航空发动机进口整流支板防冰槽裂纹故障分析  

Fault Analysis of Anti-icing Tank Cracks of the Aeroengine Inlet Vane Strut

作　　者：张弛 王雅谋 ZHANG Chi;WANG Ya-mou(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》2020年第4期47-51,共5页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了排除某型发动机进口整流支板裂纹故障,利用故障树的排查方法分析了故障原因,并对试验件进行了断口分析、尺寸测量、动应力及残余应力测试、防冰槽结构形式及表面状态疲劳对比试验。结果表明:支板防冰槽裂纹产生的主要原因是进气机匣焊接后残余应力较大,且防冰槽边缘存在应力集中,在试车过程中,防冰槽应力集中处在转子叶片激振的作用下萌生裂纹并扩展。针对故障原因开展了结构改进设计与试验,提出了修改防冰槽宽度、倾角尺寸及增加重熔层控制等措施,使得该故障得以排除。In order to eliminate the crack fault of a certain type of engine inlet vane strut, the reason of the fault was analyzed by the troubleshooting method of fault tree. Fracture surface analysis,dimension measurement, test of dynamic and residual stress,contrast test of structural style and surface fatigue of anti-icing tank were carried out. The results show that the main reason for the anti-icing tank cracks is that the residual stress of the inlet casing is large after welding and the stress concentration exists at the edge of the anti-icing tank.During the test run,the stress concentration of the anti-ice tank produces cracks and expands under the action of excitation of rotor blade.The structural improvement design and test were carried out for the fault reasons,and the measures to modify the width of the anti-icing tank,the size of the inclination angle and to increase the control of the remelting layer were put forward,which could make the fault be eliminated.

关 键 词：整流支板 防冰槽 进气机匣 裂纹 振动 风扇 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]