AECMA PREN 3882-2001 Aerospace Series Heat Resisting Alloy NI-WH1801 Filler Metal for Welding Edition P 2 Supersedes Edition P 1 December 1994《航空航天系列抗热铝合金 NI-WH1801填充丝焊接.P2版替代.P1版》.pdf

1、e e e e Withdrawal approved 2001-09-28 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months after the date of publication to AECMA-STAN Mr Evetts Gulledelle 94 Material Domain B-1200 BRUXELLES prEN 3882 Edition P 2 September 2001 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AE

2、ROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 1 I ICs: Supersedes edition P 1 December 1994 Descriptors: ENGLISH VERSION Aerospace series Heat resisting alloy NI-WHl801 Filler metal for welding Srie arospatiale Allia

3、ge rsistant chaud NI-WH1801 Mtal dapport de soudage Luft- und Raumfahrt Hochwarmfeste Legierung NI-WH1801 Schweizusatz This Herospace Series“ Prestandard has been drawn up under the respo European Association of Aerospace Industries - S needs of the European Aerospace lndustry. It has been tech conc

4、erned Domain following member comments. extent that interchangeability is a standard. After examinafi shall not be changed to an without re-identification of the ement of AECMA-STAN it will be submitted as a for Standardization) for formal vote. Replace page 1 of the previous edition by this page Co

5、pyright 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*3882 94 3404589 0081006 78T Page 3 prEN 3882 : 1994 O Introduction For the use of this standard

6、, see EN 2500-3. 1 Scope This standard specifies the requirements relating to filler metal for welding, cold drawn and annealed, in heat resisting alloy NI-WHl801 for aerospace application. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other

7、 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 these publications apply to this European Standard only when incorporated in it by amendment or r

8、evision. For undated references the latest edition of the publication referred to applies. EN 2500-3 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 3 : Specific requirements for heat resisting alloys 1) EN 2600 Aerospace series - Designation of metalli

9、c semi-finished products - Rules EN 3879 Aerospace series - Metallic materials - Filler metals for welding - Technical specification 2) EN 4060 Aerospace series - Heat resisting alloys - Filler rods and filler wires for welding - Diameter 0,5 mm 5 D 2 5,O mm - Dimensions 2, 1) Published as AECMA Pre

10、standard at the date of publication of this standard 2) 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 license with AECMANot for ResaleNo reproduction or networking perm

11、itted without license from IHS-,-,-CEN #PREN+3882 94 3404589 OOBLOO7 bLb m Material designation Page 4 prEN 3882 : 1994 Heat resisting alloy NI-WH1 801 Chemical Element composition min. max. I C Si Mn S AI Co Cr Ti B Cu Fe Zr Ni - - - - 1,0 15,O 18,O 2,O - - - - 0,13 0,5 0,5 0,015 2,O 21,O 21,O 3,O

12、0,020 0,2 1,6 0.16 Base Method of melting I Air melted and vacuum refined or consumable electrode remelted Limit dimensions (mm) 6.1 Technical specification Form Method of production - EN 3879 Filler wire and filler rods Cold drawn I 6 6.1 Delivery condition and heat treatment 6.2 Delivery condition

13、 code 7 Use condition and heat treatment Cold drawn and annealed - U Delivery condition - 5.2 Dimensional standards EN 4060 Sample Test piece Heat treatment Dimensions concerned mm - Thickness of cladding % on each face - Direction of test piece - Temperature 0 OC - Proof stress Rp0,2 MPa - T Streng

14、th R, MPa - Elongation A Yo - Reduction of 2 YO - area Hardness Shear strength R, MPa - Bending k- - Impact strength I Temperature 1 0 I OC 1 - I Time I h7 C Elongation a YO - Rupture stress - Elongation at A Y rupture OR MPa - Notes (see line 98) - Copyright Association Europeene des Constructeurs

15、de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 5 prEN 3882 : 1994 External defects Residual stress Internal defects Designation Notes Typical use See EN 3879 See EN 3879 See EN 3879 See EN 2600 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-,-,-