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两种雾化模型在横向流雾化数值模拟中的应用

刘静 徐旭

刘静, 徐旭. 两种雾化模型在横向流雾化数值模拟中的应用[J]. 航空动力学报, 2013, 28(7): 1441-1448.
引用本文: 刘静, 徐旭. 两种雾化模型在横向流雾化数值模拟中的应用[J]. 航空动力学报, 2013, 28(7): 1441-1448.
LIU Jing, XU Xu. Application on numerical simulation of atomization of liquid jet in crossflow using two atomization models[J]. Journal of Aerospace Power, 2013, 28(7): 1441-1448.
Citation: LIU Jing, XU Xu. Application on numerical simulation of atomization of liquid jet in crossflow using two atomization models[J]. Journal of Aerospace Power, 2013, 28(7): 1441-1448.

两种雾化模型在横向流雾化数值模拟中的应用

Application on numerical simulation of atomization of liquid jet in crossflow using two atomization models

  • 摘要: 通过对横向气流中燃料雾化的数值模拟,分析了两种常用的雾化模型TAB(Taylor analogy breakup)模型和Reitz波不稳定性模型中的经验参数变化对模拟结果的影响,为合理使用这两种雾化模型提供了参考.对雾化过程的模拟结果与实验结果的对比分析发现:虽然TAB和Reitz波模型都能对穿透深度进行很好的预估,但从液滴分布、SMD(Sauter mean diameter)和液滴速度等具体参数的计算结果来看,TAB模型的计算结果优于Reitz波模型,更适用于相关计算,并给出了适当的TAB模型的经验参数取值.最后,用TAB模型在相同经验参数下对不同燃料喷射速度的工况进行了计算,得到了满意的结果.这种先用实验数据校准经验参数,然后用校准后的经验参数计算相关未知结果工况的方法可以应用在今后的预估计算和研究中.

     

  • [1] May Y L,Vincent G M,Scott S G.Mixing of an airblast-atomizaed fuel spray injected into a crossflow of air [R].NASA/CR-2000-210467,2000.
    [2] Chen T H,Smith C R,Schommer D G.Multi-zone behavior of transverse liquid jet in high-speed flow [R].AIAA 93-0453,1993.
    [3] Stenzler J N,Lee J G,Santavicca D A.Penetration of liquid jets in a crossflow [R].AIAA-2003-1327,2003.
    [4] Wu P K,Kirkendall K A,Fuller R P,et al.Spray structures of liquid jets atomized in subsonic crossflows[J].Journal of Propulsion and Power,1998,14(2):173-182.
    [5] 徐胜利,岳朋涛,孙英英,等,超声速气流中雾化燃料喷射的三维数值研究[J].应用力学学报,2000,17(2):19-23. XU Shengli,YUE Pengtao,SUN Yingying,et al,Three dimensional numerical simulation of atomized fuels injected into a supersonic flow[J].Chinese Journal of Applied Mechanics,2000,17(2):19-23.(in Chinese)
    [6] 刘静.超声速气流中横向燃油喷雾的数值模拟和实验研究[D].北京:北京航空航天大学,2010. LIU jing. Numerical and experimental investigation of fuel spray in supersonic cross flow [D].Beijing:Beijing University of Aeronautics and Astronautics, 2010.(in Chinese)
    [7] 庄逢辰.液体火箭发动机喷雾燃烧的理论、模型及应用[M].北京:国防科技大学出版社,1995.
    [8] Amsden A A,O'Rourke P J,Butler T D.KIVA-Ⅱ:a computer program for chemically reactive flows with sprays [R].Los Alamos:Los Alamos National Laboratory,1989.
    [9] Reitz R D,Diwakar R.Structure of high-pressure fuel sprays [R].SAE870598,1987.
    [10] Hsiang L P,Feath G M.Near-limit drop deformation and second breakup[J].International Journal of Multiphase Flow,1992,18(5):635-652.
    [11] Anavaradham T K G,Shreenivasan O J,Sujith R I,et al.Investigation of transverse liquid injection in confined supersonic flow over cavities.AIAA-2004-4075,2004.
    [12] Miller B,Sallam K A,Bingabr M,et al.Breakup of aerated liquid jets in subsonic crossflow[J].Journal of Propulsion and Power,2008,24(2):253-258.
    [13] Osta A,Sallam K A.Effect of nozzle length/diameter ratio on the breakup of liquid jets in crossflow [R].AIAA-2008-1014,2008.
    [14] Sallam K A,Aalburg C,Faeth G M.Breakup of round nonturbulent liquid jets in gaseous crossflow[J].AIAA Journal,2004,42(12):2529-2540.
    [15] Tambe S B,Jeng S M.Liquid jets in subsonic crossflow [R].AIAA-2005-731,2005.
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出版历程
  • 收稿日期:  2012-07-02
  • 刊出日期:  2013-07-28

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