1、 AECMA PREN*33L2 95 m 1012311 00096LY Y20 m Edition approved for publication AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman Comments should be sent within six months after the date of publication to prEN 3312 Edition P 2 September 1995 ICs : PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDU
2、STRIES (AECMA) Gulledelle 94 - B-I200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 11 Supersedes Issue P 1 March 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium alloy TLP64001 Grade 2 Annealed Forgings De 150 mm Srie arospatiale Alliage de titane TLP64001 Grade 2 Recuit Pices
3、forges et pices matrices De I 150 mm Luft- und Raumfahrt Titanlegierung TLP64001 Grade 2 Geglht Schmiedestcke De I 150 mm This “Aerospace Series Ir Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for t
4、he 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 Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, p
5、hysically 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 the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Sta
6、ndardira tion) for formal vote. 1995-09-30 AECMA Gulledelle 94 B-I 200 BRUXELLES Mr Odorico I I aecma 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-
7、,-,- AECMA PREN*3312 95 = 10123LL 0009636 2T3 Page 3 prEN 3312 : 1995 O Introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies the requirements relating to grade 2 annealed forgings in titanium alloy TI-P64001, O, I 150 mm, for aerospace applications. 2 Normative r
8、eferences This 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 of any of these pub
9、lications 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. EN 2003-9 Aerospace series - Test methods for titanium and titanium alloys - Part 9 : Determination of surface contamination 1 EN
10、2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirements for titanium and titanium alloys EN 2858-3 Aerospace series - Titanium and titanium alloys - Forging stock and forgings - Technical specification - Part 3 : Pre-production
11、and production forgings EN 3310 Aerospace series - Titanium alloy TLP64001 - Grade 2 forging stock, for annealed forgings - a or D S 360 mm 2, 1) In preparation at the date of publication of this standard 2) Published as AECMA Prestandard at the date of publication of this standard Copyright Associa
12、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 PREN83312 95 = LOL23LL 0009637 L3T composition % min. max. - - - - - - - Base 5,5 3,5 6.75 4.5 0,25 0.03 0,0125 0,
13、30 0,08 0,lO 0,4 1 Method of melting Form Method of production Limit dimensions (mm) 5.1 Technical specification Grade 2 Forgings Forged from forging stock EN 331 O De 150 EN 2858-3 5.2 Dimensional standards - heat treatment 6.2 Delivery condition code Use condition and 690 OC S 05 840 OC It 2 30 mi
14、n I AC or cool in inert atmosphere U Delivery condition 8 Sample See EN 2858-3 Heat treatment Dimensions concerned mm Thickness of cladding on % each face Use condition 0, I75 75 0,s 1 50 - Temperature Proof stress e oc Ambient Rp0,2 MPa 2 830 2 830 Strength Elongation Reduction of area R, MPa 900 C
15、 R, S 1160 900 R, 5 1 I 60 A Oh 2 10 28 2 % 2 25 2 20 19 20 Bending k- - Impact strength - Elongation Rupture stress a % - aR MPa - 27 Notes (see line 98) 1) Page 4 prEN 331 2 : 1995 Material designation I Titanium alloy TI-P64001 Chemical 1 Element 1 Al 1 V 1 02+2N2 1 N2 I H2 I Fe I C Ti 6 I 6.1 De
16、livery condition Annealed - 7 heat treatment Test piece - 9 10 - 11 I Direction of test piece I See EN 2858-3 12 13 14 15 16 - - - - - T L 17 I Hardness 18 I Shear strength I R,. I MPa I - 21 22 23 24 25 26 - - - - - Time C IAI“I Elongation at ruature Copyright Association Europeene des Constructeur
17、s de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN*3332 95 3032333 0009638 076 - - 1 Page 5 prEN 331 2 : 1995 See EN 2858-3 See EN 2858-3 EN 2003-9 External defects 2 3 Lilacrostructure (gra
18、in flow) Pre-production part unless otherwise specified See inspection schedule Surface contamination 3atch uniformity alloy verification) Designation Notes Typical use -I See EN 2858-3 See the relevant drawing -I - I 1 ) Determination not required for routine acceptance 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-,-,-
