1、AECMA STANDARD NORME AECMA AECMA NORM Withdrawal approved prEN 3892 Edition P 2 September 2001 Comments should be sent within six months after the date of publication to Material Domain PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - 8-120
2、0 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: Supersedes edition P 1 January 1995 Descriptors: ENGLISH VERSION Aerospace series Titanium alloy TI-W64001 Filler metal for welding Srie arospatiale Alliage de titane TI-W64001 Mtal dapport de soudage Luft- und Raumfahrt Titanlegieru
3、ng TI-W64001 Sc hwei Ozu Satz This “Aerospace Series“ Prestandard has been drawn up unde European Association of Aerospace Industries - Standardiza needs of the European Aerospace Industry. It has been tech concerned Domain following member comments. Subsequent to the publication of extent that inte
4、rchangeability is Afer examinati shall not be changed to an reernent of AECMA-STAN it will be submitted as a Replace page 1 of the previous edition by this page 2001-09-28 AECMA-STAN Gulledelle 94 8-1200 BRUXELLES Mr Evettc I I 0 aecrna 200 Copyright Association Europeene des Constructeurs de Materi
5、el Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENx3692 95 88 LOL23LL 0008525 436 Di Page 3 prEN 3892 : 1995 ! O introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies
6、 the requirements relating to filler metal for welding, cold drawn and annealed, titanium alloy TI-W64001 for aerospace application. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are cited at th
7、e 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 incorporated in it by amendment or revision. For undated references the latest edition of the
8、 publication referred to applies. EN 2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirements for titanium and titanium alloys 1) EN 2600 Aerospace series - Designation of metallic semi-finished products - Rules ) EN 3879 Aerospa
9、ce series - Metallic materials - Filler metals for welding - Technical specification 2) EN 4058 Aerospace series - Titanium and titanium alloys - Filler rods and filler wires for welding - Diameter 0,5 mm 5 D 5 5,O mm - Dimensions 2, w+r 1) Published as AECMA Prestandard at the date of publication o
10、f this standard 2) In preparation 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 PRENx3892 95 10123
11、11 O008526 374 Page 4 prEN 3892 : 1995 Chemical Element composition min. % max. Material designation Fe Y Others 1) T, Each Total AI V 02 N2 HZ - - - - - - - - Base 5,5 3,5 6,75 4,5 0,18 0,03 0,015 0.05 0.30 50 *) 0,tO 0,40 Titanium alloy TI-W64001 6.1 Delivery condition Cold drawn and annealed Cons
12、umable electrode vacuum arc remelted I Method of melting 8 Form Sample Test piece Heat treatment Method of production Limit dimensions (mm) 9 10 11 Filler wire and filler rods Dimensions concerned mm - Thickness of cladding yo on each face Direction of test piece - - Cold drawn - 12 13 14 15 16 -. -
13、 - - 5.1 Technical specification I EN 3879 Temperature 51 OC - Proof stress Rp0,2 MPa - .,i T Strength I?, MPa - Elongation A Yo 1 - Reduction of Z YO - area I 5.2 Dimensional standards EN 4058 Rupture stress Elongation at rupture oR MPa A Yo _ _ - - 6.2 Delivery condition code Use condition and hea
14、t treatment Notes (see line 98) U *) 1) Delivery condition - I Characteristics 17 I Hardness I - 18 I Shear strength I R, IMPa I - 19 Bending - t 20 Impact strength - 21 22 23 24 25 26 27 - - - - - - I Temperature I O 1 OC I - Time Stress C 1 Elongarion 1 a 1 YO 1 - Copyright Association Europeene d
15、es Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN*3892 95 LOI12311 0008527 200 tl Page 5 prEN 3892 : 1995 Ixternal defects 3esiduai stress nternal defects Designation Notes Typical use See EN 3879 See EN 3879 See EN 3879 See EN 2600 “) p.p.m. 1) Capability clause applies 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-,-,-
