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爆震燃气轮机的变比热容热力循环性能

李晓丰 肖俊峰 王玮 王峰 危师让 郑龙席

李晓丰, 肖俊峰, 王玮, 王峰, 危师让, 郑龙席. 爆震燃气轮机的变比热容热力循环性能[J]. 航空动力学报, 2016, 31(2): 369-376. doi: 10.13224/j.cnki.jasp.2016.02.015
引用本文: 李晓丰, 肖俊峰, 王玮, 王峰, 危师让, 郑龙席. 爆震燃气轮机的变比热容热力循环性能[J]. 航空动力学报, 2016, 31(2): 369-376. doi: 10.13224/j.cnki.jasp.2016.02.015
LI Xiao-feng, XIAO Jun-feng, WANG Wei, WANG Feng, WEI Shi-rang, ZHENG Long-xi. Thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity[J]. Journal of Aerospace Power, 2016, 31(2): 369-376. doi: 10.13224/j.cnki.jasp.2016.02.015
Citation: LI Xiao-feng, XIAO Jun-feng, WANG Wei, WANG Feng, WEI Shi-rang, ZHENG Long-xi. Thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity[J]. Journal of Aerospace Power, 2016, 31(2): 369-376. doi: 10.13224/j.cnki.jasp.2016.02.015

爆震燃气轮机的变比热容热力循环性能

doi: 10.13224/j.cnki.jasp.2016.02.015
基金项目: 

华能集团总部科技项目(HNKJ14-H05)

详细信息
    作者简介:

    李晓丰(1985-),男,湖南邵阳人,工程师,博士,主要从事燃气轮机燃烧、总体性能分析以及转子动力学研究.

  • 中图分类号: V231.2

Thermodynamic cycle performance of detonation gas turbine with variable specific heat capacity

  • 摘要: 为分析变比热容下爆震燃气轮机的热力循环性能,建立了考虑比热容随工质成分及温度变化的爆震燃气轮机热力循环模型,分析中同时考虑了压气机、燃烧室、透平等部件的效率.在不同比较条件下,利用变比热容法对比分析研究了燃气轮机爆震循环(DCGT)、Brayton循环和Humphrey循环燃气轮机的热力循环性能.计算结果表明:与Brayton循环相比,DCGT具有较大性能优势;在透平前温度为1620K且压比为16.5时,DCGT热效率较Brayton循环高28.8%;在无量纲吸热量为4.25且压比为16.5时,DCGT热效率则较Brayton循环高30.7%.

     

  • [1] 严传俊,范玮,黄希桥.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005.
    [2] William H H,David T P.Thermodynamic cycle analysis of pulse detonation engines[J].Journal of Propulsion and Power,2002,18(1):68-76.
    [3] WU Yuhui,MA Fuhua,Yang V.System performance and thermodynamic cycle analysis of air breathing pulse detonation engines[J].Journal of Propulsion and Power,2003,19(4):556-567.
    [4] Vutthivithayarak R,Braun E M,Lu F K.On thermodynamic cycles for detonation engines[R].Manchester,UK:28th International Symposium on Shock Waves,2012.
    [5] Nordeen C A.Thermodynamics of a rotating detonation engine[D].Connecticut,US:University of Connecticut,2013.
    [6] 邱华,严传俊,范玮.部分充填下脉冲爆震发动机的热力循环性能分析[J].航空动力学报,2008,23(4):718-723. QIU Hua,YAN Chuanjun,FAN Wei.Analysis on thermodynamic performance of partially-fueled pulse detonation engine[J].Journal of Aerospace Power,2008,23(4):718-723.(in Chinese)
    [7] 邱华,严传俊,熊姹.带喷管脉冲爆震发动机单循环性能分析模型[J].航空动力学报,2005,20(5):818-821. QIU Hua,YAN Chuanjun,XIONG Cha.A single-cycle performance model of the pulse detonation engine with nozzle[J].Journal of Aerospace Power,2005,20(5):818-821.(in Chinese)
    [8] 张强,何立明,陈鑫,等.两级脉冲爆震发动机的理想热力循环及性能分析[J].推进技术,2012,33(4):499-504. ZHANG Qiang,HE Liming,CHEN Xin,et al.Ideal thermodynamic cycle and performance analysis of 2-stage pulse detonation engine[J].Journal of Propulsion Technology,2012,33(4):499-504.(in Chinese)
    [9] 陈鑫,于锦禄,何立明,等.脉冲爆震发动机热力循环性能分析[J].空军工程大学学报,2011,12(2):1-5. CHEN Xin,YU Jinlu,HE Liming,et al.The analysis of pulse detonation engine thermodynamic cycle performance[J].Journal of Air Force Engineering University,2011,12(2):1-5.(in Chinese)
    [10] 范孝华,林志勇,周进.脉冲爆震和斜爆震发动机热力循环过程分析[C]//第十四届全国激波与激波管学术会议论文集.北京:中国力学学会,2010:260-266.
    [11] 李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验[J].航空动力学报,2013,28(12):2731-2736. LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Principle experiments on two phase pulse detonation turbine engine[J].Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
    [12] LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Experimental investigations on the power extraction of a turbine driven by a pulse detonation combustor[J].Chinese Journal of Aeronautics,2013,26(6):1353-1359.
    [13] 李晓丰.脉冲爆震涡轮发动机技术研究[D].西安:西北工业大学,2013. LI Xiaofeng.The technology research on the pulse detonation turbine engine[D].Xi'an:Northwestern Polytechnical University,2013.(in Chinese)
    [14] The Engineering ToolBox.Specific heat of oxygen gas-O2-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/oxygen-d_978.html.
    [15] The Engineering ToolBox.Specific heat of carbon dioxide gas-CO2-temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/carbon-dioxide-d_974.html.
    [16] The Engineering ToolBox.Specific heat of nitrogen gas-N2-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/nitrogen-d_977.html.
    [17] The Engineering ToolBox.Specific heat of water vapor-H2O-at temperatures ranging 175-6000K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/water-vapor-d_979.html.
    [18] The Engineering Toolbox.Specific heat of methane gas-CH4-at temperatures ranging 200-1100K[EB/OL].[2014-12-10].http://www.engineeringtoolbox.com/methane-d_980.html.
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出版历程
  • 收稿日期:  2015-01-19
  • 刊出日期:  2016-02-28

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