Volume 22 Issue 12
Dec.  2007
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Article Navigation >  Journal of Aerospace Power  > 2007  >  22(12): 2025-2030
WU Yun, LI Ying-hong, ZHU Jun-qiang, SU Chang-bing, LIANG Hua, SONG Hui-min, LI Gang. Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability[J]. Journal of Aerospace Power, 2007, 22(12): 2025-2030.
Citation: WU Yun, LI Ying-hong, ZHU Jun-qiang, SU Chang-bing, LIANG Hua, SONG Hui-min, LI Gang. Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability[J]. Journal of Aerospace Power, 2007, 22(12): 2025-2030.
shu

Experimental investigation of using plasma aerodynamic actuation to extend low-speed axial compressor's stability

  • 1.

    The Engineering Institute, Air Force Engineering University, Xi'an 710038, China

  • 2.

    Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100080, China

  • Received Date: 2007-06-12
  • Rev Recd Date: 2007-09-25
  • Publish Date: 2007-12-28
    Abstract
  • The effect of plasma aerodynamic actuation on low-speed axial compressor performance and stability range was investigated experimentally.Aplasma aerodynamic actuation treated casing(PAATCTM) was designed.Asingle low-speed axial compressor rotor with no inlet guide vanes was tested.Pressure rise coefficient and flow coefficient for the compressor test rig were calculated with/without plasma actuation at a constant rotor speed to represent compressor performance and stability range.The experimental results show that,with plasma actuation,the mass flow coefficients near stall is decreased by 5.2% and 5.07% when the rotor speed reaches 900 r/min and 1080 r/min respectively.The influences of different actuation voltages and different actuation locations were investigated experimentally.Compressor's stability became larger along with the rise of actuation voltage.The actuation away from rotor's leading edge for 49.5% axial chord can extend compressor's stability more than the actuation away from the rotor's leading edge for 8.3% axial chord.

     

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