Volume 32 Issue 9
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Analysis of thermodynamic cycle for separated flow turbofan engine[J]. Journal of Aerospace Power, 2017, 32(9): 2187-2192. doi: 10.13224/j.cnki.jasp.2017.09.018
Citation: Analysis of thermodynamic cycle for separated flow turbofan engine[J]. Journal of Aerospace Power, 2017, 32(9): 2187-2192. doi: 10.13224/j.cnki.jasp.2017.09.018
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Analysis of thermodynamic cycle for separated flow turbofan engine

doi: 10.13224/j.cnki.jasp.2017.09.018
  • Received Date: 2016-01-19
  • Publish Date: 2017-09-28
    Abstract
  • The efficiency of separated flow turbofan engine was analyzed based on the definition of gas generator. It proved the existence criterion of the optimum fan pressure ratio and the equivalence of extreme value of the specific thrust, the total efficiency and the specific fuel consumption by theoretical deduction on the basis of the efficiency definitions. This criterion could be used to determine the optimum fan pressure ratio for separated flow turbofan engine in practical design progress. The parametric study results of two different highbypassratio separated flow turbofan engines demonstrated that when the ratio of bypass and primary exhaust velocity equaled to the product of fan and low pressure turbine efficiencies, the overall efficiency and specific thrust reached their maximums and specific fuel consumption reached its minimum, proving the validity of the criterion.

     

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    • References(15)
  • [1]
    MATTINGLY J D,HEISER W H,PRATT D T.Aircraft engine design［M］.2nd ed.Reston,VA:American Institute of Aeronautics and Astronautics,2002.
    [2]
    MATTINGLY J D.Elements of gas turbine propulsion［M］.Reston,VA:American Institute of Aeronautics and Astronautics,2005.
    [3]
    OATES G C.Aerothermodynamics of gas turbine and rocket propulsion［M］.3th ed.Reston,VA:American Institute of Aeronautics and Astronautics,1998.
    [4]
    WALSH P P,FLETCHER P.Gas turbine performance［M］.2nd ed.New Delhi,India:Wiley,2004.
    [5]
    廉小纯，吴虎.航空燃气轮机原理:下册［M］.北京：国防工业出版社，2001.
    [6]
    陈光.航空发动机结构设计分析［M］.北京：北京航空航天大学出版社，2006.
    [7]
    冯青，李世武，张丽.工程热力学［M］.西安：西北工业大学出版社，2006.
    [8]
    HINES R W,GAFFIN W O.Potential improvements in turbofan engine fuel economy［R］.AIAA 76-666,1976.
    [9]
    MYOSE R Y,YOUNG T,HERON I.Effect of fan pressure ratio and bypass ratio on business jet range performance［R］.AIAA2006-7706,2006.
    [10]
    ROTH B,MAVRIS D.Work availability perspective of turbofan engine performance［R］.AIAA2001-0391,2001.
    [11]
    HINES R W.Specific fuel consumption improvement in current transport engines［R］.AIAA78-930,1978.
    [12]
    DAVIS D Y,STEARNS E M.Energy efficient engine flight propulsion system final design and analysis［R］.NASA CR-168219,1985.
    [13]
    JOHNSTON R P,HIRSCHKRON R,KOCH C C,et al.Energy efficient engine preliminary design and integration studies［R］.NASA CR-135444,1978.
    [14]
    MILLHOUSE P T,KRAMER S C,KING P I,et al.Identifying optimal fan compressor pressure ratio for the mixedstream turbofan engine［J］.Journal of Propulsion and Power,2000,16(1):79-86.
    [15]
    GUHA A.Optimum fan pressure ratio for bypass engines with separate or mixed exhaust streams［J］.Journal of Propulsion and Power,2001,17(5):1117-1122.
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