某型发动机压气机转子叶片叶尖裂纹故障排除方案试验验证  

Verification Test of Troubleshooting Concept for an Aeroengine Compressor Rotor Blade Tip Crack Failure

作　　者：黄爱萍[1] 彭建[1] 

机构地区：[1]贵州航空发动机研究所,贵州平坝561102

出　　处：《航空发动机》2009年第3期47-49,共3页Aeroengine

摘　　要：针对某型发动机压气机转子叶片叶尖裂纹故障,制订了4种排故方案。进行了振动特性、应力分布测量及台架动频动应力测量对比试验,对各排故方案作出了评价,从而确定了最终的排故方案。试验表明4种排故方案均能有效降低振动应力,但方案4优于其它3种方案,能使振动应力水平降低60.6%,频率提高11.5%。Four troubleshooting concepts were recede for an aeroengine compressor rotor blode tip crock failure. The comparative experiments of ribation characteristic, stres distribution measurements and measurements of dynamic frequency and dynamie stress for bench were conducted. The various troubleshooting concepts were evaluated. The experimental results show that for troubleshooting concepts can reduce the ribration stress effectively but the fourth concept is prior to the others which can reduce the vibration stress level by 60.6%, and improve the frequeney by 11.5%.

关 键 词：压气机转子叶片 裂纹故障 排故方案 削角 航空发动机 振动应力 试验 

分 类 号：V216.21[航空宇航科学与技术—航空宇航推进理论与工程] TQ327.1[化学工程—合成树脂塑料工业]