1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p
3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497
4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AMS4905F AEROSPACE MATERIAL SPECIFICATION AMS4905 REV. F Issued 2000-07 Revised 2017-11 Superse
5、ding AMS4905E Titanium Alloy, Damage-Tolerant Grade Plate 6Al - 4V Beta Annealed (Composition similar to UNS R56400) RATIONALE AMS4905F results from a Five-Year Review and update of this specification that adds ASTM E2994 to analytical methods (3.1), removes larger sample size for hydrogen (covered
6、by ASTM E1447) (Table1), revises microstructure requirements (3.5.4), revises reporting (4.4), and identification (5.1). 1. SCOPE 1.1 Form This specification covers one type of titanium alloy plate in the beta-annealed condition up through 4.000 inches (101.60 mm) inclusive in thickness (see 8.6). 1
7、.2 Application This plate has been used typically for parts in damage-tolerant, stress-corrosion-resistant applications requiring strength up to 750 F (399 C), but usage is not limited to such applications. 1.3 Classification Products shall be of the following conditions: 1.3.1 Type I - Air Cooled P
8、roduct cooled from secondary anneal in accordance with 3.4.2.1 and meeting stress-corrosion resistance requirements of 3.5.3. 1.3.2 Type II - Slow Cooled Product cooled from secondary anneal in accordance with 3.4.2.2. Stress-corrosion resistance requirements of 3.5.3 are not applicable. 1.3.3 When
9、no type is specified, Type I shall be supplied. SAE INTERNATIONAL AMS4905F Page 2 of 9 1.4 Safety-Hazardous Materials While the materials, methods, applications, and processes described or referenced in this specification may involve the use of hazardous materials, this specification does not addres
10、s the hazards that may be involved in such use. It is the sole responsibility of the user to ensure familiarity with the safe and proper use of any hazardous materials and to take necessary precautionary measures to ensure the health and safety of all personnel involved. 1.5 Stress Corrosion Certain
11、 processing procedures and service conditions may cause these products to become subject to stress-corrosion cracking; ARP982 recommends practices to minimize such conditions. 2. APPLICABLE DOCUMENTS The issue of the following documents in effect on the date of the purchase order forms a part of thi
12、s specification to the extent specified herein. The supplier may work to a subsequent revision of a document unless a specific document issue is specified. When the referenced document has been cancelled and no superseding document has been specified, the last published issue of that document shall
13、apply. 2.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AMS2242 Tolerances Corrosion and Heat Resistant Steel, Iron Alloy, Titanium, and Titanium Alloy Sh
14、eet, Strip, and Plate AMS2249 Chemical Check Analysis Limits Titanium and Titanium Alloys AMS2631 Ultrasonic Inspection, Titanium and Titanium Alloy Bar, Billet and Plate AMS2750 Pyrometry AMS2809 Identification Titanium and Titanium Alloy Wrought Products ARP982 Minimizing Stress-Corrosion Cracking
15、 in Wrought Titanium Alloy Products ARP1917 Clarification of Terms Used in Aerospace Metals Specifications AS4194 Sheet and Strip Surface Finish Nomenclature AS6279 Standard Practice for Production, Distribution, and Procurement of Metal Stock 2.2 ASTM Publications Available from ASTM International,
16、 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken, PA 19428-2959, Tel: 610-832-9585, www.astm.org. ASTM A480/A480M General Requirements for Flat-Rolled Stainless and Heat-Resisting Steel Plate, Sheet, and Strip ASTM E8/E8M Tension Testing of Metallic Materials ASTM E399 Linear-Elastic Plane S
17、train Fracture Toughness KIC of Metallic Materials ASTM E539 Analysis of Titanium Alloys by X-Ray Fluorescence Spectrometry ASTM E1409 Determination of Oxygen and Nitrogen in Titanium and Titanium Alloys by Inert Gas Fusion SAE INTERNATIONAL AMS4905F Page 3 of 9 ASTM E1447 Determination of Hydrogen
18、in Titanium and Titanium Alloys by the Inert Gas Fusion Thermal Conductivity/Infrared Detection Method ASTM E1941 Determination of Carbon in Refractory and Reactive Metals and Their Alloys by Combustion Analysis ASTM E2371 Analysis of Titanium and Titanium Alloys by Direct Current Plasma and Inducti
19、vely Coupled Atomic Emission Spectrometry ASTM E2994 Analysis of Titanium and Titanium Alloys by Spark Atomic Emission Spectrometry and Glow Discharge Atomic Emission Spectrometry 3. TECHNICAL REQUIREMENTS 3.1 Composition Shall conform to the percentages by weight shown in Table 1; carbon shall be d
