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发散冷却最小冷却介质注射量的数值研究

时骏祥 王建华

时骏祥, 王建华. 发散冷却最小冷却介质注射量的数值研究[J]. 航空动力学报, 2007, 22(2): 222-227.
引用本文: 时骏祥, 王建华. 发散冷却最小冷却介质注射量的数值研究[J]. 航空动力学报, 2007, 22(2): 222-227.
SHI Jun-xiang, WANG Jian-hua. A numerical investigation of the minimum coolant injection rate for transpiration cooling[J]. Journal of Aerospace Power, 2007, 22(2): 222-227.
Citation: SHI Jun-xiang, WANG Jian-hua. A numerical investigation of the minimum coolant injection rate for transpiration cooling[J]. Journal of Aerospace Power, 2007, 22(2): 222-227.

发散冷却最小冷却介质注射量的数值研究

基金项目: 国家自然科学基金重大研究计划资助(90305006);安徽省教育厅自然科学基金重点项目资助(2004kj365zd);国家教委留学人员回国基金资助

A numerical investigation of the minimum coolant injection rate for transpiration cooling

  • 摘要: 充分发挥材料本身的抗高温能力, 以最小的冷却介质注射量, 确保推进器不被烧蚀是发散冷却系统的设计目标.本文用一维可压缩、非稳态、局部非热平衡模型, 数值研究了瞬态冷却过程及最小冷却介质注射量的依赖参数.数值研究表明:研究瞬态的冷却过程十分重要, 因为尽管当冷却过程达到稳态以后热端温度在烧蚀点以下, 但在进入稳态之前可能已经发生烧蚀;多孔介质骨架材料的初始温度越高、特征尺寸越大, 冷却介质需要量越大;在仅考虑冷却效果的前提下, 孔隙率越大, 冷却介质需要量越大;相反, 骨架材料导热系数越高, 冷却介质需要量越小.

     

  • [1] Choi S H,Scotti S J,Song K D,et al.Transpiration cooling of a scram jet engine combustion chamber[R].The 32th AIAA Thermo-physics Conference,Atlanta,Georgia,1997,AIAA 97-2576.
    [2] Glass D E,Dilley A D.Numerical analysis of convection/transpiration cooling[R].NASA/TM-1999-209828.
    [3] Landis J A,Bowman J W.Numerical study of a transpiration cooled rocket nozzle[R].AIAA Meeting 1996 Paper 96-2580.
    [4] Lacy B P,Varghese P L,Wilson D E.Unsteady effects of dissociative cooling under high-stagnation-point heat loads[J].Journal of Spacecraft and Rockets,1998,35(5):633-638.
    [5] Lacy B P,Wilson D E,Varghese P L.Dissociative cooling effect on stagnation heat transfer of gas mixture injection[J].Journal of Spacecraft and Rockets,1995,32(5):777-782.
    [6] Wang J H,Han X S.Numerical investigation of transpiration and ablation cooling[J].Journal of Heat and Mass Transfer,2007,43(1):275-284.
    [7] Greuel D,Herbertz A,Haidn O J,et al.Transpiration cooling applied to C/C liners of cryogenic liquid rocket engines[R].AIAA /ASME /SEA/ASEE/JPC Conference and Exhibit,11-14 July 2004,Fort Lauderdale,Florida 2004-3682.
    [8] Amiri A,Vafai K.Analysis of dispersion effects and non-thermal equilibrium non-darcian variable porosity,incompressible flow through porous media[J].Int.Journal of Heat Mass Transfer,1994,37:939-954.
    [9] Amiri A,Vafai K.Transient analysis of incompressible flow through a packed bed[J].Int.Journal of Heat Mass Transfer,1998,41:4259-4279.
    [10] Von Wolfersdorfvon J.Effect of coolant side heat transfer on transpiration cooling[J].Journal of Heat and Mass Transfer,2005,41:327-337.
    [11] 王海南,王建华.一维、稳态、非热平衡发汗冷却的解析解研究[J].航空动力学报,2006,21(1):77-82.WANG Hainan,WANG Jianhua.An investigation of analytical solution for one-dimensional,steady,non-equilibrium transpiration cooling[J].Journal of AerospacePower,2006,21(1):77-82.
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出版历程
  • 收稿日期:  2006-02-16
  • 修回日期:  2006-05-07
  • 刊出日期:  2007-02-28

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