Volume 28 Issue 2
Feb.  2013
Turn off MathJax
Article Contents
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.

Performance of simple/recuperation cycle gas turbines under variable conditions

  • Received Date: 2012-03-13
  • Publish Date: 2013-02-28
  • Off-design performance of simple and recuperation cycles was studied with calculation,analysis and comparison by means of gas turbine modelling technique and the models were solved by Newton-Raphson method.Main conclusions are as follows.Under the same operating parameters,the simple cycle gas turbine can provide more power output than the recuperation cycle one,while the latter is more efficient than the former.The efficiency of the recuperation cycle decreases faster than the counterpart as the turbine inlet temperatures decrease.For both cycles,the power outputs and efficiencies of gas turbines increase,but the compressor surge margins decrease with the drop of ambient temperature.The power outputs,efficiencies and compressor surge margins of gas turbines increase with the rise of ambient pressure.The above conclusions can provide good references for the off-design operation of aero-engine derived land-borne turbine generators.

     

  • loading
  • [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.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (2160) PDF downloads(1232) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return