Volume 22 Issue 9
Sep.  2007
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Article Navigation >  Journal of Aerospace Power  > 2007  >  22(9): 1401-1404
SONG Shuang-wen, JIANG Rong-wei, CHEN Jian, LIANG De-wang. Performance experiment of a reflection flow annular combustor with slinger[J]. Journal of Aerospace Power, 2007, 22(9): 1401-1404.
Citation: SONG Shuang-wen, JIANG Rong-wei, CHEN Jian, LIANG De-wang. Performance experiment of a reflection flow annular combustor with slinger[J]. Journal of Aerospace Power, 2007, 22(9): 1401-1404.
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Performance experiment of a reflection flow annular combustor with slinger

  • 1.

    College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • 2.

    China Aviation Powerplant Research Institute, Zhuzhou 412002, China

  • Received Date: 2007-03-26
  • Rev Recd Date: 2007-06-22
  • Publish Date: 2007-09-28
    Abstract
  • An experimental study on performance of a slinger annular combustor was performed at various slinger rotary speeds.The experimental results show that it has a higher total pressure recovery coefficient and a narrow lean blowoff limit.The outlet temperature distribution factor is less than 0.3,and combustion efficiency is above 0.99.The experimental results provide technical support for this kinds of combustor design and development.

     

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    • References(4)
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    Lefebvre A H.Gas turbine combustion[M].Washington:Hemisphere Publishing Corp,1983.
    [2]
    Mellor A M.Design of modern turbine combustors[M].New York,NY:Academic Press Inc,1990.
    [3]
    Maskey H C,Marsh F X.The annular combustion chamber with centrifugal fuel injection[R].SAE-444C,1962.
    [4]
    Rogo C,Trauth R L.Design of high heat release slinger combustor with rapid acceleration requirement[R].SAE-740167,1974.
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