Volume 26 Issue 1
Jan.  2011
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Article Navigation >  Journal of Aerospace Power  > 2011  >  26(1): 108-114
ZHANG Ming-ming, HOU An-ping, HE Xiao-fan, LI Shao-bin, LIANG Chao. Intensity analysis of blades in axial compressor with inlet distortion[J]. Journal of Aerospace Power, 2011, 26(1): 108-114.
Citation: ZHANG Ming-ming, HOU An-ping, HE Xiao-fan, LI Shao-bin, LIANG Chao. Intensity analysis of blades in axial compressor with inlet distortion[J]. Journal of Aerospace Power, 2011, 26(1): 108-114.
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Intensity analysis of blades in axial compressor with inlet distortion

  • 1.

    National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

  • 2.

    School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • Received Date: 2009-12-08
  • Rev Recd Date: 2010-04-06
  • Publish Date: 2011-01-28
    Abstract
  • A method of examining inlet distortion for intensity of compressor blades was described.A CFD (computational fluid dynamics) modeling of entire compressor flowpath was conducted to analyze the pressure fluctuation on the rotor blades due to inlet total-pressure distortion.A finite element model of the blade was then used to analyze the modal frequencies and stress,providing information on the fatigue failure potential and sensitivity to the imposed distortion.Results show that circumferential total-pressure distortion not only causes the decrease of efficiency and stall margin of compressor,but also leads to nonuniformity of aerodynamic force of blades at different circumferential positions,producing an important influence on the blade intensity.

     

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    • References(12)
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