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ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2025 , Vol. 46 >Issue 21: 532364 - 532364

DOI: https://doi.org/10.7527/S1000-6893.2025.32364

Special Issue: 60th Anniversary of Aircraft Strength Research Institute of China

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

  • Hao QIN ,
  • Qiang LIU ,
  • Rong JIANG ,
  • Yingdong SONG ,
  • Qiang ZHANG ,
  • Jiantao LIU ,
  • Jian DENG ,
  • Tianjian LU
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  • 1.MIIT Key Laboratory of Multifunctional Lightweight Materials and Structures，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
    2.MIIT Key Laboratory of Aero-engine Thermal Environment and Structure，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
    3.High Temperature Material Institute，Central Iron and Steel Research Institute，Beijing 100081，China
E-mail： liuqiang2015@nuaa.edu.cn

Received date: 2025-06-03

  Revised date: 2025-06-17

  Accepted date: 2025-07-07

  Online published: 2025-07-15

Supported by

National Natural Science Foundation of China(12272174);Innovation and Entrepreneurship Teams of Jiangsu Province(JSSCTD202206);Natural Science Foundation of Jiangsu Province(BK20220136);National Science and Technology Major Project （2017-Ⅵ-0008-0078）;Key Project of the Basic Science Center for Aero Engines and Gas Turbines （P2022-B-Ⅲ-007-001）

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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 impact 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.

Key words： powder metallurgy superalloy; oxidation damage; fatigue crack propagation; crack propagation rate model; high temperature

Cite this article

Hao QIN , Qiang LIU , Rong JIANG , Yingdong SONG , Qiang ZHANG , Jiantao LIU , Jian DENG , Tianjian LU . Dwell-fatigue crack growth behavior of FGH4108 alloy at high temperature[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(21) : 532364 -532364 . DOI: 10.7527/S1000-6893.2025.32364

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