喷嘴参数调整下的火箭推力室膜冷却优化研究  

Effect of Rocket Thrust Chamber Gas Film Holes on Cooling Characteristics

作　　者：于柠宁 王忠巍[1] 张海[1] YU Ningning;WANG Zhongwei;ZHANG Hai(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150000,China)

机构地区：[1]哈尔滨工程大学动力与能源工程学院,哈尔滨150000

出　　处：《工程热物理学报》2025年第1期120-126,共7页Journal of Engineering Thermophysics

基　　金：哈尔滨工程大学高水平科研引导专项(No.3072022QBZ0302)。

摘　　要：利用数值仿真方法分析某型火箭推力室气膜孔变化对冷却特性地影响,对比了固定吹气量条件下冷却效果,并探究对孔数(Ni=200,300,400)、出口直径(b/S=0.446,0.594,0.743)及出口张角(β=30°,40°,60°)的变化对射流状态及冷却效果地影响,结果发现:气膜孔孔数及出口结构参数改变对气膜均匀性及射流流态产生影响,在基准孔结构基础上就行调整,在一定程度上能够改善冷却效果。The effect of adjusting the air film holes on the cooling characteristics of a particular type of rocket thrust chamber is analyzed with a numerical simulation method.The cooling effect is compared under fixed blowing volume conditions,and the effects of changing the outlet diameter(b/S=0.446,0.594,0.743),the outlet angle(β=30°,40°,and 60°),and the number of holes(N i=200,300,400)are investigated with respect to the state of the jet flow and the cooling effect.The findings demonstrate that variations in the quantity of gas film holes and outlet structural characteristics affect both the jet flow condition and the regularity of the gas film.To a certain extent,modifications can be made to enhance the cooling effect based on the benchmark hole structure.

关 键 词：超声速 气膜冷却 壁温 数值模拟 

分 类 号：TK121[动力工程及工程热物理—工程热物理]