20、etermined in accordance with ASTM E1941, hydrogen in accordance with ASTM E1447, oxygen and nitrogen in accordance with ASTM E1409, and other elements in accordance with ASTM E539, ASTM E2371, or ASTM E2994. Other analytical methods may be used if acceptable to the purchaser. Table 1 - Composition E
21、lement Min Max Aluminum 5.60 6.30 Vanadium 3.60 4.40 Iron - 0.25 Oxygen - 0.12 Carbon - 0.05 Nitrogen - 0.03 (300 ppm) Hydrogen - 0.0125 (125 ppm) Yttrium - 0.005 ( 50 ppm) Other Elements, each (3.1.1) - 0.10 Other Elements, total (3.1.1) - 0.40 Titanium remainder 3.1.1 Determination not required fo
22、r routine acceptance. 3.1.2 Check Analysis Composition variations shall meet the applicable requirements of AMS2249. 3.2 Melting Practice Alloy shall be multiple melted. The first melt shall be made by vacuum consumable electrode, nonconsumable electrode, electron beam cold hearth, or plasma arc col
23、d hearth melting practice. The subsequent melt or melts shall be made using vacuum arc remelting (VAR) practice. Alloy additions are not permitted in the final melt cycle. 3.2.1 The atmosphere for non-consumable electrode melting shall be vacuum or shall be argon and/or helium at an absolute pressur
24、e not higher than 1000 mm of mercury. 3.2.2 The electrode for nonconsumable electrode melting shall be water-cooled copper. 3.3 Condition Hot rolled, beta-annealed, secondary annealed, descaled, and flattened, having a surface appearance comparable to a commercial corrosion-resistant steel No. 1 fin
25、ish (see 8.2). Plate product shall be produced using standard industry practices designed strictly for the production of plate stock to the procured thickness. Bar, billet, forgings, or forging stock shall not be substituted for plate. SAE INTERNATIONAL AMS4905F Page 4 of 9 3.4 Annealing 3.4.1 Plate
26、 shall be beta-annealed by heating to the beta transus temperature plus 50 F (28 C), holding at the selected temperature within 25 F (14 C) for not less than 30 minutes, and cooling in air to below 1000 F (538 C). Plate shall not be stacked during beta-annealing or air cooling. 3.4.2 Secondary Annea
27、ling 3.4.2.1 Type I Product Secondary Annealing After beta-annealing in accordance with 3.4.1, plate shall then be annealed by heating to 1350 F 25 F (732 C 14 C), holding at temperature for not less than 2 hours, and air cooling. 3.4.2.2 Type II Product Secondary Annealing After beta-annealing in a
28、ccordance with 3.4.1, plate shall then be annealed by heating to 1350 F 25 F (732 C 14 C), holding at temperature for not less than 2 hours, and slow cooling at a rate not faster than 100 F per hour (56 C per hour) to meet the requirements of 3.5, except 3.5.3. 3.4.3 Pyrometry shall be in accordance
29、 with AMS2750. 3.4.4 Beta transus temperature shall be determined by any method acceptable to purchaser. 3.4.5 Plate shall be held at temperature for sufficient time to ensure that the most remote section (i.e., mid-thickness position in the center of the plate) is at temperature for at least 30 min
30、utes. 3.5 Properties Plate shall conform to the following requirements after all thermo-mechanical processing (including any flattening or stress relief in accordance with 3.7) is completed: 3.5.1 Tensile Properties Shall be as specified in Table 2, determined in accordance with ASTM E8/E8M with the
31、 rate of strain set at 0.005 inch/inch/minute (0.005 mm/mm/minute) and maintained within a tolerance of 0.002 inch/inch/minute (0.002 mm/mm/minute) through the 0.2% offset yield strain. Table 2 Table 2A - Minimum tensile properties, inch/pound units Nominal Thickness Inches Tensile Strength ksi Yiel
32、d Strength at 0.2% Offset ksi Elongation in 2 Inches or 4D Long. and Trans. % 0.1875 to 0.500, incl 130 115 10 Over 0.500 to 1.000, incl 127 112 10 Over 1.000 to 2.000, incl 125 108 8 Over 2.000 to 4.000, incl 122 108 8 Table 2B - Minimum tensile properties, SI units Nominal Thickness Millimeters Te
33、nsile Strength MPa Yield Strength at 0.2% Offset MPa Elongation in 50.8 mm or 4D Long. and Trans. % 4.762 to 12.70, incl 896 793 10 Over 12.70 to 25.40, incl 876 772 10 Over 25.40 to 50.80, incl 862 745 8 Over 50.80 to 101.60, incl 841 745 8 SAE INTERNATIONAL AMS4905F Page 5 of 9 3.5.1.1 The results
34、 of tensile tests on each lot shall show a maximum difference between the transverse and longitudinal directions of 6.00 ksi (41.4 MPa) for the tensile strength and the yield strength. 3.5.1.2 Mechanical property requirements for product outside the size range covered by 1.1 shall be agreed upon bet
