1、 STD-AECMA PREN 4374-ENGL 3777 = 3012311 0033774 UT2 Edition approved for publication AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman Comments should be sent within six months after the date of oublication to prEN 4374 Edition P 1 December 1997 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE IN
2、DUSTRIES (AECMA) Guliedelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: Descriptors: ENGLISH VERSION Aerospace series Heat resisting alloy NI-PH1 301 (NiCrl9Col8Mo4Ti3A13) Solution treated and precipitation treated Bar and section De S 200 mm Srie arospatiale Alliage
3、 rsistant chaud Ni-PH1301 (NiCrl9Col8Mo4Ti3Ai3) Mis en solution et prcipit Barres et profils De 5 200 mm Luft- und Raumfahrt Hochwarmfeste Legierung Ni-PH 1301 (NiCrl9Col8Mo4Ti3Ai3) Lsungsgegiht und ausgehrtet Stangen und Profile De 5 200 mm This “Aerospace Series“ Prestandard has been drawn up unde
4、r the responsibility of AECMA (The European Association of Aerospace Industries). 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 publicati
5、on 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 Official
6、 Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. 1997-12-31 AECMA Gulledeile 94 B-1200 BRUXELLES Mr Evetts aecma 1997 STD-AECMA PREN 4374-ENGL 1777 LnL23L1 0033775 TI7 Page 3 prEN 4374: 1997 O Introdu
7、ction 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. i Scope This standard specifies the requirements relating to: Heat re
8、sisting alloy NI-PH1301 (NiCrl9Col8Mo4Ti3A13) Solution treated and precipitation treated Bar and section De I 200 mm for aerospace applications. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are
9、 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 revision. For undated references the latest ed
10、ition of the publication referred to applies. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excluding forgings and castings) 1) EN 3235-3 Aerospace series - Heat resisting alloys - Wrought products - Technical specification - Part 3: Ba
11、r and section 1) EN 4258 Aerospace series - Metallic 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 hea
12、t resisting alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank STD-AECMA PREN q37Li-ENGL 1977 m LOL23LL 003397b 775 Page 4 prEN 4374: 1997 Material designation 1 2 4.3 1 Heat resisting alloy NI-PHI301 (NiCrl9Col8Mo4Ti3A13) min. I Element I
13、I si 0,03 - - Mn - 0,015 - 2,50 20 *) 13 15 0,015 3,25 80 *) 20,O 20,o j_/ 1 !; 1 OF 1 ;: composition % Element min. 3,OO 2.50 3,25 I max. I 0.10 I 4,OO I 5,OO - - - - Base 0,060 5 *) 0,5 *) 5 *) Method of melting Form Ti I Zr I Ag I Bi I Pb I Ni Consumable electrode remelted Bar and section Method
14、of production Limit dimension(s) mm Technical specification Wrought De 200 EN 3235-3 Delivery condition Solution treated Heat treatment Delivery condition code Use condition = 1 175 “C f 10 “C/t = 2 h/AC + O= 1 O80 “C I 10 “CA = 1 h/AC or faster W Solution treated and precipitation treated Heat trea
15、tment Delivery condition + e= 850 “C f 10 “C/t = 24 h/AC + = 760 “C f 10 “C/t = 16 h/AC Characteristics 8.1 Test sample(s) See EN 3235-3 8.2 Test piece(s) See EN 3235-3 8.3 Heat treatment Use condition 9 Dimensions concerned mm De 200 4 n Thickness of cladding on OL - I 11 I Direction of test piece
16、I See EN 3235-3 I 12 I I Temperature I e I “C I I - Rp0,2 MPa Proof stress 14 T Strength Rm MPa - I I i5 I I Elongation bl%l - - I 16 I I Reduction of area I 2 I % I I 17 I Hardness 2 340 HB I 18 I Shear strength I Rc I MPa I - I 19 I Bending lkl-1 - 20 Impact strength - 21 Temperature I eloc 815 I2
17、2 I ITime lhl I . 25 Rupture stress OR MPa 370 26 A% 2.8 Elongation at rupture 27 Notes (see line 98) - Microstructure 2 7 3ain size The “capability clause“ applies Homogeneous structure - No prononced segregation Ixternal defects - 7 - Macrostructure See EN 3235-3 G 2 2, O 2 G 2 accepted up to 5 %
18、max. area See EN 3235-3 nternal defects - 7 Marking inspection Dimensional inspection See EN 3235-3 No harmful defects Notes Typical use 7 Page 5 prEN 4374: 1997 See EN 3235-3 - Class 3 - - See EN 3235-3 See EN 3235-3 -I See EN 3235-3 - I *) p.p.m. -I Page 6 prEN 4374: 1997 Product qualification See EN 2043 2ualification programme to be agreed behveen manufacturer and purchaser.
