摘要
某型航空发动机压气机四级转子叶片是故障多发叶片。对该型发动机压气机四级转子叶片进行振动特性试验和分析,结果表明,四级转子叶片失效是由于发动机在转速为3700r/min时叶片产生共振导致疲劳失效。对排故措施进行了初步研究,指出通过采用LD7-1铝合金替换LY2铝合金来改变叶片固有频率的实际意义不大。
The compressor blades of the 4th stage in an aero-engine fractured several times. Vibration characteristics of the blade were tested and analyzed. The results show that resonance of the blade leads to fatigue failure when rotation speed of engine is 3700r/min. In this paper, measures to avoid failure were studied. It was pointed out that there was no practical meaning of using LD7-1 aluminum alloy in place of LY2 aluminum alloy to change the natural frequency of the blades.
出处
《失效分析与预防》
2006年第4期10-12,共3页
Failure Analysis and Prevention
关键词
压气机叶片
疲劳
振动特性
compressor blade
fatigue
vibration characteristics
