某型辅助动力装置可调导向叶片断裂故障分析  

Failure Analysis for Rolling Bearing of an Aero-engine Compressor

作　　者：刘杰薇 张春月 侯明 Liu Jie-wei;Zhang Chun-yue;Hou Ming(AECC Hunan Aviation Powerplant Research Institute,Hubei Zhuzhou 412002;Key Laboratory of Aero-engine Vibration Technology,Aero Engine Corporation of China,Hubei Zhuzhou 412002)

机构地区：[1]中国航空发动机集团湖南动力机械研究所,湖南株洲412002 [2]中国航空发动机集团航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《内燃机与配件》2025年第2期87-89,共3页Internal Combustion Engine & Parts

基　　金：2023年国家自然科学基金“非定常流激励下航空压气机动叶片在线监测与故障诊断研究”(编号:92060105)阶段性研究成果。

摘　　要：对于航空发动机而言,进口导叶的断裂往往带来下游各部件的损坏,严重影响飞行安全。本文以某型辅助动力装置导向叶片发生的高周疲劳断裂故障为研究对象,从故障树出发进行排查,确定导叶角度异常是故障发生的直接原因。通过高周疲劳试验确定了导叶的高周疲劳特性,并进行了动应力测试,确认了导叶角度异常变小会造成叶片交变应力水平的突增,甚至在高转速状态下已超过允许的交变应力值。本文揭示了故障机理,为其他型号提供参考。For aircraft engine,the fracture of inlet guide vane always causes damage to other components downstream and influence flight safety badly.This article does research on high-cycle fatigue failure of inlet guide vane of a certain model of APU.Starting from reviewing the fault tree,this article confirmed that the anomaly of the angle of guide vane is the main reason to the failure.The high-cycle fatigue property of the guide vane is discovered by high-cycle fatigue test.After the dynamic stress test,it is discovered that the amorous decrease of the angle may lead a sharp increase of alternating stress level of the guide vane.The alternating stress level is even higher than the allowable value at high rotate speed.This article reveals the failure mechanism,and can be referred by other model as well.

关 键 词：辅助动力装置 导向叶片 高周疲劳 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]