AECMA PREN 3965-2001 Aerospace Series Titanium Alloy TI-B17001 Filler Metal for Brazing Rolled Foil Edition P 3《航空航天系列.航空航天系列钛铝合金TI-B17001硬钎焊用填充金属轧制箔》.pdf

《AECMA PREN 3965-2001 Aerospace Series Titanium Alloy TI-B17001 Filler Metal for Brazing Rolled Foil Edition P 3《航空航天系列.航空航天系列钛铝合金TI-B17001硬钎焊用填充金属轧制箔》.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 3965-2001 Aerospace Series Titanium Alloy TI-B17001 Filler Metal for Brazing Rolled Foil Edition P 3《航空航天系列.航空航天系列钛铝合金TI-B17001硬钎焊用填充金属轧制箔》.pdf（4页珍藏版）》请在麦多课文档分享上搜索。

1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3965 Edition P 3 September 2001 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 EI 10 - Fax. (+32) 2 775 E1 i 1 Supersedes edition P 2 ICs: May 1995 Descriptors

2、: ENGLISH VERSION Aerospace series Titanium alloy TI-617001 Filler metal for brazing Rolled foil Srie arospatiale Alliage de titane TI-B17001 Mtal dapport de brasage Feuillard lamin Luft- und Raumfahrt Titanlegierung TI-BI7001 Hartlot in Form von gewalzter Folie Subsequent to the publication of exte

3、nt that interchangeability is After examinati not be changed to an re-identification of the reement of AECMA-STAN it will be submiffed as a Replace page I of the previous edition by this page Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 92138 IS

4、SY-LEC-MOULINEAUX CEDU( Withdrawal approved 2001-09-28 Comments should be sent within six months after the date of publication to Gulledelle 94 AECMA-STAN B-1200 BRUXELLES Material Domain Mr Evetts 1 I aecma 200 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IH

5、S under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 3965 : 1995 1 O Introduction For the use of this standard, see EN 2500-6. 1 Scope This standard specifies the requirements relating to titanium alloy braze filler metal TI-B17001

6、in rolled foil form 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 dated referenc

7、es, 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. ,. Part 6 : Specific requirements for braze alloys 1) EN 2600 Aerospa

8、ce series - Designation of metallic semi-finished products - Rules 2) EN 3875 Aerospace series - Braze alloys - Technical specification 1) EN 4062 Aerospace series - Dimensional standards for filler metals for brazing for rolled foil 2) wt 1 ) In preparation at the date of publication of this standa

9、rd 2) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank 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-,-,

10、-Page 4 prEN 3965 : 1995 I I I 14,O 14.0 - - - composition ,in. O! max. 16.0 16.0 0.02 0,02 0.04 AECMA PRENt3965 95 = LOL23LL 0008605 520 111 - Base 0.10 Material designation Titanium base brazing alloy TI - B17001 I Element Chemical I N2 I O2 I Cu I Ni Method of melting I Inert gas or vacuum mefted

11、 Form Method of production Limit dimensions mm) Rolled foil Coiamination of Cu - Ni foils between two Ti - foils 5.1 Technical specification EN 3875 5.2 Dimensional standards EN 4062 6.1 Delivery condition and heat treatment 6.2 Delivery condition code Use condition and heat treatment I As manufactu

12、red or annealed U Delivery condition - Characteristics Sample - Test piece Heat treatment - - Dimensions concerned mm - Thickness of cladding % - on each face Direction of test piece - Temperature 6 OC - Proof stress Rp0,2 MPa - i - It, ., Elongation A % Reduction of Z YO area Hardness 4, - j/ , I.

13、A Y, I - I, (ICft, Shear strength U, MPa - I, Bending k- - ( i -1 I Impact strength - Temperature 6 OC - I Time lhl - Stress * a, MPa - C Elongation a% - Rupture stress GR MPa - Elongation at A % - rupture Notes (see line 98) Copyright Association Europeene des Constructeurs de Materiel Aerospatial

14、Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN83965 95 1012311 ooo8b06 467 = Page 5 prEN 3965 : 1995 External defects Thermal analysis (Differential thermal analysis) Wettability (fusion test) Designation Notes Ty

15、pical use See EN 3876 See EN 3876 Liquidus : 940 OC Solidus : SOO OC See EN 3876 Test plate to be Ti alloy See EN 2600 Joining titanium alloys. 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-,-,-