Volume 25 Issue 12
Dec.  2010
Turn off MathJax
Article Contents
KANG Yu-dong, SUN Bing. Effects of hot-gas wall nickelage and cooling channel inflow on regenerative cooling[J]. Journal of Aerospace Power, 2010, 25(12): 2834-2838.
Citation: KANG Yu-dong, SUN Bing. Effects of hot-gas wall nickelage and cooling channel inflow on regenerative cooling[J]. Journal of Aerospace Power, 2010, 25(12): 2834-2838.

Effects of hot-gas wall nickelage and cooling channel inflow on regenerative cooling

  • Received Date: 2009-11-02
  • Rev Recd Date: 2010-01-12
  • Publish Date: 2010-12-28
  • Three-dimensional numerical simulation was carried out for coupled flow and heat transfer of regenerative cooling channel and coolant in consideration of the cooling channel inflow and hot-gas wall nickelage.The empirical method was used to simulate hot-gas convective and radiative heat transfer;the coolant was methane,whose thermophysical properties varied with both temperature and pressure.The results show that,the secondary flow plus sudden expansion flow field at inflow could lead to increase of local pressure lose and affect the flow and heat transfer situation at a large downstream region;nickelage on hot-gas wall can improve its capacity to endure high temperature and reduce the copper-alloy temperature.

     

  • loading
  • [1]
    Pascal P,Thomas F,Hilda V.LOX/methane and LOX/kerosene high thrust engine trade-off .AIAA 2001-3542,2001.
    [2]
    Preclik D,Hagemann G,Knab O,et al.LOX/hydrocarbon propellant trade considerations for future reusable liquid booster engines .AIAA 2005-3567,2005.
    [3]
    Reuben S,Matthew M,Oleg S,et al.Integrated modeling and analysis for a LOX/methane expander cycle engine:focusing on regenerative cooling jacket design .AIAA 2006-4534,2006.
    [4]
    Marco P,Francesco N,Marcello O.Flow analysis of transcritical methane in rectangular cooling channels .AIAA 2008-4556,2008.
    [5]
    Marco P,Francesco N,Marcello O.Investigation of transcritical methane flow and heat transfer in curved cooling channels .AIAA 2009-5304,2009.
    [6]
    Immich H,Mayer W.Cryogenic liquid rocket engine technology developments within the german national technology programme .AIAA 97-2822,1997.
    [7]
    Immich H,Kretschmer J,Preclik D.Technology developments for cryogenic rocket engines .AIAA 2000-3780,2000.
    [8]
    Immich H,Kretschmer J,Preclik D.Thrust chamber technology developments for future launch vehicle liquid rocket engines .AIAA 2001-3544,2001.
    [9]
    陶文铨.数值传热学(第二版)[M].西安:西安交通大学出版社,2001.
    [10]
    LUO Jiang,Lakshminarayana B.Prediction of strongly curved turbulent duct flows with Reynolds stress model[J].AIAA Journal,1997,35(1):91-98.
    [11]
    康玉东,孙冰,高翔宇.液体火箭发动机推力室冷却通道温度分层数值研究[J].航空动力学报,2009,24(8):1904-1910. KANG Yudong,SUN Bing,GAO Xiangyu.Numerical investigations of thermal stratification in cooling channel of liquid rocket engine thrust chamber[J].Journal of Aerospace Power,2009,24(8):1904-1910.(in Chinese)
    [12]
    Lebail F,Popp M.Numerical analysis of high aspect ratio cooling passage flow and heat transfer .AIAA 93-1829,1993.
  • 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 (2146) PDF downloads(392) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return