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不同孔型对高超声速逆喷流气膜冷却影响

商圣飞 向树红 姜利祥

商圣飞, 向树红, 姜利祥. 不同孔型对高超声速逆喷流气膜冷却影响[J]. 航空动力学报, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006
引用本文: 商圣飞, 向树红, 姜利祥. 不同孔型对高超声速逆喷流气膜冷却影响[J]. 航空动力学报, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006
SHANG Shengfei, XIANG Shuhong, JIANG Lixiang. Effect of different hole shapes on hypersonic counter-jet film cooling[J]. Journal of Aerospace Power, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006
Citation: SHANG Shengfei, XIANG Shuhong, JIANG Lixiang. Effect of different hole shapes on hypersonic counter-jet film cooling[J]. Journal of Aerospace Power, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006

不同孔型对高超声速逆喷流气膜冷却影响

doi: 10.13224/j.cnki.jasp.2020.08.006

Effect of different hole shapes on hypersonic counter-jet film cooling

  • 摘要: 主要对不同孔型在不同质量流量下对高超声速逆喷流气膜冷却影响规律开展研究,得到不同孔型对气膜冷却效果的影响规律。采用CFD计算方法,对飞行高度为50 km,飞行马赫数为15条件下圆柱孔、收缩孔、扩张孔、收缩-扩张孔4种孔型开展研究。研究显示:小流量供气时,收缩孔和圆柱孔会出现长穿透模态(LPM)工作状态,扩张孔和收缩-扩张孔则不会出现;随着喷流流量的增大,喷流会从LPM转向短穿透模态(SPM),此时继续增大气膜喷流流量,并不会显著增大冷却收益。综合整个流域的变化,扩张孔在高超声速飞行器头部逆流喷流气膜冷却中是比较稳定可靠的气膜冷却孔。

     

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出版历程
  • 收稿日期:  2020-01-09
  • 刊出日期:  2020-08-28

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