基于边界层控制方法的喷管主动冷却数值研究  

Numerical Research on Active Cooling of Nozzles based on Boundary Layer Control Method

作　　者：朱力 李察 王泽宇 黎明 霍亮 ZHU Li;LI Cha;WANG Zeyu;LI Ming;HUO Liang(The 41st Institute of the Sixth Academy of CASIC,Hohhot 010010,China;College of Aerospace Science,National University of Defence Technology,Changsha 410073,China;Military Representative’s Office in Hohhot of the Regional Military Representative Bureau of the Air Force Armament Department in Shenyang,Hohhot 010010,China)

机构地区：[1]中国航天科工集团六院四十一所,内蒙古呼和浩特010010 [2]国防科技大学空天科学学院,湖南长沙410000 [3]空军装备部驻沈阳地区军事代表局驻呼和浩特地区军事代表室,内蒙古呼和浩特010010

出　　处：《新技术新工艺》2023年第3期37-41,共5页New Technology & New Process

摘　　要：采用数值研究的方法进行了基于边界层控制方法的喷管主动冷却的数值研究,验证了基于边界层控制方法的喷管主动冷却方案的可行性,分析了冷却介质喷注压强、冷却介质温度对于冷却效果的影响规律。计算结果表明:当冷却介质具有足够的喷注压强时,采用基于边界层控制方法的喷管主动冷却方案可以有效降低喷管喉部及扩散段内表面的温度,提高喷注压强与降低冷却介质温度均可提高冷却效果。It was carried out that the numerical research on active cooling of nozzles based on boundary layer control method,and the feasibility of active cooling of nozzles based on boundary layer control method was verified.The influence law of injection pressure of cooling medium and temperature of cooling medium on cooling effect were analyzed.The calculation results showed that when the cooling medium had sufficient injection pressure,the active cooling scheme based on boundary layer control method could effectively reduce the temperature of the nozzle throat and the inner surface of the diffusion section,and both increasing the injection pressure and decreasing the temperature of the cooling medium could improve the cooling effect.

关 键 词：发动机 喷管 主动冷却 数值研究 

分 类 号：TM54[电气工程—电器] V435.23[航空宇航科学与技术—航空宇航推进理论与工程]