Volume 22 Issue 3
Mar.  2007
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LI Shao-bin, SU Jie-xian, FENG Guo-tai, WANG Zhong-qi. Effect of blade bowing and local modification on high-turning angle compressor stator performance[J]. Journal of Aerospace Power, 2007, 22(3): 465-470.
Citation: LI Shao-bin, SU Jie-xian, FENG Guo-tai, WANG Zhong-qi. Effect of blade bowing and local modification on high-turning angle compressor stator performance[J]. Journal of Aerospace Power, 2007, 22(3): 465-470.
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Effect of blade bowing and local modification on high-turning angle compressor stator performance

  • School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

  • Received Date: 2006-03-09
  • Rev Recd Date: 2006-05-22
  • Publish Date: 2007-03-28
    Abstract
  • This paper presents a numerical study of a high-turning angle compressor stator with 51°.The main ideas and local modification to achieve better control of boundary layer flow in aircraft are applied to the contouring of bowed stator.The skin friction line of suction side and total pressure loss are discussed in the straight blade,bowed blade and local modified bowed blade.The results show that the local modified bowed blade can effectively control the boundary layer flow and it is applicable to the boundary conditions of high adverse pressure gradient,high-turning and high subsonic inlet velocity.

     

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    • References(9)
  • [1]
    Bryce J D,Cherrett M A,Lyes P A.Three-dimensional flow in a highly loaded single-stage transonic fan[J].ASME Journal of Turbomachinery,1995,117:22-28.
    [2]
    Emmerson P R.Three-dimensional flow calculations of the stator in a highly loaded transonic fan[R].ASME Paper 96-GT-546,Birmingham,1996.
    [3]
    Calvert W J,Emmerson P R,Moore J M.Design,test and analysis of a high-Pressure-ratio transonic Fan[R].ASME Paper GT2003-38302,Atlanta,2003.
    [4]
    Friedrichs J,Baumgarten S,Kosyna G,et al.Effect of stator design on stator boundary layer flow in a highly loaded single-stage axial-flow low-speed compressor[R].ASME Paper 2000-GT-616,Munich,2000.
    [5]
    Boese M,Fottner L.Effects of riblets on the loss behavior of a highly loaded comperssor cascade[R].ASME Paper GT-2002-30438,Amsterdam,2002.
    [6]
    Douglas J W,Li S M,Song B,et al.Effects of freestream turbulence on the losses of a highly loaded comperssor stator blade[R].ASME Paper GT2003-38604,Atlanta,2003.
    [7]
    Hilgenfeld L,Pfitzner M.Unsteady boundary layer development due to wake passing effects on a highly loaded linear comperssor cascade[R].ASME Paper GT2004-53186,Vienna,2004.
    [8]
    刘宝杰,邹正平,严明,等.叶轮机计算流体动力学技术现状与发展趋势[J].航空学报,2002,23(5):394-404.LIU Baojie,ZOU Zhengping,YAN Ming,et al.Present status and future development of CFD in turbomachinery[J].Acta Aeronautic et Astronatica Sinica,2002,23(5):394-404.
    [9]
    夏雪湔,邓学蓥.工程分离流动力学[M].北京:北京航空航天大学出版社,1991:242-254.
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