宇航学报 ›› 2021, Vol. 42 ›› Issue (3): 324-332.doi: 10.3873/j.issn.1000-1328.2021.03.007

• 飞行器设计与力学 • 上一篇    下一篇

激波干扰对发汗冷却影响的数值模拟研究

张红军,康宏琳   

  1. 北京空天技术研究所,北京 100074
  • 收稿日期:2020-02-26 修回日期:2020-06-22 出版日期:2021-03-15 发布日期:2021-03-15
  • 基金资助:
    国家自然科学基金(11802296);装备预研领域基金(61402060301

Numerical Simulation Study on the Effects of Shock Wave Interference on Transpiration Cooling

ZHANG Hong jun, KANG Hong lin   

  1. Beijing Aerospace Technology Institute, Beijing 100074, China
  • Received:2020-02-26 Revised:2020-06-22 Online:2021-03-15 Published:2021-03-15

摘要: 基于宏观表征体元(REV)的数值模拟方法开展了激波干扰对异质发汗冷却影响的数值模拟研究,获得了外部激波干扰与引射气体边界层耦合相互作用流场特征。研究结果表明,不同冷却介质对于冷却效率有显著的影响,冷却介质比热容越大,相同注入率条件下的冷却效果更好;入射激波干扰会显著影响多孔材料表面的压力分布,使得多孔材料内部冷却介质会发生显著的横向流动,流动的重新分配使得处于高压区的干扰位置处的冷却效果降低;激波干扰引起的局部压力梯度还会使得高温主流与冷却介质掺混加剧,同时壁面的恢复温度也随之升高,显著影响激波干扰局部位置处的冷却效果。

关键词:

发汗冷却;激波干扰, 多孔介质;数值模拟

Abstract: The shock wave interference on transpiration cooling is investigated numerically based on the macro representative elementary volume (REV) scale analysis method. The flow field characteristics of the shock wave/transpiration boundary interaction are obtained. The results indicate that different coolants have significant influence on the cooling efficiency. The larger the specific heat capacity of the cooling media, the better the cooling effect can be achieved under the same blowing ratio condition. The incident shock wave interference can affect the pressure distribution on the material surface, leading to obvious transverse flow of the coolant inside the porous media. The redistribution of the coolant flow can remarkably reduce the cooling effect of the shock wave interference location with higher pressure. The shock wave can also enhance the mixing of the high temperature mainstream and cooling media, and the wall recovery temperature can increase accordingly, weakening the cooling performance obviously.

Key words: Transpiration cooling, Shock wave interference, Porous media, Numerical simulation

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