燃气涡轮起动机离心叶轮叶片断裂分析  

Fracture Analysis of Centrifugal Impeller Blade of Gas Turbine Starter

作　　者：武威 滕旭东 隋海鸥 WU Wei;TENG Xu-dong;SUI Hai-ou(AECC Changzhou Lanxiang Machinery Co.,Ltd.,Jiangsu Changzhou 213002,China;The Chinese PLA Representative Office at 370 Factory,Jiangsu Changzhou 213002,China)

机构地区：[1]中国航发常州兰翔机械有限公司,江苏常州213002 [2]空军驻370厂军事代表室,江苏常州213002

出　　处：《失效分析与预防》2020年第3期196-201,共6页Failure Analysis and Prevention

摘　　要：燃气涡轮起动机长试到某一阶段,分解检查发现离心叶轮排气边叶片断裂。采用外观观察、断口宏微观观察、组织检查及硬度检测等方法对该断裂叶片进行原因分析。结果表明:离心叶轮排气边叶片断裂性质为高周疲劳,可能与叶盘振动有关。对离心叶轮进行振动特性计算,绘制用于振动分析的坎贝尔图,经分析,离心叶轮在设计转速附近存在高阶高频耦合共振、激振载荷较强,两者共同作用导致叶片断裂。During the long test to a certain stage of gas turbine starter,the decomposition inspecting findings that the exhaust edge blade of centrifugal impeller was fractured.Though the analysis of macro and micro observation,microstructure examination,organization inspection,hardness testing on fracture surface.The result shows that the nature of centrifugal impeller blade fracture was high cycle fatigue,it may be related to disc vibration.Calculated the frequencies of centrifugal impeller at different rotational speed as well as the camp bell diagram were worked out.The centrifugal impeller has high frequency coupling resonance near the design point,strong excitation load,the combined action of two causes result the blades fracture.

关 键 词：燃气涡轮起动机 离心叶轮 疲劳断裂 共振 

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]