关键词: 压气机, 声共振, 声模态, 声反射系数, 相位

Abstract: The acoustic resonance of aero-engine compressor is a complex unsteady flow phenomenon, which can cause aero-dynamic instability of the compressor and may even lead to compressor blade fatigue failure. Aiming at the problem of vibration fatigue failure of the first-stage rotor blade of a certain type of high pressure compressor, the theoretical study of acoustic resonance of the compressor is carried out, and the analysis model of acoustic wave propagation and reflection between blade rows is established. 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 occurred. The experiment results show that the speed of the compressor is consistent with the predicted results, and the first-stage rotor blades show frequency locking characteristics. There are strong circumferential propagation characteristics in the sound field and the pressure pulsation field. The circumferential propagation mode is 13 orders, which accords with the characteristic frequency theory analysis results. The pulsating pressure amplitude near the first stage rotor is the largest, where is the main reflection area of acoustic wave, which is consistent with the predicted results.

Key words: compressor, acoustic resonance, acoustic modal, acoustic reflection coefficient, phase