压气机转子叶片掉块失效机理分析  

Failure Mechanism Analysis of Compressor Rotor Blade Fragment-off

作　　者：王全 王寅超 佟文伟 翟贤超 李青 WANG Quan;WANG Yin-chao;TONG Wen-wei;ZHAI Xian-chao;LI Qing(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2022年第6期121-126,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：针对航空发动机压气机转子叶片在工作中发生的掉块故障,通过对故障叶片进行宏观检查、断口分析、叶尖端面检查、材质及有限元分析等工作,确定了压气机转子叶片掉块的性质和原因。结果表明:叶片掉块性质源于叶尖与加强筋之间前缘区域叶盆侧表面的疲劳裂纹,裂纹扩展并产生瞬时断裂,最终形成掉块。排除了叶片由外来物打伤及材质和冶金缺陷等异常因素造成掉块的可能性。掉块原因为故障叶片叶尖与机匣封严涂层之间存在较重的非均匀碰摩,在叶片进气边叶尖与加强筋之间区域产生应力集中,在振动应力和离心载荷的共同作用下,导致叶片萌生疲劳裂纹并扩展,进而形成掉块。为避免类似故障再次发生,建议适当加大转子叶片与机匣的径向间隙,并严格控制装配质量和机匣封严涂层尺寸。Aimed at the fragment-off fault of aeroengine compressor rotor blade in operation,the nature and cause of the fragment-off of compressor rotor blade were identified by visual inspection,fracture surface analysis,inspection of blade-tip,material properties analysis,and finite element analysis of the failed blade. The results show that the nature of fragment-off was fatigue crack which originated from blade concave side surface at the leading edge area between blade tip and stiffener. The crack propagated until a sudden fracture led to the fragment broken off from the blade. The possibility of fragment-off caused by anomalies such as foreign object damage, material and metallurgical defects was excluded by analysis. The blade-tip had serious non-uniform rubbing with the casing seal coating. Stress concentration was generated at the leading edge area between blade-tip and stiffener. Under the combined effect of vibration stress and centrifugal load,fatigue cracks of the blade were initiated,propagated and then the fragment broken off from the blade. In order to avoid the recurrence of similar faults,it is suggested to appropriately increase the radial clearance between rotor blades and casing,and strictly control the assembly quality and the dimension of casing seal coating.

关 键 词：压气机转子叶片 掉块 疲劳裂纹 有限元分析 封严涂层 碰摩 振动应力 航空发动机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]