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
刘逸飞 1刘陆广 2窦怡彬 2刘韬略 1贺菲1
作者信息
- 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
- 折叠
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.
Abstract
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Key words
active thermal protection/transpiration cooling/porous media/liquid-gas phase change/thermal protection引用本文复制引用
基金项目
安徽省杰青(2308085J21)
国家自然科学基金(52376154)
国家自然科学基金(U22B20135)
出版年
2024
NETL
NSTL
万方数据