航空发动机压气机声共振是一种复杂非定常流动现象，能够造成压气机气动不稳定，甚至可能导致压气机叶片疲劳破坏。针对某高压压气机一级转子叶片振动疲劳失效问题，开展压气机声共振理论研究，建立声波在叶片排间传播与反射的分析模型。发展压气机声共振特性预测方法，对压气机声共振进行预测分析。基于发展的理论预测方法，开展某压气机声共振试验测试，通过多参数动态测试分析技术，获取压气机发生声共振时管道内部模态传播特性和叶片振动特性。试验结果表明：压气机发生声共振时转速与预测结果相吻合，一级转子叶片表现出锁频特征，压气机内脉动压力场、同级转子叶片间均存在强烈的周向传播特性，周向传播模态为13阶，符合特征频率的理论分析结果。一级转子附近脉动压力幅值最大，为声波轴向传播的主反射区，与预测结果相吻合。

The acoustic resonance of aero-engine compressors is a complex unsteady flow phenomenon， which can cause aerodynamic instability of the compressor and may even lead to compressor blade fatigue failure. Aiming at the vibration fatigue failure of the first-stage rotor blade of a certain type of high-pressure compressor， we conduct a theoretical study on acoustic resonance of the compressor， and establish an analysis model of acoustic wave propagation and reflection between blade rows. The acoustic resonance test of a certain type of compressor is carried out based on the developed theoretical prediction method， and the acoustic mode propagation characteristics in the pipeline and blade vibration characteristics are obtained by the multi-parameter dynamic test and analysis technology when the sound resonance of the compressor occurs. The experimental results show that the speed of the compressor is consistent with the predicted results， and that the first-stage rotor blades exhibit frequency locking characteristics. Strong circumferential propagation characteristics are displayed in the sound field and the pressure pulsation field. The circumferential propagation mode is 13 orders， in accordance with the characteristic frequency theory analysis results. The pulsating pressure amplitude near the first stage rotor is the largest which is the main reflection area of acoustic wave， consistent with the predicted results.