Volume 26 Issue 2
Feb.  2011
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ZHANG Xiao-wei, WANG Yan-rong, XU Ke-ning. Prediction method of blade flutter boundary in a compressor stage[J]. Journal of Aerospace Power, 2011, 26(2): 392-396.
Citation: ZHANG Xiao-wei, WANG Yan-rong, XU Ke-ning. Prediction method of blade flutter boundary in a compressor stage[J]. Journal of Aerospace Power, 2011, 26(2): 392-396.
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Prediction method of blade flutter boundary in a compressor stage

  • School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • Received Date: 2009-12-15
  • Rev Recd Date: 2010-03-16
  • Publish Date: 2011-02-28
    Abstract
  • The blade flutter boundary in a compressor stage was obtained by the developed numerical prediction method based on the energy method.The displacements of blade surface structural nodes,obtained from the computational structural dynamics (CSD) analysis,were transferred to fluid interface grids,and the designed multi-layer moving grid technique was applied to computational fluid dynamics (CFD).The unsteady analysis under the oscillating cascades was achieved to calculate the unsteady aerodynamic work for aerodynamic modal damping ratio.For a certain first-stage compressor rotor,the aeroelastic stability of different operating conditions was investigated and compared at different blade modes.And the blade flutter boundary has been obtained by analyzing the distribution of aerodynamic modal damping ratio in compressor characteristic map.The results show that the developed numerical method for aerodynamic modal damping ratio to determine the flutter boundary is feasible to preliminarily predict the aeroelastic stability of compressor blade.

     

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