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简单循环与回热循环燃气轮机变工况特性

左志涛 孙志刚 朱阳历 陈海生 谭春青

左志涛, 孙志刚, 朱阳历, 陈海生, 谭春青. 简单循环与回热循环燃气轮机变工况特性[J]. 航空动力学报, 2013, 28(2): 356-364.
引用本文: 左志涛, 孙志刚, 朱阳历, 陈海生, 谭春青. 简单循环与回热循环燃气轮机变工况特性[J]. 航空动力学报, 2013, 28(2): 356-364.
ZUO Zhi-tao, SUN Zhi-gang, ZHU Yang-li, CHEN Hai-sheng, TAN Chun-qing. Performance of simple/recuperation cycle gas turbines under variable conditions[J]. Journal of Aerospace Power, 2013, 28(2): 356-364.
Citation: ZUO Zhi-tao, SUN Zhi-gang, ZHU Yang-li, CHEN Hai-sheng, TAN Chun-qing. Performance of simple/recuperation cycle gas turbines under variable conditions[J]. Journal of Aerospace Power, 2013, 28(2): 356-364.

简单循环与回热循环燃气轮机变工况特性

基金项目: 国家高技术研究发展计划(2007AA050502);国家自然科学基金(50906079)

Performance of simple/recuperation cycle gas turbines under variable conditions

  • 摘要: 针对某简单循环燃气轮机和回热循环燃气轮机建立了性能计算数学模型,并以Newton-Raphson法进行求解,对各自的变工况性能进行计算、分析及对比.研究结果表明:在工作参数相同的情况下,简单循环燃气轮机做功能力强于回热循环燃气轮机,但是前者的效率远远低于后者;涡轮进口温度自设计点降低时,回热循环燃气轮机效率降低幅度更大.对于简单循环、回热循环燃气轮机,环境温度降低使燃气轮机的输出功率和效率增加,但压气机喘振裕度降低;环境压力升高有助于提高燃气轮机的做功能力,使经济性以及稳定性更好.这些研究结果可以为航机陆改燃气轮机的变工况运行提供有益的参考.

     

  • [1] Cohen H,Rogers G F C,Saravanamuttoo H I H.Gas turbine theory[M].4th ed.Great Britain:Longman Group Limited,1996.
    [2] Kulikov G G,Thompson H A.Dynamic modelling of gas turbines:identification,simulation,condition monitoring and optimal control[M].London:Springer,2004.
    [3] Sellers J F,Daniele C J.DYNGEN:a program for calculating steady-state and transient performance of turbojet and turbofan engines[R].NASA-TN-D-7901,1975.
    [4] Al-Hamdan Q Z,Ebaid M S Y.Modeling and simulation of a gas turbine engine for power generation[J].Journal of Engineering for Gas Turbines and Power,2006,128(2):302-311.
    [5] Seldner K,Mihaloew J R,Blaha R J.Generalized simulation technique for turbojet engine system analysis[R].NASA-TN-D-6610,1972.
    [6] Koenig R W,Fishbach L H.GENENG:a program for calculating design and off-design performance for turbojet and turbofan engines[R].NASA-TN-D-6552,1972.
    [7] Fishbach L H,Koenig R W.GENENG:Ⅰa program for calculating design and off-design performance of two-and three-spool turbofans with as many as three nozzles[R].NASA-TN-D-6553,1972.
    [8] Sanghi V,Lakshmanan B K,Sundararajan V.Survey of advancements in jet-engine thermodynamic simulation[J].Journal of Propulsion and Power,2000,16(5):797-807.
    [9] Kurzke J.Gas turbine cycle design methodology:a comparison of parameter variation with numerical optimization[J].Journal of Engineering for Gas Turbines and Power,1999,121(1):6-11.
    [10] Kurzke J.How to get component maps for aircraft gas turbine performance calculations[R].ASME Paper GT-1996-164,1996.
    [11] 范作民,傅巽权.热力过程计算与燃气性质表[M].北京:国防工业出版社,1987.
    [12] 廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005.
    [13] 聂加耶夫,费多洛夫.航空燃气涡轮发动机原理[M].姜树明,译.北京:国防工业出版社,1984.
    [14] 杨世铭,陶文铨.传热学[M].4版.北京:高等教育出版社,2006.
    [15] Carnahan B,Luther H A,Wilkes J O.Applied numerical methods[M].New York:Wiley,1969.
    [16] 沈炳正.燃气轮机装置[M].北京:机械工业出版社,1981.
    [17] National Oceanic and Amospheric Administration,National Aeronautics and Space Administration,United States Air Force.NOAA-S/T 76-1562 U.S.Standard atmosphere 1976[S].Washington DC:US Government Printing Office,1976:1-20.
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出版历程
  • 收稿日期:  2012-03-13
  • 刊出日期:  2013-02-28

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