Volume 29 Issue 1
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Article Navigation >  Journal of Aerospace Power  > 2014  >  29(1): 125-132
WU Yan-hui, WANG Xiao, LANG Fang-yu, WU Jun-feng. Numerical simulation of stall inception in single-stage axial-flow compressor[J]. Journal of Aerospace Power, 2014, 29(1): 125-132. doi: 10.13224/j.cnki.jasp.2014.01.016
Citation: WU Yan-hui, WANG Xiao, LANG Fang-yu, WU Jun-feng. Numerical simulation of stall inception in single-stage axial-flow compressor[J]. Journal of Aerospace Power, 2014, 29(1): 125-132. doi: 10.13224/j.cnki.jasp.2014.01.016
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Numerical simulation of stall inception in single-stage axial-flow compressor

doi: 10.13224/j.cnki.jasp.2014.01.016

  • School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

  • Received Date: 2013-03-29
  • Publish Date: 2014-01-28
    Abstract
  • Based on the investigation results involving pre-stall behavior in subsonic single-stage axial-flow compressor test rig under isolated-rotor environment, whole-passage simulations were further carried out to investigate the stall inception process under single-stage environment. The monitoring results from the numerical probes indicate that the local breakdown of flow-field of single-stage axial-flow compressor is initiated at rotor tip region during stall inception process. The simulation results were validated by available experimental data. Detailed instantaneous flow-field analysis demonstrates that the type of pre-stall wave is "multi-cell" disturbance under single-stage environment in contrast to "spike" disturbance under isolated-rotor environment, implying that the presence of stator alters the pattern of near-tip circumferential loading distribution. However, the flow mechanism for the emergence of "multi-cell" disturbance is still represented by the formation and movement of tip secondary vortex.

     

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