Volume 27 Issue 9
Sep.  2012
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Article Navigation >  Journal of Aerospace Power  > 2012  >  27(9): 2099-2105
LIU Yong-quan, LIU Huo-xing, ZHENG Ning. Numerical simulation of an aero-engine fan with inlet distortion[J]. Journal of Aerospace Power, 2012, 27(9): 2099-2105.
Citation: LIU Yong-quan, LIU Huo-xing, ZHENG Ning. Numerical simulation of an aero-engine fan with inlet distortion[J]. Journal of Aerospace Power, 2012, 27(9): 2099-2105.
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Numerical simulation of an aero-engine fan with inlet distortion

  • 1.

    Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

  • 2.

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

  • Received Date: 2012-05-12
  • Publish Date: 2012-09-28
    Abstract
  • The method of replacing the blade row forces with distributed bulk body force source terms was developed to simulate fan flow field with inlet distortion.The fan with clean inlet and inlet steady total pressure distortion in an aeroengine were simulated respectively.It demonstrates that the results of fan with clean inlet agree well with the solutions of RANS(Reynolds-averaged Navier-Stokes).In the case with inlet distortion,this code can obtain the propagation of inlet distortion correctly.The unsteady simulation shows that large-scale strong reaction and three-dimentional transportation were main property of flow field with inlet distortion. The attraction of the distributed bulk body force model is obvious in that it can be relatively independent of the empiricism while at the same time demands much less computer resources.

     

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