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 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.

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