole basis of th
18、e hardness meawrements if the measured tensile characteristics are in conformity with the requirements in line 14. 2) Proportional round test piece. 3) Stress may be increased after 48 h to promote the rupture. 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-,-,-
