SAE AMS 5605H-2024

VIP专享

史蒂文 2025-05-11 9 177.32KB 7 页 20星币

__________________________________________________________________________________________________________________________________________

SAE Executive Standards Committee 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 therefrom, 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.

recording, or otherwise, or used for text and data mining, AI training, or similar technologies, without the prior written permission of SAE.

TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada)

Tel: +1 724-776-4970 (outside USA)

Fax: 724-776-0790

Email: CustomerService@sae.org

SAE WEB ADDRESS: http://www.sae.org

For more information on this standard, visit

https://www.sae.org/standards/content/AMS5605H/

AEROSPACE

MATERIAL SPECIFICATION

AMS5605™

REV. H

Issued 1971-11

Reaffirmed 2011-08

Revised 2024-09

Superseding AMS5605G

Nickel Alloy, Corrosion- and Heat-Resistant, Sheet, Strip, and Plate

41.5Ni - 16Cr - 37Fe - 2.9Cb (Nb) - 1.8Ti

Consumable Electrode or Vacuum Induction Melted,

1800 °F (982 °C) Solution Heat Treated (Alloy 706)

(Composition similar to UNS N09706)

RATIONALE

AMS5605H is the result of a Five-Year Review and update of the specification. The revision updates composition testing

and reporting (see 3.1 and 3.1.1), updates finish requirements (see 3.3.1), clarifies bend test requirements (see 3.5.1.3),

adds pyrometry control (see 3.5.2), adds strain rate control during tensile testing (see 3.5.2.1.1), establishes minimum sizes

for tests (see 3.5.1, 3.5.2.1, 3.5.2.2, and 8.2), and updates the exceptions requirements (see 3.5.3 and 8.5).

1. SCOPE

1.1 Form

This specification covers a corrosion- and heat-resistant nickel alloy in the form of sheet, strip, and plate 1.00 inch (25.4 mm)

and under in nominal thickness.

1.2 Application

These products have been used typically for parts requiring good machinability and high strength at room and cryogenic

temperatures and for short-time use up to 1000 °F (538 °C), particularly for those parts which are formed or welded and

then heat treated to develop required properties, but usage is not limited to such applications.

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.

AMS2262 Tolerances, Nickel, Nickel Alloy, and Cobalt Alloy Sheet, Strip, and Plate

SAE INTERNATIONAL AMS5605™H Page 2 of 7

AMS2269 Chemical Check Analysis Limits, Nickel, Nickel Alloys, and Cobalt Alloys

AMS2283 Composition Testing Methods for Nickel- and Cobalt-Based Alloys

AMS2371 Quality Assurance Sampling and Testing, Corrosion and Heat-Resistant Steels and Alloys, Wrought

Products and Forging Stock

AMS2750 Pyrometry

AMS2807 Identification, Carbon and Low-Alloy Steels, Corrosion- and Heat-Resistant Steels and Alloys, Sheet, Strip,

Plate, and Aircraft Tubing

AS7766 Terms Used in Aerospace Metals Specifications

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 E18 Rockwell Hardness of Metallic Materials

ASTM E112 Determining Average Grain Size

ASTM E140 Hardness Conversion Tables for Metals Relationship Among Brinell Hardness, Vickers Hardness,

Rockwell Hardness, Superficial Hardness, Knoop Hardness, Scleroscope Hardness, and

Leeb Hardness

ASTM E290 Bend Testing of Material for Ductility

2.3 Definitions

Terms used in AMS are defined in AS7766.

3. TECHNICAL REQUIREMENTS

3.1 Composition

Composition shall conform to the percentages by weight shown in Table 1, determined in accordance with AMS2283 or by

other analytical methods acceptable to the purchaser.

SAE INTERNATIONAL AMS5605™H Page 3 of 7

Table 1 - Composition

Element

Min

Max

Carbon

0.06

Manganese

0.35

Silicon

0.35

Phosphorus

0.020

Sulfur

0.015

Chromium

14.50

17.50

Nickel

39.00

44.00

Columbium (Niobium)

2.50

3.30

Tantalum

0.05

Titanium

1.50

2.00

Aluminum

0.40

Boron

0.006

Copper

0.30

Iron

remainder

3.1.1 The producer may test for any element not listed in Table 1 and include this analysis in the report of 4.4. Reporting

of any element not listed in the composition table is not a basis for rejection unless limits of acceptability are

specified by the purchaser.

3.1.2 Check Analysis

Composition variations shall meet the applicable requirements of AMS2269.

3.2 Melting Practice

Alloy shall be produced by multiple melting using consumable electrode practice in the remelt cycle or shall be induction

melted under vacuum. If consumable electrode remelting is not performed in vacuum, electrodes that have been produced

by vacuum induction melting shall be used for remelting.

3.3 Condition

The product shall be supplied in the following condition:

3.3.1 Sheet and Strip

Sheet and strip shall be hot or cold rolled, solution heat treated, and, unless solution heat treatment is performed in an

atmosphere yielding a bright finish, descaled producing a uniform finish.

3.3.2 Plate

Plate shall be hot rolled, solution heat treated, and descaled.

3.4 Heat Treatment

No specific solution heat treatment is specified, but it is recommended that the product be solution heat treated by heating

in a suitable protective atmosphere to a temperature within the range 1750 to 1850 °F (954 to 1010 °C), holding at the

selected temperature within ±25 °F (±14 °C) for a time commensurate with section thickness but not less than 5 minutes,

and cooling at a rate equivalent to an air cool or faster. Pyrometry shall be in accordance with AMS2750.

3.4.1 Continuous Heat Treatment

When continuous heat treating is used, process parameters (e.g., furnace temperature set points, heat input, travel rate,

etc.) for continuous heat-treating lines shall be established by the producer and validated by testing of product to the

requirements of 3.5.

文档加载中……请稍候！
如果长时间未打开，您也可以点击刷新试试。

下载文档到电脑，查找使用更方便

亲，本站95%以上的标准规范都面向会员免费，办理VIP会员下载更省钱，平均每篇不到2元

立即下载

标签： #MS

摘要：

SAE AMS 5605H-2024标准规范是由SAE International（国际自动机工程师学会）发布的最新版本，旨在取代旧版AMS 5605G，对耐腐蚀钢（主要为440C型不锈钢）的化学成分、热处理工艺、机械性能及质量控制要求进行了全面更新与修订。该标准适用于航空航天、高精度轴承、阀门及耐磨组件等对材料疲劳强度、硬度和耐腐蚀性有严格要求的领域。通过遵循AMS 5605H-2024，制造商可以确保所使用的高碳马氏体不锈钢在高温回火或低温淬火后具备稳定一致的微观结构和抗磨损性能。此外，新版

展开>> 收起<<

SAE AMS 5605H-2024.pdf

共7页,预览3页

还剩页未读，继续阅读

声明：本文档系会员上传，若文档所含内容侵犯了您的版权或隐私，请立即通知，我们立即给予侵权申诉删除！

SAE AMS 5605H-2024

相关推荐

开通VIP享超值会员特权

相关内容

热门标签

举报选择: