AECMA PREN 4327-2001 Aerospace Series Heat Resisting Alloy CO-WH1401 (CoCr26Ni11W8) Filler Metal for Welding Wire and Rod Edition P 2 Supersedes Edition P 1 March 1997 Replaced by .pdf

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1、AECMA STANDARD NORME AECMA AECMA NORM prEN 4327 Edition P 2 September 2001 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 8110 - Fax. (+32) 2 775 8111 Supersedes edition P 1 March 1997 ICs: Descriptors:

2、 ENGLISH VERSION Aerospace series Heat resisting alloy CO-WH1401 (CoCr26Nil I W8) Filler metal for welding Wire and rod Srie arospatiale Alliage rsistant chaud CO-WH1401 (CoCr26NillW8) Mtal dapport de soudage Fil et baguette Luft- und Raumfahrt Hochwarmfeste Legierung CO-WH1401 (CoCr26NilI W8) Schwe

3、izucatz Draht und Stbe needs of the European Aerospace Industry. It has been tech concerned Domain following member comments. Subsequent to the publication of extent that interchangeability is After examinati not be changed to an re-identification of the Replace page I of the previous edition by thi

4、s page Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX I I Withdrawal approved 2001 -09-28 Comments should be sent within six months after the date of publication to Gulledelle 94 AECMA-STAN 8-1200 BRUXELLES Material

5、 Domain Mr Evetts I I aecma 20 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-,-,-STD-AECMA PREN i327-ENGL 1777 101231L 0011334 14b Page 3 prEN 4327 : 199

6、7 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is described in EN 4258. This standard has been prepared in accordance with EN 4500-3. 1 Scope This standard specifies the requirements relating

7、to : Heat resisting alloy CO-WH1401 (CoCr26Nill W8) Filler metal for welding Wire and rod for aerospace applications. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are cited at the appropriate p

8、laces 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 publication re

9、ferred to applies. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excluding forgings and castings) 1) EN 3879 Aerospace series - Metallic materials - Filler metal for welding - Technical specification 1) EN 4258 Aerospace series - Metall

10、ic materials - General organization of standardization - Links between types of EN standards and their use 1) EN 4500-3 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 3 : Specific rules for heat resisting alloys 1) Previous page is blank 1) P

11、ublished as AECMA Prestandard 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-,-,-Page 4 prEN 4327 : 1997 C si

12、- 0,45 0,55 1,OO 1 1 I Material designation Mn P S Cr Ni W Fe Co - - - 24,50 9,50 7,OO - 1,OO 0,040 0,040 26,50 11,50 8,OO 2,OO Base 2 3 4.1 4.2 4.3 Chemical Element composition min. % max. Method of melting Form Method of production Limit dirnension(s) rnm Wire and rod 6.1 Delivery condition Heat t

13、reatment Cold drawn Cold drawn and annealed - 5 I Technical specification 10 EN 3879 Thickness of cladding on % each face Temperature o “C Proof stress Rpa,2 MPa Strength R, MPa 6.2 I Delivery condition code I - - - U 18 19 20 21 - 22 23 24 25 26 27 - - - _. I 7 1 Use condition I Delivery condition

14、I Shear strength R, MPa - Bending k- - Impact strength - - Temperature e OC Time h Stress Oa MPa - C Elongation a% - Rupture stress OR MPa - Elongation at A yo - Notes (see line 98) - - rupture II I I I Heazatment Characteristics 8.1 I Test sample(s) I I 8.3 1 Heat treatment 9 I Dimensions concerned

15、 I mm I I I - 11 I Direction of test piece I Elongation T % I Reduction of areal Z I % I I 17 I Hardness I I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IH

16、S-,-,-STD-AECMA PREN 4327-ENGL 1777 LOL23LL 00LL33b TL7 - - - - Page 5 prEN 4327 : 1997 See EN 3879 See EN 3879 - - ixternal defects ?esidual stress nternal defects Marking inspection Dimensional inspection Notes rypicai use See EN 3879 See EN 3879 See EN 3879 I Copyright Association Europeene des C

17、onstructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 4327 : 1997 Product qualification See EN 2043 2ualification 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-,-,-