Volume 33 Issue 5
May  2018
Turn off MathJax
Article Contents
Experiment on flow and heat transfer of aviation kerosene with time variation of inlet mass flow rate[J]. Journal of Aerospace Power, 2018, 33(5): 1186-1192. doi: 10.13224/j.cnki.jasp.2018.05.021
Citation: Experiment on flow and heat transfer of aviation kerosene with time variation of inlet mass flow rate[J]. Journal of Aerospace Power, 2018, 33(5): 1186-1192. doi: 10.13224/j.cnki.jasp.2018.05.021

Experiment on flow and heat transfer of aviation kerosene with time variation of inlet mass flow rate

doi: 10.13224/j.cnki.jasp.2018.05.021
  • Received Date: 2016-11-09
  • Publish Date: 2018-05-28
  • Characteristics of turbulent flow and heat transfer of compressed liquid kerosene were studied experimentally with sudden changes of the inlet mass flow rate. Flow and heat transfer experiments were conducted at a fuel temperature range of 300-650K, a Reynolds number range of 3000-60000 and a supercritical pressure of 3MPa. The fuel temperature, pressure and mass flow rate, and tube outside wall temperature were measured. Fuel skin friction coefficient and Nusselt number were calculated through unsteady control volume analysis based on momentum and energy conservations. The present results show that the time change of mass flow rate has very little effect on the skin friction coefficient and Nusselt number for compressed liquid kerosene tube flow when the temperature of kerosene doesnt exceed critical value 650K.

     

  • loading
  • [1]
    SOBELl D R,SPADACCINI L J.Hydrocarbon fuel cooling technologies for advanced propulsion[J].Journal of Engineering for Gas Turbines and Power,1997,119(2):344-351.
    [2]
    HANG H,SPADACCINI L J,SOBEL D R.Fuel-cooled thermal management for advanced aero-engines[J].Journal of Engineering for Gas Turbines and Power,2004,126(2):284-293.
    [3]
    LINNE D L,MEYER M L.Evaluation of heat transfer and thermal stability of supercritical JP-7 fuel[R].AIAA 97-3041,1997.
    [4]
    SHIRALKAR B S,GRIFFITH P.Deterioration in heat transfer to fluids at supercritical pressure and high heat flux[J].Journal of Heat Transfer,1969,91(1):27-36.
    [5]
    张斌,张春本,邓宏武,等.超临界压力下碳氢燃料在竖直圆管内换热特性[J].航空动力学报,2012,27(3):595-603.ZHANG Bin,ZHANG Chunben,DENG Hongwu,et al.Heat transfer characteristics of hydrocarbon fuel at supercritical pressure in vertical circular tubes[J].Journal of Aerospace Power,2012,27(3):595-603.(in Chinese)
    [6]
    胡志宏,陈听宽,罗毓珊,等.高热流条件下超临界压力煤油流过小直径管的传热特性[J].化工学报,2002,53(2):134-138.HU Zhihong,CHEN Tingkuan,LUO Yushan,et al.Heat transfer to kerosene at supercritical pressure in small diameter tube with large heat flux[J].Journal of Chemical Industry and Engineering,2002,53(2):134-138.(in Chinese)
    [7]
    ZHONG Fengquan,FAN Xuejun,YU Gong,et al.Heat transfer of aviation kerosene at supercritical conditions[J].Journal of Thermophysics and Heat Transfer,2009,23(3):543-550.
    [8]
    ZHONG Fengquan,FAN Xuejun,YU Gong,et al.Thermal cracking and heat sink capacity of aviation kerosene under supercritical conditions[J].Journal of Thermophysics and Heat Transfer,2011,25(3):450-456.
    [9]
    DANG Guoxin,ZHONG Fengquan,ZHANG Yongjiang,et al.Numerical study of heat transfer deterioration of turbulent supercritical kerosene flow in heated circular tube[J].International Journal of Heat and Mass Transfer,2015,85():1003-1011.
    [10]
    李勋锋,仲峰泉,范学军,等.超临界压力下航空煤油水平圆管内对流换热特性数值研究[J].航空动力学报,2010,25(8):1690-1697.LI Xunfeng,ZHONG Fengquan,FAN Xuejun,et al.Numerical study of convective heat transfer characteristics of kerosene flowing in a horizontal pipe at supercritical pressure[J].Journal of Aerospace Power,2010,25(8):1690-1697.(in Chinese)
    [11]
    CHOI J Y,MA F,YANG V.Combustion oscillations in a scramjet engine combustor with transverse fuel injection[J].Proceedings of the Combustion Institute,2005,30(2):2851-2858.
    [12]
    KANDA T,MASUYA G,WAKAMATSU Y,et al.Parametric study of airframe integrated scramjet cooling requirement[J].Journal of propulsion and Power,1991,7(3):431-436.
    [13]
    WISHART D P,FORTIN T B,GUINAN D,et al.Design,fabrication and testing of an actively cooled scramjet propulsion system[R].AIAA-2003-0015,2003.
    [14]
    BERGHOLZ R F,HITCH B D.Thermal management systems for high Mach airbreathing propulsion[R].AIAA 92-0515,1992.
    [15]
    SIDER E N,TATE C E.Heat transfer and pressure drop of liquids in tubes[J].Industrial and Engineering Chemistry,1936,28(12):1429-1435.
    [16]
    GNIELINSKI V.New equations for heat mass transfer in turbulent pipe and channel flows[J].International Chemical Engineering,1976,16(2):359-368.
    [17]
    ALLEN R W,ECKERT E R G.Friction and heat transfer measurements to turbulent pipe flow of water (Pr=7 and 8) at uniform wall heat flux[J].Journal of Heat Transfer,1964,86(3):301-310.
    [18]
    ZHANG Ruoling,JIANG Jin,YANG Yang,et al.Researches on heat transfer correlations of hydrocarbon fuel under supercritical pressure[R].AIAA-2012-5957,2012.
  • 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 (1071) PDF downloads(626) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return