含损伤不锈钢叶片剩余疲劳极限研究OA

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.