1、ASD-STAN STANDARD NORME ASD-STAN ASD-STAN NORM prEN 3355 Edition P 3 November 2010 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATIONAvenue de Tervuren, 270 - B-1150 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 775 8131 - www.asd-stan.orgICS: Supersedes editio
2、n P 2 of December 1996 Descriptors: ENGLISH VERSION Aerospace series Titanium alloy TI-P64001 (Ti-6Al-4V) Annealed Extruded section De 150 mm 900 MPa Rm 1 160 mm MPa Srie arospatiale Alliage de titane TI-P64001 (Ti-6Al-4V) Recuit Profils fils De 150 mm 900 MPa Rm 1 160 MPa Luft- und Raumfahrt Titanl
3、egierung TI-P64001 (Ti-6Al-4V) Geglht Strangpreprofile De 150 mm 900 MPa Rm 1 160 MPa This “Aerospace Series“ Prestandard has been drawn up under the responsibility of ASD-STAN (The AeroSpace and Defence Industries Association of Europe - Standardization). It is published for the needs of the Europe
4、an Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, withou
5、t re-identification of the standard. After examination and review by users and formal agreement of ASD-STAN, it will be submitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national me
6、mbers have then to implement the EN at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Edition approved for publication 1 November 2010 Comments should be sent within six months after the date of publication to ASD-
7、STAN Metallic Material Domain Copyright 2010 by ASD-STAN prEN 3355:2010 (E) 2 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
8、with EN 4500-4. 1 Scope This standard specifies the requirements relating to: Titanium alloy TI-P64001 (Ti-6Al-4V) Annealed Extruded section De 150 mm 900 MPa Rm 1 160 MPa for aerospace applications. 2 Normative references The following referenced documents are indispensable for the application of t
9、his document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. EN 2032-2, Aerospace series Metallic materials Part 2: Coding of metallurgical condition in delivery condition EN 4258, Aerosp
10、ace series Metallic materials General organization of standardization Links between types of EN standards and their use EN 4500-4, Aerospace series Metallic materials Rules for drafting and presentation of material standards Part 4: Specific rules for titanium and titanium alloys 1) EN 4800-002, Aer
11、ospace series Titanium and titanium alloys Technical specification Part 002: Bar and section 1)1) Published as ASD-STAN Standard at the date of publication of this standard by Aerospace and Defence Industries Association of Europe-Standardization (ASD-STAN), (www.asd-stan.org). prEN 3355:2010 (E) 3
12、1 Material designation Titanium alloy TI-P64001(Ti-6Al-4V) 2 Others Element Al V O N O + 2N H Fe C Y Each Total Ti min. 5,50 3,50 Chemical composition %max. 6,75 4,50 0,20 0,03 0,25 0,012 5 0,30 0,08 0,005 0 0,10 0,40 Base 3 Method of melting See EN 4800-002. 4.1 Form Extruded section 4.2 Method of
13、production Extruded ( + or processed) 4.3 Limit dimension(s) mm De 150 5 Technical specification EN 4800-002 6.1 Delivery condition Annealed Heat treatment 690 C 840 C / t 30 min AC or cooled in inert atmosphere a6.2 Delivery condition code Ub7 Use condition Delivery conditionHeat treatment Characte
14、ristics 8.1 Test sample(s) See EN 4800-002. 8.2 Test piece(s) See EN 4800-002. 8.3 Heat treatment Use condition 9 Dimensions concerned mm De 150 10 Thickness of cladding on each face % 11 Direction of test piece L c12 Temperature C Ambient 13 Proof stress Rp0,2MPa 830 14 T Strength RmMPa 900 Rm 1160
15、 15 Elongation A % 8 16 Reduction of area Z % 20 17 Hardness 18 Shear strength Rc MPa 19 Bending k 20 Impact strength 21 Temperature C 22 Time h 23 Stress a MPa 24 C Elongation a % 25 Rupture stress R MPa 26 Elongation at rupture A % 27 Notes (see line 98) a, b, c prEN 3355:2010 (E) 4 30 Microstruct
16、ure See EN 4800-002. 2 Each extruded section back end 3 The sample shall represent the full cross section 7 Criteria to be agreed between the manufacturer and the purchaser 44 External defects See EN 4800-002. 1 Visual examination 61 Internal defects See EN 4800-002. 74 Surface contamination See EN
17、4800-002. 95 Marking inspection See EN 4800-002. 96 Dimensional inspection See EN 4800-002. 98 Notes a If after annealing, any straightening or stretching operations are performed on extruded section below 550 C, the extruded section shall be stress relieved by heating to a temperature 550 C 700 C /
18、 t 30 min/AC or cooled in inert atmosphere. b According to EN 2032-2. c If required, properties for LT direction to be agreed between manufacturer and purchaser. 99 Typical use prEN 3355:2010 (E) 5 100 Product qualification See EN 4800-002. Qualification programme to be agreed between manufacturer and purchaser.
