Volume 27 Issue 11
Nov.  2012
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LIU Yong-quan, SHI Lei, LIANG Cai-yun. Aerodynamic stability design method for certain aero-engine in whole engine's flight operating envelope[J]. Journal of Aerospace Power, 2012, 27(11): 2462-2467.
Citation: LIU Yong-quan, SHI Lei, LIANG Cai-yun. Aerodynamic stability design method for certain aero-engine in whole engine's flight operating envelope[J]. Journal of Aerospace Power, 2012, 27(11): 2462-2467.

Aerodynamic stability design method for certain aero-engine in whole engine's flight operating envelope

  • Received Date: 2012-07-23
  • Publish Date: 2012-11-28
  • According to the basic theory of aerodynamic stability and engineering experience,an aero-engine,for example,aerodynamic stability design method in the whole flight envelope was presented on the basis of GJB/Z 224-2005,and some experimental verification were performed.The results show that stability margin required of fan and compressor is larger at high-altitude and low-speed state,stability margin required of fan is larger at right boundary of the engine envelope and basically remains the same,affected by the nozzle subcritical,stability margin required of fan is larger during landing.Therefore,these conditions should be focused in the engine design and use.Engine should be designed to ensure that the stability margin available of fan and compressor is greater than the stability margin required.The design method can effectively meet the demand for complex engineering development.

     

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