氢氧发动机非均匀圆孔头部气膜冷却数值模拟  

Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine

作　　者：王太平 孙冰[2] 薛立鹏 刘迪 李林 WANG Taiping;SUN Bing;XUE Lipeng;LIU Di;LI Lin(Beijing Key Laboratory of Cryogenic Technology Research,Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;Beihang University,Beijing 100084,China;Beijing Electro-Mechanical Engineering Institute,Beijing 100074,China)

机构地区：[1]北京宇航系统工程研究所深低温技术研究北京市重点实验室,北京100076 [2]北京航空航天大学,北京100084 [3]北京机电工程研究所,北京100074

出　　处：《火箭推进》2022年第4期1-12,共12页Journal of Rocket Propulsion

摘　　要：氢氧火箭发动机燃烧室壁面热环境十分恶劣,头部气膜冷却是主要辅助冷却手段之一,圆孔头部气膜冷却是重要的设计方案。对圆孔型头部气膜进行了三维数值仿真研究,考虑推力室外部再生冷却的影响,通过全面数值实验分析了气膜流量占比、气膜孔直径和相邻气膜孔面积比等参数的影响,提出一种非均匀分布的圆孔头部气膜冷却方案。结果表明,在氢氧火箭发动机圆孔头部气膜冷却中,存在一个最佳吹风比使得头部区域冷却效果最好,最佳吹风比的值由气膜流量占比和气膜孔直径共同决定,最佳吹风比介于5.454~5.849之间;通过合理的非均匀圆孔气膜结构设计,控制相邻气膜孔面积比在0.6~0.8范围内,采用提出的非均匀气膜孔方案有利于提高燃烧室的整体性能。The thermal environment of the combustion chamber wall in hydrogen/oxygen rocket engine is very harsh,and the circular-hole film cooling is one of the main auxiliary methods to reduce the heat load in the near-injection region.In this study,the three-dimensional numerical simulation of the head gas film with cylindrical film hole was carried out,considering the influence of regenerative cooling outside the thrust chamber.Through comprehensive numerical experiments,the effects of parameters such as the proportion of gas film flow ratio,the diameter of film hole and the area ratio of adjacent film holes,and a gas film cooling scheme of circular hole head with non-uniform distribution was proposed.The results show that there is an optimal blowing ratio to make the cooling effect of the head area the best in the film cooling of the head of the hydrogen/oxygen rocket engine.The optimal blowing ratio is determined by the ratio of the air film flow rate and the diameter of the air film hole,and the optimal air blowing ratio in this study is between 5.454 and 5.849.Through the reasonable structure design of the non-uniform circular-hole,the area ratio of adjacent gas film holes is controlled within the range of 0.6-0.8.The proposed non-uniform film hole scheme is beneficial to the improvement of the overall combustion chamber performance,which can provide a reference for engineering design.

关 键 词：头部气膜冷却 非均匀气膜 气膜冷却效率 燃烧室 氢氧火箭发动机 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]