航空发动机高压转子连接部件松动故障动力学特性研究  

Research on dynamic characteristics of aero-engine high-pressure rotor connection component loosening fault

作　　者：张庆山 胡振辉 洪军[1] 裴世源[1] ZHANG Qingshan;HU Zhenhui;HONG Jun;PEI Shiyuan(Key Laboratory of Education Ministry for Modern Design and Rotor-Bearing System,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西安交通大学现代设计及转子轴承系统教育部重点实验室,西安710049

出　　处：《航空动力学报》2024年第3期146-161,共16页Journal of Aerospace Power

基　　金：国家自然科学基金(NSFC_51975456);国家科技重大专项(2017-Ⅶ-0010-0105)。

摘　　要：针对航空发动机高压转子在实际工作过程中存在的连接部件松动现象,建立了考虑松动故障特性的高压转子Timoshenko梁模型,探讨了结合面刚度、转速、松动螺栓数量、松动故障位置、拧紧力矩对转子动力学的影响,并对理论分析结果进行了试验验证。结果表明:故障系统升速过程中呈现出明显亚临界共振现象,且临界峰值转速提前;松动螺栓数量越多,系统倍周期分岔现象越明显;松动故障位于转子跨距中间时对系统动力学的影响较大;螺栓拧紧力矩减小,系统第二阶临界峰值转速提前;试验数据与理论分析结果比较吻合,提出的理论方法具有一定的准确性和适用性。研究结果为航空发动机高压转子连接部件松动故障的进一步研究提供了理论和试验基础。To study the effects of the connection component loosening fault in aero-engine highpressure rotor,a Timoshenko beam model considering loosening fault was established.The influences of joint surface stiffness,speed,number of loose bolts,position of loosening fault and tightening torque on rotor dynamics were discussed.The results of theoretical analysis were verified by experiments.The results showed that there was an obvious subcritical resonance in the speed-up process of the fault system,and the critical peak speed was generated in advance.The more number of loose bolts indicated the more obvious period-doubling bifurcation of the system.The loosening fault was located in the middle of the rotor span,which had a great influence on the system dynamics.When the bolt tightening torque was reduced,the second critical peak speed of the system was generated in advance.The experimental data were in good agreement with the results of theoretical analysis,and the proposed theoretical method had certain accuracy and applicability.The research results provide a theoretical and experimental basis for further study on connection component loosening fault of aero-engine high pressure rotor.

关 键 词：航空发动机高压转子 松动故障 转子动力学 谐波平衡法 非线性振动 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]