AECMA PREN 4342-2001 Aerospace Series Titanium TI-W99001 Filler Metal for Welding Wire and Rod Edition P 2《航空系列 钛TI-W99001填充金属焊接电线杆.P2版取代.P1版 1997年3月被取代EN 4342》.pdf

《AECMA PREN 4342-2001 Aerospace Series Titanium TI-W99001 Filler Metal for Welding Wire and Rod Edition P 2《航空系列 钛TI-W99001填充金属焊接电线杆.P2版取代.P1版 1997年3月被取代EN 4342》.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 4342-2001 Aerospace Series Titanium TI-W99001 Filler Metal for Welding Wire and Rod Edition P 2《航空系列 钛TI-W99001填充金属焊接电线杆.P2版取代.P1版 1997年3月被取代EN 4342》.pdf（5页珍藏版）》请在麦多课文档分享上搜索。

1、AECMA STANDARD NORME AECMA AECMA NORM Withdrawal approved Comments should be sent within six months after the date of ublication to prEN 4342 Edition P 2 September 2001 Material Domain PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - 8-1200

2、 BRUXELLES - Tel. (+32) 2 775 81 1 O - Fax. (+32) 2 775 81 11 Supersedes edition P 1 March 1997 ICs: Descriptors: ENGLISH VERSION Aerospace series Titanium TI-W99001 Filler metal for welding Wire and rod Srie arospatiale Titane TI-W99001 Mtal dapport de soudage Fil et baguette Luft- und Raumfahrt Ti

3、tan TI-W99001 Schweizusatz Draht und Stbe After examinati ement of AECMA-STAN it will be submitted as a for Standardization) for formal vote. I Replace page 1 of the previous edition by this page I 2001-09-28 AECMA-STAN Gulledelle 94 8-1200 BRUXELLES Mr Evettc I I aecrna 20( Copyright Association Eu

4、ropeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 4342 : 1997 O Introduction This standard is part of the series of EN metallic material standards for aerospace appl

5、ications. The general organization of this series is described in EN 4258. This standard has been prepared in accordance with EN 4500-4. 1 Scope This standard specifies the requirements relating to : Titanium TI-W99001 Filler metal for welding Wire and rod for aerospace applications. 2 Normative ref

6、erences This European 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 th

7、ese publications apply to this European Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excl

8、uding forgings and castings) 1) EN 3879 Aerospace series - Metallic materials - Filler metal for welding - Technical specification 1) EN 4258 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use 1) EN 4500-4 Aerospace ser

9、ies - Metallic materials - Rules for drafting and presentation of material standards - Part 4 : Specific rules for titanium and titanium alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank Copyright Association Europeene des Constructeurs de

10、 Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 4342-ENGL 1977 LO123Ll OOLL558 441 M 1 Material designation - - - - - - - Base 0,18 0,05 50 *) 0,20 0,08 0,lO 0,40 Limit dimension(s) mm 6.2

11、 7 Heat treatment - Delivery condition code U Use condition Delivery condition Heat treatment - Time h Stress Ca MPa Elongation a% - - - 26 Elongation at A % rupture Page 4 prEN 4342 : 1997 Titanium TI-W99001 Element I N2 I H2 I Fe 1 C l+l Ti Each Total 02 2 C hem cal composition % I min. I max. Met

12、hod of melting Consumable electrode vacuum arc remelted Wire and rod Cold drawn - EN 3879 16.1 I Delivery condition I Cold drawn and annealed I Characteristics - 18.1 I Test sample(s) I 18.2 I Test piece(s) I - 18.3 I Heat treatment I - - mm I 11 I Direction of test piece I 1 12 I I Temperature I 0

13、I “C I - 1 13 I I Proof stress I Rpo,21 MPa I - I Elongation A % - Redudinofarea Z % - Hardness - Shear strength I R, MPa - I 19 I Bending lkl-1 - - I 20 I Impact strength I I21 I ITemperature I e I “C I - Rupture stress I OR 1 MPa 1 I- l Notes (see line 98) Copyright Association Europeene des Const

14、ructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 43qZ-ENGL 1997 = L0123LL 0011559 388 - - External defects Residual stress Internal defects See EN 3879 See EN 3879 Marking inspec

15、tion - - - Dimensional inspection See EN 3879 See EN 3879 *) p.p.m. 1) Determination not required for routine acceptance Notes rypicai use -I See EN 3879 Page 5 prEN 4342 : 1997 -I - Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot

16、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 4342 : 1997 Product qualification See EN 2043 3ualification programme to be agreed between manufacturer and purchaser. 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-,-,-