Volume 40 Issue 7
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LI Hongxin, JIA Bobo, CHEN Yuxi, et al. Experimental investigation of aerodynamic instabilities in a multistage high pressure ratio compressor[J]. Journal of Aerospace Power, 2025, 40(X):20230302 doi: 10.13224/j.cnki.jasp.20230302
Citation: LI Hongxin, JIA Bobo, CHEN Yuxi, et al. Experimental investigation of aerodynamic instabilities in a multistage high pressure ratio compressor[J]. Journal of Aerospace Power, 2025, 40(X):20230302 doi: 10.13224/j.cnki.jasp.20230302

Experimental investigation of aerodynamic instabilities in a multistage high pressure ratio compressor

doi: 10.13224/j.cnki.jasp.20230302
  • Received Date: 2023-05-09
    Available Online: 2025-03-28
  • The aerodynamic instability inception of aero-engine multistage high pressure ratio compressor has weak feature, complicated mechanism and difficulty in detection and prediction. A systematic experimental investigation of rotating stall and surge inception in a full-size multistage high pressure ratio axial flow compressor was developed. The rotating stall and surge characteristics at different rotate speed and angel of variable vanes were obtained by using a multi-section, multi-phase, high sample rate test method combined with the whole ring and sector uniformed measuring point distributions. These efforts aimed at providing an important research basis for compressor aerodynamic stability research and aero engine active safety control. The results showed that at the relative corresponding speed of 0.8 and 1.0, the instability was manifested as surge; before entering the surge state, the amplitude and order of the circumferential modal wave of inception characteristic frequency increased gradually; the stage leading to instability was different at different speeds. The influence of variable vanes angle was reflected in the modal wave amplitude change before surge.

     

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