1、CEN PREN*33L4 94 9 3404587 0062218 3.59 9 Edition approved for publication 1994-03-31 AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman M. Odorico 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
2、Cedex - FRANCE prEN 3314 Edition P2 March 1994 EDITE PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 UDC : Descriptors : ENGLISH VERSION Aerospace series Titanium alloy TbP6400
3、1 Solution treated and aged Bar for machining Dr75mm Supersedes issue P1 March 1988 Srie arospatiale Alliage de titane TI-P64001 Mis en solution et revenu Barres pour usinage Ds75mm Luft- und Raumfahrt Titanlegierung TI-P64001 Lsungsgeglht und ausgelagert Stangen zum Zerspanen DI75mm This “Aerospace
4、 Series“ Prestandard has been drawn up under the 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 comm
5、ent by the Member countries. Subsequent to the publication 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 Ch
6、ecking Centre (NPSI and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN European Committee for Standardization) for formal vote, I I aecma 1994 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provide
7、d by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENa3314 94 m 3404589 0062239 290 = Page 3 prEN 3314 : 1994 O Introduction For the use of this standard, see EN 2500-4. 1 Scope This standard specifies the requirements relating t
8、o bar for machining, D I 75 mm, solution treated and aged, in titanium alloy TI-P64001, for aerospace applications. 2 Normative references EN 2340 EN 2500-4 EN 2600 EN 31 14-2 EN 3544-1 EN 3544-3 Round bars - Titanium and titanium alloys - Diameter 12 mm S D I 80 mm - Dimensions - Aerospace series A
9、erospace series - Instructions for the drafting and use of metallic material standards - Part 4 : Specific requirements for titanium and titanium alloys 2, Aerospace series - Designation of metallic semi-finished products - Rules 2, Aerospace series - Microstructure of (a + ) titanium alloy - Wrough
10、t products - Part 2 : Microstructure of bars, section, forging stock and forgings 3, Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 1 : General requirements 2, Aerospace series - Titanium and titanium alloys - Wrought products - Technical specific
11、ation - Part 3 : Bar and section 2, 1) Published as AECMA Standard at the date of publication of this standard 2) Published as AECMA Prestandard at the date of publication of this standard 3) In preparation at the date of publication of this standard Previous page is blank Copyright Association Euro
12、peene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3314 94 m 3404589 O062220 TO2 m Page 4 prEN 331 4 : 1994 Method of production - Limit dimensions immi DS75 5 5Technical
13、specification EN 3544-3 5.2 Dimensional standards EN 2340 6 6.1 Delivery condition and Heat treatment Solution treated and aged 860 OC 5 0 960 OC 21 It 2 30 min I uenched in agitated water + 460 OC S0 s 600 OC 12h t s 8h /AC 1 22 I !Time 7 1 26 6.2 Delivery condition code U Use condition Delivery co
14、ndition and Heat treatment - Stress 15 Elongation A % 28 28 28 28 16 Reduction 2% L 20 2 20 L 20 2 20 17 Hardness - of area 18 Shear strength Rc MPa - - 19 Bending k- - 20 Impact strength - Rupture stress Elongation at rupture 27 Notes (see line 98) OC I I hI I MPa I I MPa - - % I Copyright Associat
15、ion Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENx3314 94 m 3404589 0062223 949 m D imm) 5 25 30 - 44 - 61 - - 97 Acceptable Not acceptable microstructure microst
16、ructure From 2 T 1 to 2 T 12 From 2 T 13 to 2 T 15 98 - 99 - From 2 L 1 From 2 T 100 to 2 T 103 to 2 L 7 2A1 Jlicrostructure From 2 L 8 From 2 T 104 to 2 T 11 7 to 2 L 15 - Ixternal defects - From 2 T 1 From 2 L 1 From 2 T 100 to 2 T 106 From 2 T 108 to 2 T 110, if number of defects less than 5 per
17、cmz of the sampling section - 2A1 to 2 T 15 to 2 L 12 - nternal defects From 2 T 200 to 2 T 201 - From 2 L 13 to 2 L 15 2 T 107 From 2 T 108 to 2 T 110, if number of defects more than 5 per cm2 of the sampling section From 2 T 11 1 to 2 T 117 - From 2 T 200 to 2 T 201 Designation Notes Typical use P
18、age 5 prEN 331 4 : 1994 See EN 3544-3 25 D 5 75 See EN 3544-3 Visual examination See EN 3544-3 Class 5. See EN 2600 1 ) Determination not required for routine acceptance. 2) As an alternative beta-transus minus 3OoC may be used as the solution heat treatment temperature. 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-,-,-
