基于梯度孔隙率的楔形鼻锥相变发汗冷却研究  

Experimental and Numerical Study on Phase Change Transpiration Cooling for a Wedge-shaped Nose Cone with a Gradient Porosity Layout

作　　者：刘逸飞 刘陆广 窦怡彬 刘韬略 贺菲[1] LIU Yifei;LIU Luguang;DOU Yibin;LIU Taolue;HE Fei(University of Science and Technology of China,Hefei,230026;Shanghai Electro-mechanical Engineering Institute,Shanghai,201109)

机构地区：[1]中国科学技术大学,合肥230026 [2]上海机电工程研究所,上海201109

出　　处：《导弹与航天运载技术（中英文）》2024年第5期81-91,共11页Missiles and Space Vehicles

基　　金：安徽省杰青(2308085J21);国家自然科学基金(52376154、U22B20135)。

摘　　要：为提高飞行器鼻锥驻点处的发汗冷却效率,提出了一个孔隙率呈梯度分布的楔形多孔鼻锥,在不同冷却剂注入率下,在亚声速条件下对相变发汗冷却进行了试验与数值研究。结果表明,梯度孔隙率的设置可以有效提高驻点处的冷却效率和多孔表面的整体温度均匀度。冷却剂注入率M=0.125%时,驻点处冷却效率提高了52.4%,整体冷却效率提高了31.7%。数值结果表明,梯度孔隙率通过使多孔内最大压力值从驻点后移来提高前缘处的冷却剂流量,改善冷却剂的流动分布,冷却剂注入率为M=0.150%时,驻点处冷却剂流量提高了76%。此外,冷却剂流出多孔结构后在外表面形成的气膜分布更为均匀。In order to improve the transpiration cooling efficiency at the stagnation point of the nose cone of the near space vehicle,a wedge-shaped porous nose cone with a gradient porosity layout is proposed and the phase change transpiration cooling is experimentally and numerically investigated under different coolant injection ratio.The experimental results indicate that the gradient porosity layout can effectively improve the cooling efficiency at the stagnation point and the overall temperature uniformity of the porous surface.When the coolant injection ratio M is 0.125%,the cooling efficiency at the stagnation point is increased by 52.4%,and the overall cooling efficiency is increased by 31.7%.The numerical results indicate that the gradient porosity layout increases the coolant mass flux at the leading edge and optimizes coolant distribution by moving the maximum pressure value at the stagnation point downstream.When the coolant injection ratio M=0.15%,the coolant mass flux at the stagnation point is increased 76%.In addition,the film formed by the coolant flows out of the porous structure is more uniform.

关 键 词：主动热防护 发汗冷却 多孔介质 液气相变 梯度孔隙率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]