压气机中叶片与叶盘耦合系统振动特性研究

CALCULATION OF THE BLADE AND THE BLADE-DISC COUPLING SYSTEM OF COMPRESSOR

基于有限元方法建立某型航空发动机压气机叶片模型,通过模态仿真获得了该叶片在榫头固支约束下的动力学特性,研究了离心力对叶片振动的影响,并通过模态试验对计算模型和仿真数据进行验证;利用循环对称法对建立的叶片轮盘有限元模型进行振动分析,获得叶轮耦合系统在不同工作转速下的振型和频率,并与单个固支叶片进行比较,结果表明,相同阶次下叶片耦合系统的自振频率较低;通过Campbell图分析得出了叶片耦合系统可能发生共振的频率及相应的转子转速,为其故障诊断、可靠性分析以及寿命估算提供了参考依据。

A type of aero engine compressor blade model was built based on finite element. Dynamics of the clamped constrained blade was obtained by modal simulation and the influence of centrifugal force on the vibration of blades was researched. And then,the modal test was carried out to validate the model and the simulation data. Vibration analysis of blade disc finite element model was carried out based on cyclic symmetry method. The vibration mode and frequency of the coupling system with different working speeds were obtained. The result shows that the natural frequency of the coupling system is lower in the same order when compared with a single fixed blade. The resonance frequency and the corresponding rotor speed could be obtained by analysis of Campbell contours. It provides reference for the fault diagnosis,reliability analysis and life estimation.