Investigation of Compressor Surge Triggering Mechanisms Under Inlet Distortion Condition

Compressors are crucial for aeroengines, but compressor surge, especially under inlet distortion, threatens engine performance and safety. This study focuses on the surge triggering mechanisms in such conditions. Experiments were conducted on a high - speed axial - flow compressor test platform, with a flow distorter used to create inlet distortion. Three-hole probes and Kuite sensors measured flow parameters. Numerical simulations using CFD were also carried out. Results show that inlet distortion advances the stall triggering tail cone position and delays the surge point one. The surge frequency is around 4.8 Hz, determined by the compression system's Helmholtz resonance frequency. The numerical method has high accuracy. Inlet distortion leads to uneven flow, blade load imbalance, and rotating stall, with the expansion of the low-energy flow region triggering surge. This research deepens the understanding of surge mechanisms and can contribute to anti-surge strategy development for better aero-engine performance and safety.