1、CEN PRENt345b 93 m 3404587 0044bb2 073 W Edition approved for publication 1993-04-26 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months after the date of publication to AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE C5 Chairm
2、an M. ODORICO prEN 3456 Edition P 2 April 1993 EDITE PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes Issue P 1 UDC : March 1988 Descriptors : ENGLISH VERSION Aerospac
3、e series Titanium alloy TLP64001 Annealed Sheet and strip, hot rolled aI6mm Srie arospatiale Alliage de titane TI-P64001 Recuit Tles et bandes, lamines chaud aS6mm Luft- und Raumfahrt Titanlegierung TI-P64001 Geglht Bleche und Bnder, warmgewalzt aS6mm This “Aerospace Series“ Prestandard has been dra
4、wn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). 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. Subs
5、equent 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 Standard Checking Centre (NPS) and formal ag
6、reement 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. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Resale
7、No reproduction or networking permitted without license from IHS-,-,-(EN PREN*3456 93 W 3404587 0044663 TOT W prEN 3456 Page 3 O Introduction For the use of this standard, see EN 2500-4. 1 Scope and field of application This standard specifies the requirements relating to sheet and strip, hot rolled
8、, a 16 mm, annealed, in titanium alloy TLP64001 for aerospace applications. 2 References EN 2338 EN 2500-4 EN 2600 EN 31 14-3 EN 3544-1 EN 3544-2 Sheets, titanium and titanium alloys - Hot rolled - Thickness 0,8 mm I a I 5 mm - Dimensions - Aerospace series Aerospace series - Instructions for the dr
9、afting and use of metallic material standards - Part 4 - Specific requirements for titanium and titanium alloys 2, Aerospace series - Designation of metallic semi-finished products - Rules 2, Aerospace series - Microstructure of (a + 13) titanium alloy wrought products - Part 3 - Microstructure of p
10、late 3, Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 1 - General requirements 3, Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 2 - Plate, sheet and strip 3, 1) Published as AECMA standard at
11、the date of publication of this standard 2) Published as AECMA pre-standard at the date of publication of this standard 3) In preparation at the date of publication of this standard Previous page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under
12、 license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENx345b 93 3404589 0044664 946 Material designation Chemical Element composition min. % max. Method of melting Form prEN 3456 Page 4 Titanium alloy TI - P64001 Al V 02+2N2 N2 H2 Fe C Others Ti
13、 5,5 3,5 - Base 6,75 4,5 0,25 0,03 0,0125 0,30 0,08 0,101) 0,40 Each Total See EN 3544-1 Sheet and strip 5.1 Technical specification Method of production Limit dimensions (mm) EN 3544-2 Hot rolled 6.1 Delivery condition and heat treatment 6.2 Delivery condition code Use condition and heat treatment
14、as6 Annealed 700 “C s 8 s 840 “C I t 2 30 min I AC or inert atmosphere U Delivery condition 8 Sample Test piece Heat treatment 9 Dimensions concerned mm 10 Thickness of cladding on % each face 1 I Direction of test piece 12 Temperature 0 “C _ 5.2 Dimensional standards Use condition as5 5as6 I See EN
15、 3544-2 Ambient EN 2338 - 13 14 15 16 - - - Proof stress Rpo,2 MPa 2 870 T Strength R, MPa 920Rm;1180 Elongation A% A 50 mrn Reduction of Z% area 17 I8 19 il I I Hardness Shear strength R, MPa Bending k 5 ; a = 105 I 20 Impact strength 21 Temperature 8 “C 22 Time h - stress Elongation Rupturestress
16、ua MPa a % UR MPa Elongation at A NptUre % 27 Notes (see line 98) 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-,-,-CEN PREN*345b 93 W 3404589 0044bb5 882 W prEN 3456 Page 5 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-,-,-
