SAE AMS 4920H-2025 钛合金锻件 6al - 4v Alpha-Beta或Beta加工退火（UNS R56400）

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For more information on this standard, visit

https://www.sae.org/standards/content/AMS4920H/

AEROSPACE

MATERIAL SPECIFICATION

AMS4920™

REV. H

Issued 1984-07

Revised 2019-12

Stabilized 2025-12

Superseding AMS4920G

Titanium Alloy, Forgings

6AI - 4V

Alpha-Beta or Beta Processed, Annealed

(Composition similar to UNS R56400)

RATIONALE

AMS4920H has been declared “STABILIZED” by AMS Committee G Titanium and Refractory Metals Committee. This

document will no longer be updated and may no longer represent standard industry practice. This document was stabilized

because Committee G can find no producers for this document.

NOTE: Previously, this document was Revised. The last technical update of this document occurred in December 2019.

Users of this document should refer to the cognizant engineering organization for disposition of any issues with

reports/certifications to the specification, including exceptions listed on the certification. In many cases, the

purchaser may represent a sub-tier supplier and not the cognizant engineering organization.

STABILIZED NOTICE

AMS4920H has been declared “STABILIZED” by SAE AMS Committee G Titanium and Refractory Metals and will no longer

be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of

technical requirements. Newer technology may exist.

SAE INTERNATIONAL AMS4920™H Page 1 of 6

1. SCOPE

1.1 Form

This specification covers a titanium alloy in the form of forgings, 6.000 inches (152.40 mm) and under in cross-sectional

thickness and forging stock of any size.

1.2 Application

These forgings have been used typically for parts that do not require heat treatment but require high mechanical properties

in the annealed condition and for which processing above the beta transus is permissible, but usage is not limited to such

applications. This alloy exhibits high strength-to-weight ratios up to 750 °F (399 °C).

1.2.1 Certain 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 this 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 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.

AMS2249 Chemical Check Analysis Limits, Titanium and Titanium Alloys

AMS2750 Pyrometry

SAE INTERNATIONAL AMS4920™H Page 2 of 6

AMS2808 Identification, Forgings

ARP982 Minimizing Stress-Corrosion Cracking in Wrought Titanium Alloy Products

ARP1917 Clarification of Terms Used in Aerospace Metals Specifications

AS1814 Terminology for Titanium Microstructures

AS6279 Standard Practice for Production, Distribution, and Procurement of Metal Stock

2.2 ASTM Publications

Available from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken, PA 19428-2959, Tel: 610-

832-9585, www.astm.org.

ASTM E8/E8M Tension Testing 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

ASTM E1447 Determination of Hydrogen 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 Inductively Coupled Plasma

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 determined 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

Element

Min

Max

Aluminum

5.50

6.75

Vanadium

3.50

4.50

Iron

0.30

Oxygen

0.20

Carbon

0.10

Nitrogen

0.05

(500 ppm)

Hydrogen

0.0125

(125 ppm)

Yttrium (3.1.1)

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 for routine acceptance. Variation over maximum is not permitted for yttrium.

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标签： #合金 #锻件 #钛合金

摘要：

本页面详细介绍 SAE AMS 4920H-2025 标准，该标准规范了采用 6Al-4V 钛合金（UNS R56400）制造的锻件要求，涵盖 Alpha-Beta 或 Beta 加工工艺及退火状态。作为航空航天领域广泛使用的高强度钛合金材料，AMS 4920H 标准明确了锻件的化学成分、力学性能、热处理规范及质量控制要求。该标准适用于需要优异强度重量比、耐腐蚀性和抗疲劳性能的结构部件，适用于飞机框架、发动机零部件及紧固件等关键应用场景。更新至2025年版的H版本在工艺控制与检测要求上进行了优化

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SAE AMS 4920H-2025 钛合金锻件 6al - 4v Alpha-Beta或Beta加工退火（UNS R56400）

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