航空工程进展2026，Vol.17Issue(3)：80-87,8.DOI:10.16615/j.cnki.1674-8190.2026.03.08
含损伤不锈钢叶片剩余疲劳极限研究
Research on the residual fatigue limit of damaged stainless-steel blades
摘要
Abstract
When aero-engine blades are subjected to foreign object impact,the resulting blade damage may lead to fatigue fractures,which pose a serious threat to the reliability and operational safety of the engine.In order to inves-tigate the effect of metallic foreign object damage(FOD)on the fatigue performance of aircraft engine blades,a high-speed light gas gun testing system is used to accelerate 3 mm-diameter steel balls to speeds of 290～310 m/s for the pre-damage testing of the blades.Subsequently,a high-cycle vibration fatigue testing system is used to study the impact of metallic foreign object damage on the residual fatigue limit of stainless-steel blades.By analyzing the influence of notch size on the fatigue limit and using the Peterson model,the fatigue limit of the dam-aged blades is predicted.The results show that the residual fatigue limit of the damaged blades decreases significant-ly with increasing damage depth and width,with the notch depth having the most pronounced effect on the fatigue limit.According to the predictions from the Peterson model,the residual fatigue limit of the damaged blades falls within 1.5 times the scatter band,and most experimental values are lower than the predicted values.关键词
压气机叶片/外物损伤/高周疲劳/剩余疲劳极限/轻气炮Key words
compressor blade/foreign object damage/high-cycle fatigue/residual fatigue limit/light gas gun分类
航空航天引用本文复制引用
颜诚,毛倩竹,唐小天,唐湘林,安驳,刘少华,张超..含损伤不锈钢叶片剩余疲劳极限研究[J].航空工程进展,2026,17(3):80-87,8.基金项目
陕西省秦创原引用高层次创新创业人才项目(QCYRCXM-2023-064) （QCYRCXM-2023-064）
西北工业大学中央高校科研启动经费(23GH02021) （23GH02021）
