1、 AECMA PREN83310 95 W 1012311 0009609 Ob3 AECMA STANDARD prEN 3310 NORME AECMA Edition P 2 AECMA NORM September 1995 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (32) 2 775 81 1 O - Fax. (32) 2 775 81 1 1 ICs : Supersedes Issue P 1 Mar
2、ch 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium alloy TLP64001 Not heat treated Grade 2 forging stock, for annealed forgings a or D I 360 mm Srie arospatiale Alliage de titane TI-P64001 Non trait Demi-produits de grade 2 destins la forge, pour pices forges ltat recuit a ou D I 360 mm
3、 Luft- und Raumfahrt Titanlegierung TLP64001 Nicht wrmebehandelt Grade 2 Schmiedevormaterial, fr geglhte Schmiedestcke a oder D I 360 mm This “Aerospace Series r Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on gre
4、en 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 Prestandard, the technical content shall not be changed to an extent that interchangeability
5、is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPSI and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Com
6、mittee for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX I Edition approved for publication Comments should be sent within six months after the date of publication to 1995-09-30 AE
7、CMA Gulledelle 94 B-1200 BRUXELLES C5 Chairman 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-,-,-AECMA PREN*33LO 95 = LOL23LL OO
8、ObLL 71% Page 3 prEN 3310 : 1995 O Introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies the requirements relating to not heat treated grade 2 forging stock, for annealed forgings, in titanium alloy TI-P64001, a or D 5 360 mm, for aerospace applications. 2 Normati
9、ve references 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
10、 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. EN 2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirem
11、ents for titanium and titanium alloys l) EN 2858-2 Aerospace series - Titanium and titanium alloys - Forging stock and forgings - Technical specification - Part 2 : Forging stock 1) Published as AECMA Prectandard at the date of publication of this standard Copyright Association Europeene des Constru
12、cteurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECflA PREN*3330 95 m 3032333 0009632 658 m 5.1 Technical specification 5.2 Dimensional standards Page 4 prEN 331 O : 1995 EN 2858-2 - 6.2 Delive
13、ry condition code Use condition and heat treatment U Delivery condition - Dimensions concerned Thickness of cladding on each face mm - OY - T Strength R, MPa 900 5 R, 5 11 60 Elongation A Yo 2 10 Reduction of 2 YO 2 25 area Hardness - Shear strength Bending Rc MPa - k- - Impact strength Temperature
14、e oc - - Time Stress IS, h - MPa - Meterial designation Titanium alloy TI-P64001 I I Chemical Others Base 02+2N2 I N2 Element max. composition % I Method of melting Grade 2 Form Method of production Limit dimensions (mm) Forging stock a or D 360 I 6.1 Delivery condition end heat treatment Not heat t
15、reated - Characteristics Sample Test piece Heat treatment See EN 2858-2 Heat treated before machining See line 29 Direction of test piece I See EN 2858-2 I Temperature I 0 I OC I Ambient Proof stress I Rp, I MPe I 2 830 I Eloneation I a I % I Rupture stress Elongation at rupture Notes (see line 98)
16、I *I 1) 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*3310 95 H LOL23LL 0009633 594 - - - 7 - - 3eference heat :reatment External defects
17、Vlacrostructure Annealed 690 OC 5 O 840 “C It 2 30 min / AC or cool in inert atmosphere See EN 2858-2 See EN 2858-2 Diameter Maximum acceptable Not acceptable To be submitted for approval mm macrostructure macrostructure 5 50 2 MA 2 2 MA 80 to 2 MA 40 to - 50 05150 2 MA 3 2 MA 84 2 MA 42 and 150 D 5
18、 250 2 MA 5 and 2 MA 60 to 250 D 5 360 2 MA 6 2 MA 100 2 MA 62 See EN 2858-2 See EN 2858-2 nternal defects 3atch uniformity ,Allov verification) - - - Designation *I p.p.m. 1) Determination not required for routine acceptance - Notes Typical use 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-,-,-
