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<p>Foreign object damage (FOD) is a common issue during the aero-engine operation process, which can usually lead to high-cycle fatigue (HCF) fracture failure of fan and compressor blades. To investigate the effect of post-impact heat treatment on the HCF performance of compressor blade alloy GH4169 with FOD, this study uses an FOD simulation device to conduct impact tests on specimens. The impacted specimens are subjected to heat treatment of varying duration, followed by HCF testing. The results show the presence of adiabatic shear bands (ASB) on the exit side of the impact crater, with lengths mostly in the range of 100-250&#xa0;μm. The HCF strength of GH4169 alloy is reduced by 41.5% due to the microscopic defects generated by FOD. But its mechanical properties and fatigue resistance are enhanced to some extent by certain post-impact heat treatment processes, and its beneficial effect appears to be stress-ratio-dependent. The most significant beneficial influence on the HCF strength is at the stress ratio of − 1 condition indicated by an increase of 61.4% in HCF strength compared with the as-damaged specimen and is associated with the fatigue crack initiation mode transition from ASB cracking to slip band cracking. As the stress ratio of the HCF tests increases from − 1 to 0.5, the crack initiation is dominated by slip band cracking, and the beneficial influence of post-impact heat treatment on the HCF strength diminishes.</p>

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Influence of Post-Impact Heat Treatment on the High Cycle Fatigue Behavior of GH4169 Alloy

  • 期刊论文

  • 发表日期：

    2026年4月1日

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  • X. Zhang,
  • X. Jia,
  • Z. W. Zhang,
  • Y. Chen,
  • R. Jiang,
  • Y. D. Song

摘要

Foreign object damage (FOD) is a common issue during the aero-engine operation process, which can usually lead to high-cycle fatigue (HCF) fracture failure of fan and compressor blades. To investigate the effect of post-impact heat treatment on the HCF performance of compressor blade alloy GH4169 with FOD, this study uses an FOD simulation device to conduct impact tests on specimens. The impacted specimens are subjected to heat treatment of varying duration, followed by HCF testing. The results show the presence of adiabatic shear bands (ASB) on the exit side of the impact crater, with lengths mostly in the range of 100-250 μm. The HCF strength of GH4169 alloy is reduced by 41.5% due to the microscopic defects generated by FOD. But its mechanical properties and fatigue resistance are enhanced to some extent by certain post-impact heat treatment processes, and its beneficial effect appears to be stress-ratio-dependent. The most significant beneficial influence on the HCF strength is at the stress ratio of − 1 condition indicated by an increase of 61.4% in HCF strength compared with the as-damaged specimen and is associated with the fatigue crack initiation mode transition from ASB cracking to slip band cracking. As the stress ratio of the HCF tests increases from − 1 to 0.5, the crack initiation is dominated by slip band cracking, and the beneficial influence of post-impact heat treatment on the HCF strength diminishes.