Volume 28 Issue 6
Jun.  2013
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JIA Zhen. Flame-holding mechanism of cavity structure in super-sonic combustor[J]. Journal of Aerospace Power, 2013, 28(6): 1392-1401.
Citation: JIA Zhen. Flame-holding mechanism of cavity structure in super-sonic combustor[J]. Journal of Aerospace Power, 2013, 28(6): 1392-1401.

Flame-holding mechanism of cavity structure in super-sonic combustor

  • Received Date: 2012-10-18
  • Publish Date: 2013-06-28
  • The influences of length to depth ratio of cavity as well as its depth on the mixing effect of fuel and air and the combustion efficiency in supersonic flow field with/without reactions were numerically investigated. It is found that although increasing length to depth ratio could bring about fuel entrainment into cavity, delay the mixing time in low speed high-temperature recirculation zone and enhance the mixing and combustion efficiency. Yet, excessive length to depth ratio no longer improves combustion, but enhances the attached shock, increasing total pressure loss and drag between front and back walls. Increasing depth of cavity produces more loss of available energy induced by shock wave, but increases mass exchange rate between mainstream and cavity, enlarging cavity volume remarkably and increasing combustion efficiency.

     

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  • [1]
    Vinagradov V,Grachev V,Petrov M.Experimental investigation of 2-D dual mode scramjet with hydrogen fuel at Mach 4-6.AIAA 90-5269,1990.
    [2]
    司徒明.煤油超燃冲压发动机性能分析[J].推进技术,1998,19(2):18-22 SITU Ming.Performance analysis of hydrocarbon-fueled scramjet[J].Journal of Propulsion Technology,1998,19(2):18-22.(in Chinese)
    [3]
    Niioka T,Terada K,Kobayashi H,et al.Flame stabilization characteristics of strut divided into two parts in supersonic airflow[J].Journal of Propulsion and Power,1995,11(1):112-116.
    [4]
    Brandstetter A,Denis S R,Kau H P.Flame stabilization in supersonic combustion[J].AIAA-2002-5224,2002.
    [5]
    Rogers R C, Capriotti D P,Guy R W.Experimental supersonic combustion research at NASA Langley[R].AIAA 98-2506,1998.
    [6]
    Abdel-Salam T M,Tiwari S N,Mohieldin T O.Effects of ramp swept angle in supersonic mixing[R].AIAA-2000-2377,2000.
    [7]
    Roudakov A S,Schikhmann Y,Semenov V,et al.Flight testing of an axisymmetric scramjet-Russian recent advances[R].International Astronautical Federation,IAF Paper 93-S4.458,1993.
    [8]
    Rodriguez C G.CFD analysis of the CIAM/NASA scramjet[R].AIAA-2002-4128,2002.
    [9]
    Owens M G,Tehranian S,Segal C,et al.Flame-holding configurations for kerosene combustion in a Mach 1.8 airflow[J].Journal of Propulsion and Power,1998,14(4):456-461
    [10]
    Gruber M R,Baurle R A,Mathur T,et al.Fundamental studies of cavity-based flameholder concepts for supersonic combustor[R].AIAA 99-2248.1999.
    [11]
    Baurle R A,Tam C J,Dasgupta.S.Analysis of unsteady cavity flows for scramjet applications[R].AIAA-2000-3617,2000.
    [12]
    Gruber M R.Fundamental investigation of an integrated fuel injector/flameholder concept for supersonic combustion[R].AFRL-PR-WP-TR,1998-2111,1998.
    [13]
    Gruber M R,Baurle R A,Mathur T,et al.Fundamental studies of cavity-based flameholder concept for supersonic combustors[J].Journal of Propulsion and Power,2001,17(1):146-153.
    [14]
    王春,司徒明,马继华,等.高温富油燃气超声速燃烧数值模拟[J].推进技术,2000,21(2):60-63. WANG Chun,SITU Ming,MA Jihua,et al.Numerical simulation on supersonic combustion of fuel-rich hot gas[J].Journal of Propulsion Technology,2000,21(2):60-63.(in Chinese)
    [15]
    Settles G S,Willians D R,Baca B K,et al.Reattachment of a compressible turbulent free shear layer[J].AIAA Journal,1982,20(1):60-67.
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