1、CEN PREN*33LL 94 W 3404589 OOb22L4 709 W Comments should be sent within six months after the date of publication to AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE Edition approved for publication 1994-04-29 AECMA STANDARD NORME AECMA AECMA NORM C5 Chairm
2、an M. Odorico prEN 331 1 Edition P 2 April 1994 UDC : DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AEROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes issue P1 March 1988 Descriptors : ENGLISH VERSION Aerospace
3、series Titanium alloy TI-P64001 Annealed Bar for machining D I150 mm Srie arospatiale Alliage de titane TI-P64001 Recuit Barres pour usinage D I150 mm Luft- und Raumfahrt Titanlegierung TI-P64001 Geglht Stangen zum Zerspanen D 5 150 mm This “Aerospace Series“ Prestandard has been drawn up under the
4、responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the pu
5、blication of this prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPSI and formal agreement of the O
6、fficial Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction
7、or networking permitted without license from IHS-,-,-CEN PREN*33Ll 94 3404569 0062235 645 Page 3 prEN 331 1 : 1994 O Introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies the requirements relating to bar for machining, D I 150 mm, annealed, in titanium alloy TI-P6
8、4001, for aerospace applications. 2 Normative references EN 2340 Round bars - Titanium and titanium alloys - Diam Aerospace series 1 ter 12 mm D I80 mm - Dimensions - EN 2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirements fo
9、r titanium and titanium alloys 2) EN 2600 Aerospace series - Designation of metallic semi-finished products - Rules 2) EN 31 14-2 Aerospace series - Microstructure of (a + ) titanium alloy - Wrought products - Part 2 : Microstructure of bars, section, forging stock and forgings 3) EN 3544-1 Aerospac
10、e series - Titanium and titanium alloys - Wrought products - Technical specification - Part 1 : General requirements 2) EN 3544-3 Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 3 : Bar and section 2) Previous page is blank 1) Published as AECMA St
11、andard at the date of publication of this standard 2) Published as AECMA Prestandard at the date of Dublication of this standard 3) In preparation at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with
12、AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN+33&3 94 3404589 O062236 581 Chemical Element min. composition n, Page 4 prEN 331 1 : 1994 Fe c Others 1) Ti AI V 02+2N2 N2 H2 5,5 3,5 - - - - - - - Each Total . Base Material designation 70 max. Method o
13、f melting Titanium alloy TI-P64001 6,75 I 4,5 I 0,25 0,03 10.0125 0,30 I 0,O 0,lO I 0,40 I See EN 3544-1 5.1 Technical specification 5.2 Dimensional standards EN 3544-3 EN 2340 Form 6 6.1 Delivery condition and Heat treatment 6.2 Delivery condition code 7 Use condition and Heat treatment Method of p
14、roduction Limit dimensions mm) Annealed 690 OC 5 0 5 840 OC I t 2 30 min I AC or inert atmosphere U Delivery condition - Bar for machining - 24 C Elongation a% - 25 Rupture stress BR MPa - 26 a Elongation at A % - 27 Notes (see line 98) 1) - - . rupture DS 150 Copyright Association Europeene des Con
15、structeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*33LL 94 = 3404589 O062217 418 Page 5 prEN 331 1 : 1994 Microstructure See EN 3544-3 See EN 31 14-2 Acceptable Not acceptable microstr
16、ucture microstructure From2T1 to2T12 From2T13 to2T15 D imrn) I25 From 2 L 1 to 2 L 7 I From 2 L 8 to 2 L 15 From 2 T 100 to 2 T 103 From 2 T 104 to 2 T 117 - 2A1 - From 2 T 200 to 2 T 201 - From 2 T 1 to 2 T 15 25 100 mm Class 5 Class 4 Designation See EN 2600 Notes 1) Determination not required for routine acceptance. Typical use 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-,-,-
