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小涵道比涡扇发动机动态特性数值计算

田金虎 乔渭阳 彭生红

田金虎, 乔渭阳, 彭生红. 小涵道比涡扇发动机动态特性数值计算[J]. 航空动力学报, 2013, 28(9): 1988-1996.
引用本文: 田金虎, 乔渭阳, 彭生红. 小涵道比涡扇发动机动态特性数值计算[J]. 航空动力学报, 2013, 28(9): 1988-1996.
TIAN Jin-hu, QIAO Wei-yang, PENG Sheng-hong. Numerical calculation of dynamic performance of low-bypass ratio turbofan engine[J]. Journal of Aerospace Power, 2013, 28(9): 1988-1996.
Citation: TIAN Jin-hu, QIAO Wei-yang, PENG Sheng-hong. Numerical calculation of dynamic performance of low-bypass ratio turbofan engine[J]. Journal of Aerospace Power, 2013, 28(9): 1988-1996.

小涵道比涡扇发动机动态特性数值计算

Numerical calculation of dynamic performance of low-bypass ratio turbofan engine

  • 摘要: 研究了涡扇发动机动态数学模型以及数值模拟方法,对于进口条件变化、发动机加速、发动机减速、发动机加力等情况下动态工作过程,改进的发动机动态性能数值模拟程序具备了数值仿真的能力,并对小涵道比涡扇发动机动态特性进行了数值计算分析,结果表明:对于飞行条件快速变化的情况,当发动机推力增大到一定程度后,会有逐渐减小的趋势,而缓慢变化时,就没有这种振荡现象;对于燃油质量流量增大、减小情况,变化的快慢对应耗油率的峰值是不同的;同样,随着加力温升的变化速度不同,发动机推力和耗油率达到的峰值也不同.

     

  • [1] Meilunas R.Overview of the simulation[R].AIAA-2007-6572,2007.
    [2] Findlay D.Collaborative simulation and testing utilizing high performance computing[R].AIAA-2007-6570,2007.
    [3] Wellborn S R,Reichert B A,Okiishi T H.An experimental investigation of the flow in a diffusing S-duct[R].AIAA 92-3622,1992.
    [4] Jin W,Tahavi R.A computational study of icing effects on performance of S-duct inlets[R].AIAA-2008-4584,2008.
    [5] Milt W,Hale A A,Vining C.Application of numerical analysis tools for airframe-propulsion integrated test and evaluation[R].ASME Paper 2008-GT-50194,2008.
    [6] Emmons H W,Pearson C E,Grant H P.Compressor surge and stall propagation[J].Transactions of the ASME,1955,77(3):455-469.
    [7] Hah C H,Rabe D C,Sullivan T J,et al.Effects of inlet distortion on the flow field in a transonic compressor rotor[R].ASME Paper 96-GT-547,1996.
    [8] Camp T R,Day I J.A study of spike and modal stall phenomena in a low-speed axial compressor[J].Journal of Turbomachinery,1998,120(7):393-401.
    [9] Batterton P G,Gold H.Experimental test results of a generalized-parameter fuel control[R].NASA TN D-7198,1973.
    [10] Calogeras J E.Experimental investigation of dynamic distortion in a Mach 2.50 inlet with 60 percent internal contraction and its effect on turbojet stall margin[R].NASA TM X-1842,1969.
    [11] Choby D A,Burstadt P L,Calogeras G E.Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60 percent internal-area contraction[R].NASA TM X-2192,1971.
    [12] Davis M W Jr.Parametric investigation into the combined effects of pressure and temperature distortion on compression system stability[R].AIAA 91-1895,1991.
    [13] Batterton P G,Gold H.Experimental test results of a generalized-parameter fuel control[R].NASA TN D-7198,1973.
    [14] Costakis W G,Wenzel L M.An experimental investigation of compressor stall using an on-line distortion indicator and signal conditioner[R].NASA TM X-3 182,1975.
    [15] Jr Davis M W,Owen A K,Daniele W F.Joint dynamic air breathing propulsion simulations partnership JDAPS[R].ASME Paper 95-GT-143,1995.
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出版历程
  • 收稿日期:  2012-09-18
  • 刊出日期:  2013-09-28

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