1、AECMA PREN*335L 95 D L01231L 000963g 219 D 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 3351 Edition P 2 September 1995 ICs : PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUS
2、TRIES (AECMA Gulledelle 94 - 8-1200 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 TLP63001 Grade 2 Solution treated and aged Forgings De I 150 mm Srie arospatiale Alliage de titane TLP63001 Grad
3、e 2 Mis en solution et revenu Pices forges et pices matrices De 5 150 mm Luft- und Raumfahrt Titanlegierung TI-P6300 1 Grade 2 Lsungsgeglht und ausgelagert Schmiedestcke De I 150 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of A
4、erospace 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 Prestandard, the technical content shall not be c
5、hanged 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 INPSI and formal agreement of the Official Services of the Member countries it will be submitted as a
6、draft European Standard to CEN (European Committee for Standardization) for formal vote. 1995-09-30 AECMA Gulledelle 94 B-1200 BRUXELLES Mr Odorico I I aecma 199! Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reprod
7、uction or networking permitted without license from IHS-,-,-AECMA PREN*(335L 95 LOL23LL 0009636 091 Page 3 prEN 3351 : 1995 O Introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies the requirements relating to grade 2 solution treated and aged forgings in titanium
8、alloy TI-P63001, De 2 150 mm, for aerospace applications. 2 Normative 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 date
9、d references, subsequent amendments to or revisions of any of these 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 2003-9 Aerospace series - Test methods for titanium and
10、titanium alloys - Part 9 : Determination of surface contamination 1) EN 2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirements for titanium and titanium alloys 2, EN 2858-3 Aerospace series - Titanium and titanium alloys - Forg
11、ing stock and forgings - Technical specification - Part 3 : Pre-production and production forgings EN 3465 Aerospace series - Titanium alloy TI-P63001 - Not heat treated - Grade 2 forging stock, for solution and aged forgings - a or D I 360 mm *) 1) In preparation at the date of publication of this
12、standard 2) Published as AECMA Prestandard 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 PRENg335L
13、95 lOL23LL O009637 T28 3,O 5,O 3.0 1,s 0,3 - - - - - - - 5,O 2,5 0,7 0,25 0,03 0,0125 0,20 0,08 0,lO) 0,401) .mit dimensions (mm) 5.1 Technical specification D,5150 EN 2858-3 5.2 Dimensional standards - I 6.1 Delivery condition and Solution treated andaged 6.2 Delivery condition code U Use condition
14、 and heat treatment Delivery condition - 8 9 Sample See EN 2858-3 Test piece - Heat treatment Use condition Dimensions concerned mm D, S 100 100 D, 5 150 Direction of test piece See EN 2858-3 Temperature e oc Ambient Proof stress Rp0,2 MPa 2 920 2 870 T Strength R, MPa 1050 5 R, 5 1220 1000 5 R, S 1
15、MO Elongation A Yo 29 29 Reduction of Z % 2 20 2 20 I area 18 19 Shear strength Rc MPa - Bending k- - ,act strength Temperature e oc - - Stress Elongation Rupture stress Elongation at rupture ma MPa - mR MPa - - a Oh A % - :es (see line 98) 1) Page 4 prEN 3351 : 1995 Element Chemical AI 1 Mo 1 Sn I
16、Si 1 O2 1 NI 1 H2 1 Fe I C 1- Each Total min. composition Oh ulethod of melting I Grade 2 I I i :orm Method of production Forgings Forged from forging stock EN 3465 heat treatment 900 OC / t2 20 min I AC +50O0CIt=24hIAC 10 Thickness of cladding on each face 11 12 13 14 15 16 - - - - - 17 I Hardness
17、20 21 22 23 24 25 26 - - - - - - Time - C 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-,-,-44 51 - - - 74 - 82 See EN 2858-3 See EN 2858-3 97 98 - 1 2 9
18、9 - EN 2003-9 Pre-production part unless otherwise specified AECMA PRENs335L 95 = LOL23LL 0009638 964 3 - Page 5 prEN 3351 : 1995 See inspection schedule See EN 2858-3 External defects - - )4acrostructure ,grain flow) See the relevant drawing 1) Determination not required for routine acceptance Surface contamination 3atch uniformity lalloy verification) Designation Notes Typical use -I 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-,-,-
