摘要
针对航空发动机机匣裂纹故障,经断口分析确定为疲劳裂纹。采用ANSYS软件建立机匣有限元分析模型并进行机匣模态及相对振动应力计算,结合发动机使用工况得出坎贝尔共振图。经与多点激振、单点响应的模态试验及应变片电测的台架动应力测试等试验结果的对比分析,在波瓣振型、振动频率及共振转速等方面相互验证,确定了压气机机匣裂纹故障原因,并在此基础上提出了改进措施建议。经长试试验考核,改进效果良好,为航空发动机机匣的结构设计、振动故障分析提供了依据。
It was confirmed by fracture analysis that the crack of an aero-engine casing was fatigue crack.The finite element analysis model of casing was established by ANSYS software to calculate the modal and relative vibration stresses of the casing.The Campbell resonance figure was obtained according to the working conditions of the aero-engine.Compared with the test results of multi-point excitation,single point response modal test and dynamic stress test of strain gauge electrical measurement,with the mutual validation of the lobe mode,vibration frequency and resonance speed,the reason underlying in this failure mode was confirmed.Based on the above analysis,the improvement approach was put forward and proved by long-term engine test,providing a basis for structural design and vibration fault analysis of aero-engine casing.
作者
吴宏春
陈勇
洪志亮
WU Hong-chun;CHEN Yong;HONG Zhi-liang(School of Mechanical Engineering and Automation,Northeastern University,Shenyang 110819,China;The Military Representative Office In AECC Shenyang Liming Aero-Engine Corporation Ltd.,Shenyang 110043,China;AECC Shenyang Liming Aero-Engine Corporation Ltd.,Shenyang 110043,China)
出处
《燃气涡轮试验与研究》
北大核心
2017年第5期42-46,共5页
Gas Turbine Experiment and Research
