Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃

JIANG He; DONG Jianxin; ZHANG Maicang; YAO Zhihao

doi:10.16080/j.issn1671-833x.2021.01/02.062

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Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃

更新时间：2025-10-30

- Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃
- Aeronautical Manufacturing Technology Vol. 64, Issue 1/2, (2021)
- 作者机构：
  
  北京科技大学材料科学与工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2021.01/02.062
  CLC：
- Published：2021
- 稿件说明：
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江河，董建新，张麦仓，姚志浩. 800℃以上服役涡轮盘用难变形镍基高温合金研究进展[J]. 航空制造技术, 2021, 64(1/2): 62-73. JIANG He,DONG Jianxin, ZHANG Maicang, YAO Zhihao. Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃. Aeronautical Manufacturing Technology, 2021, 64(1/2): 62-73.

JIANG He, DONG Jianxin, ZHANG Maicang, et al. Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃[J]. Aeronautical Manufacturing Technology, 2021, 64(1/2).
江河，董建新，张麦仓，姚志浩. 800℃以上服役涡轮盘用难变形镍基高温合金研究进展[J]. 航空制造技术, 2021, 64(1/2): 62-73. JIANG He,DONG Jianxin, ZHANG Maicang, YAO Zhihao. Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃. Aeronautical Manufacturing Technology, 2021, 64(1/2): 62-73. DOI： 10.16080/j.issn1671-833x.2021.01/02.062.

JIANG He, DONG Jianxin, ZHANG Maicang, et al. Development of Typical Hard-to-Deform Nickel-Base Superalloy for Turbine Disk Served Above 800℃[J]. Aeronautical Manufacturing Technology, 2021, 64(1/2). DOI： 10.16080/j.issn1671-833x.2021.01/02.062.

摘要

大推重比航空发动机涡轮盘需在更高温度下服役，为满足更高温度服役航空发动机涡轮盘材料的需求，在新合金的发展过程中合金化程度和 γ′ 相含量逐渐提高。其中 GH4151、GH4175 和 GH4975 合金是 800℃以上服役变形高温合金的典型代表。对难变形高温合金国内外的发展趋势、3 种典型合金的特征和发展过程进行了概述，并对难变形高温合金制备过程中开坯工艺和超塑性等问题进行了探讨。为充分发挥 800℃以上服役高相含量难变形高温合金的优势和作用，需对合金成分设计特点、组织特性、热变形和超塑性变形过程中相的作用机制等方面开展相应的理论研究工作。

Abstract

The aero-engine with high thrust-weight ratio needs to operate under higher temperature. In order to meet the requirements of high performance aero-engine

the alloying degree and mass fraction of γ′ phase keep increasing in the development of new wrought superalloy with higher service temperature. GH4151

GH4175 and GH4975 are typical nickelbase wrought superalloys with service temperature up to 800℃ . In present work

the domestic and overseas development of hard-to-deform superalloy is summarized. The characteristics of the three typical hard-to-deform nickel-base superalloy with high γ′ phase content are compared. In addition

the cogging technology and superplasticity characteristics of hard-todeform superalloy are discussed in detail. In summary

in order to fulfill the advantages of hard-to-deform superalloy with high γ′ phase content for turbine disk served above 800℃

there is still much research work need to be done in chemical composition and microstructure characteristics

characteristics of γ′ phase and control mechanism during hot deformation and superplasticity of the alloy

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