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高温条件下FGH4108合金的保载-疲劳裂纹扩展行为

秦豪 刘强 江荣 宋迎东 张强 刘建涛 邓健 卢天健

航空学报2025,Vol.46Issue(21):117-130,14.
航空学报2025,Vol.46Issue(21):117-130,14.DOI:10.7527/S1000-6893.2025.32364

高温条件下FGH4108合金的保载-疲劳裂纹扩展行为

Dwell-fatigue crack growth behavior of FGH4108 alloy at high temperature

秦豪 1刘强 1江荣 2宋迎东 2张强 3刘建涛 3邓健 1卢天健1

作者信息

  • 1. 南京航空航天大学 多功能轻量化材料与结构工信部重点实验室,南京 210016
  • 2. 南京航空航天大学 航空发动机热环境与热结构工信部重点实验室,南京 210016
  • 3. 钢铁研究总院 高温材料研究所,北京 100081
  • 折叠

摘要

Abstract

Fatigue crack growth experiments and interrupted tests are conducted on the fourth-generation powder metallurgy superalloy FGH4108 under varying temperatures and dwell time.The influence of temperature and dwell time on crack growth behavior is analyzed using characterization techniques such as Scanning Electron Microscopy(SEM),Electron Backscatter Diffraction(EBSD),and Electron Probe Microanalysis(EPMA).The mechanism by which oxidation damage affects crack growth is revealed.A fatigue crack growth rate model describing the mechanical-oxidation coupling effect is proposed.The results show that as temperature and dwell time increase,the crack growth rate rises and fatigue life decreases significantly.Fractographic analysis reveals that at 650℃,fatigue cracks primarily propagate transgranularly with relatively flat fracture surfaces,while at temperatures above 750℃,fatigue cracks mainly propagate intergranularly,accompanied by the formation of secondary cracks.Concurrently,phenomena such as alterations in crack tip morphology and oxide formation were observed during crack propagation,elucidating the im-pact of oxidation on crack growth.The proposed model can better describe the fatigue crack growth rate at different temperatures and dwell time.At the same time,the effects of mechanical damage and oxidative damage on crack growth are decoupled,and the temperature dependence of oxidative damage parameters is determined.

关键词

粉末高温合金/氧化损伤/疲劳裂纹扩展/裂纹扩展速率模型/高温

Key words

powder metallurgy superalloy/oxidation damage/fatigue crack propagation/crack propagation rate model/high temperature

分类

航空航天

引用本文复制引用

秦豪,刘强,江荣,宋迎东,张强,刘建涛,邓健,卢天健..高温条件下FGH4108合金的保载-疲劳裂纹扩展行为[J].航空学报,2025,46(21):117-130,14.

基金项目

国家自然科学基金(12272174) (12272174)

国家科技重大专项(2017-Ⅵ-0008-0078) (2017-Ⅵ-0008-0078)

江苏省双创团队(JSSCTD202206) (JSSCTD202206)

江苏省自然科学基金(BK20220136) (BK20220136)

航空发动机及燃气轮机基础科学中心重点项目(P2022-B-Ⅲ-007-001) National Natural Science Foundation of China(12272174) (P2022-B-Ⅲ-007-001)

National Science and Technology Major Project(2017-Ⅵ-0008-0078) (2017-Ⅵ-0008-0078)

Innovation and Entrepreneurship Teams of Jiangsu Province(JSSCTD202206) (JSSCTD202206)

Natural Science Foundation of Jiangsu Province(BK20220136) (BK20220136)

Key Project of the Basic Science Center for Aero Engines and Gas Turbines(P2022-B-Ⅲ-007-001) (P2022-B-Ⅲ-007-001)

航空学报

OA北大核心

1000-6893

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