Volume 31 Issue 10
Oct.  2016
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Article Navigation >  Journal of Aerospace Power  > 2016  >  31(10): 2395-2404
YANG Hui, SHEN Zhen, ZHENG Yun. Influence of up- and downstream blade rows on aeroelastic stability of compressor rotor blade[J]. Journal of Aerospace Power, 2016, 31(10): 2395-2404. doi: 10.13224/j.cnki.jasp.2016.10.012
Citation: YANG Hui, SHEN Zhen, ZHENG Yun. Influence of up- and downstream blade rows on aeroelastic stability of compressor rotor blade[J]. Journal of Aerospace Power, 2016, 31(10): 2395-2404. doi: 10.13224/j.cnki.jasp.2016.10.012
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Influence of up- and downstream blade rows on aeroelastic stability of compressor rotor blade

doi: 10.13224/j.cnki.jasp.2016.10.012

  • 1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;

  • 2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China

  • Received Date: 2015-01-14
  • Publish Date: 2016-10-28
    Abstract
  • Aeroelastic stability analysis of compressor rotor blades, including up- and downstream blade rows interaction, was conducted by self-developed fluid-structure coupled simulation programs. Blade aerodynamic damping values under different vibration modes were calculated through the time trace of the blade vibration amplitude induced by the unsteady flow field, using a whole assembly aeroelastic model. And the influence of wakes and potential waves on the aerodynamic damping values was studied for different axial gaps. Interaction effects on the flutter characteristics of rotor-stator and inlet guide vane-rotor configurations were assessed by comparing the damping data with that of the single rotor. The results show that the aeroelastic stability is not changed monotonically with the axial gap value for the first bending modal. The results also illustrate that the intensified wake and potential wave effects could destabilize the first torsional modal, but stabilize the first bending-torsion coupled modal.

     

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