Volume 31 Issue 8
Aug.  2016
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HUANG Zhong-shan, WANG Yan-rong, FU Zhi-zhong. Aero-elastic stability analysis of an axial compressor with splitter rotor[J]. Journal of Aerospace Power, 2016, 31(8): 1964-1972. doi: 10.13224/j.cnki.jasp.2016.08.023
Citation: HUANG Zhong-shan, WANG Yan-rong, FU Zhi-zhong. Aero-elastic stability analysis of an axial compressor with splitter rotor[J]. Journal of Aerospace Power, 2016, 31(8): 1964-1972. doi: 10.13224/j.cnki.jasp.2016.08.023
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Aero-elastic stability analysis of an axial compressor with splitter rotor

doi: 10.13224/j.cnki.jasp.2016.08.023

  • 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: 2014-11-13
  • Publish Date: 2016-08-28
    Abstract
  • The aero-elasticity of an axial compressor with splitter rotor was investigated by employing energy method and time-domain method. The aerodynamic modal damping ratio of blade and unsteady aerodynamic work distribution on the blade surface were obtained while the frequency domain analysis of blade vibration displacement were made; the conventionally designed rotors and the splitter rotor were also compared. The results show that the structural mistuning and aerodynamic mistuning had significant positive effects on the aero-elastic stability of the system. Aerodynamic mistuning improved the unsteady aerodynamic work distribution on the blade surface and the structural mistuning weakened the effect of interblade phase angles. For the first vibration mode, aerodynamic modal damping ratio (AMDR) of the splitter rotor has the value of 0.000791, and that of conventionally designed rotors have the value of 0.000217.Therefore,the structure of the splitter rotor not only has a better aerodynamic performance, but also enhanced the aero-elastic stability.

     

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