35、ween purchaser and producer. 3.5.2 Fracture Toughness Plate 0.500 inch (12.70 mm) and over in nominal thickness shall meet a KIc or KQ not lower than 85 ksi inch (93 MPa m) determined in accordance with ASTM E399 using the compact tension specimen with the minimum “W“ dimension as specified in Table
36、 3; plate may be machined not more than 0.010 inch (0.25 mm) on each face. Table 3 - Fracture toughness, specimen dimension Plate Thickness Inches Plate Thickness mm W Inches, min W mm, min 0.500 to 1.000, incl 12.70 to 25.40, incl 5.0 127 Over 1.000 Over 25.40 3.0 76 3.5.2.1 Post-test Validity Veri
37、fication for Specimen In order to establish a measured level of KQ as a valid KIC value, all of the validity criteria of ASTM E399 shall be satisfied. Otherwise, the value reported shall be KQ. 3.5.2.2 Test Data At the time of testing, the following data shall be recorded on the load-displacement te
38、st record: Date Specimen identification Load scale calibration (pounds per inch (kN/m) chart) Maximum stress intensity (K, maximum) during final pre-cracking Displacement scale calibration (inch per inch (mm/mm) chart) Loading rate in terms of KI in accordance with ASTM E399 PQ, pounds (kN) Pmax, po
39、unds (kN) Temperature Relative humidity Testing laboratory Test machine 3.5.2.3 Reduction of Test Data Test data shall be reduced as specified in ASTM E399 to calculate a KQ value and to determine if a valid KIC property value has been measured. Tensile coupons shall be provided for validity checkin
40、g. The yield strength value used shall be the yield strength measured for the same plate that the fracture toughness specimen was taken. One or more transverse (T-L) tensile specimens taken immediately adjacent to the location of the fracture toughness specimen are required (see 8.3.4). 3.5.2.4 Inva
41、lid Test Results If a value of KQ is invalid solely on the basis of either of the following criteria, (1) W-a 1.10, or both, then such value KQ may be compared to the minimum level specified in 3.5.2 for qualification purposes. Otherwise (i.e., in the case of a KQ value invalid on the basis of other
42、 ASTM E399 criteria - e.g., crack front curvature, etc.), a minimum of a single retest shall be required. SAE INTERNATIONAL AMS4905F Page 6 of 9 3.5.3 Stress-Corrosion Resistance (Type I Material Only) Plate 0.500 inch (12.70 mm) and greater thickness shall be tested in the transverse (T-L) directio
43、n to determine the KSL value in accordance with 3.5.3.1 (see 8.3.4). Acceptance criteria for KSL shall be 60.0 ksi inch (66 MPa m ) for Type I material. 3.5.3.1 Stress-Corrosion Resistance Testing This testing procedure covers the determination of fracture toughness for Ti-6Al-4V beta-processed plat
44、e in an environment of 3.5% NaCl solution in distilled water. 3.5.3.1.1 List of Terms K = A stress intensity factor derived from fracture mechanics KSL = A stress intensity factor sustained at a specified level for 20 minutes in aqueous 3.5% NaCl W = Specimen width a = Total crack length (sum of not
45、ch and fatigue crack length) 3.5.3.1.2 Apparatus Stress-corrosion test apparatus shall meet the requirements of ASTM E399 for compact tension specimens with the addition of a salt water reservoir. 3.5.3.1.3 Test Specimen Compact tension specimens shall be prepared in accordance with 3.5.2. The speci
46、mens shall be pre-cracked in accordance with ASTM E399. Post-test examination shall be made to ensure that the crack front (as pre-cracked) meets the criteria of ASTM E399. 3.5.3.1.4 Test Procedures 3.5.3.1.4.1 Calculate the load required to develop KSL = 60 ksi inch (66 MPa m ), using the calculati
47、ons for compact tension specimens of ASTM E399. 3.5.3.1.4.2 Assemble a salt water reservoir enclosing the pre-cracked area. Fill the reservoir with salt water, making sure that the crack tip is completely immersed. 3.5.3.1.4.3 Load the specimen to KSL = 60 ksi inch (66 MPa m ) at a load rate in term
48、s of KI in accordance with ASTM E399. Hold the load at KSL for 20 minutes. If the specimen has not failed after 20 minutes at KSL, raise the load at the same rate as used initially until fracture. 3.5.3.1.4.4 Calculate K at fracture in accordance with ASTM E399. 3.5.4 Microstructure The microstructu
49、re shall be uniform and consist of basketweave (Widmanstatten) or colony morphology and shall not contain primary or equiaxed alpha phase. Prior beta grains exceeding 0.075 inch (1.90 mm) in width or length shall constitute no more than 10% of the microstructure when examined at 10 to 50X magnification. One microstructural determination shall be made for each lot. The specimen surfa
