发动机引气管卡箍断裂原因分析  

Fracture Analysis of Aero-engine Cited Trachea Clamp

作　　者：李洋[1] 佟文伟[1] 韩振宇[1] 张开阔[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《失效分析与预防》2013年第3期167-172,共6页Failure Analysis and Prevention

摘　　要：在发动机试车过程中,其引气管卡箍发生断裂。通过对该故障引气管卡箍进行外观检查、断口分析、表面微观检查、材质分析及卡箍应力分布计算,以确定引气管卡箍断裂性质及原因。结果表明:卡箍断裂性质为高周疲劳断裂,卡箍安装端折弯处转角较小与划痕所致的应力集中是导致卡箍过早发生疲劳断裂的主要原因,振动载荷也加速了该卡箍疲劳断裂故障发生;提出了在卡箍成型加工过程中避免划痕划伤基体及适当加大折弯处转角R的改进建议。In this paper, the aero-engine cited trachea clamp was fractured during test driving was analyzed. The fracture feature of high-cycle fatigue was identified by the visual inspection, fracture analysis, surface-microscopic inspection, material analysis and stress distribution calculation of an aero-engine cited trachea clamp. The stress concentration was induced by crease on the mounting side bending of clamp. Results indicated that the stress concentration induced by small bending comer and nick as a pivotal factor led to fatigue fracture which was accelerated by the vibration loading from aero-engine cited trachea clamp. Finally, the improved proposal was provided that it should be prevented the nick chipping the matrix in forming process and the bending comer should be increased properly.

关 键 词：引气管卡箍 高周疲劳 划痕 应力集中 航空发动机 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]