液体火箭发动机燃烧室液膜冷却数值研究  

Numerical Study of Liquid Film Cooling in Combustion Chamber of Liquid Rocket Engine

作　　者：张宏伟[1] 陶文铨[1] 何雅玲[1] 丰镇平[1] 

机构地区：[1]西安交通大学动力工程多相流国家重点实验室,西安710049

出　　处：《西安交通大学学报》2006年第7期748-752,共5页Journal of Xi'an Jiaotong University

基　　金：国家自然科学基金资助项目(50476046)

摘　　要：对液体火箭发动机燃烧室中的液膜冷却进行了数值模拟.采用有限容积法对燃气和液膜控制方程同时进行求解,对燃气和液膜分别采用标准k-ε模型和修正的Van Driest模型描述其湍流流动.燃气的辐射传热采用热流模型计算,同时对液膜干涸点下游的流动与传热进行了模拟.详细研究了气液界面上质量、动量和热量的传输特性,发现当壁面绝热时,燃气对流传热和液膜蒸发所吸收的汽化潜热在界面热量传递中起主导作用,但燃气的辐射传热和液膜显热不能被忽略.同时,分析了各种因素对液膜长度的影响,计算结果与实验符合良好,对工程实践有指导意义.A numerical study was performed to investigate the liquid film cooling in a rocket combustion chamber. The finite volume method was employed to solve simultaneously the respective governing equations for the liquid film and gas stream. The standard turbulence k-ε model was used to simulate the turbulence gas flow and a modified Van Driest model was adopted to simulate the turbulent liquid film flow. Radiation of gas stream was also considered and simulated with the FLUX model. Downstream of the liquid film dryout point the gaseous film cooling was numerically studied. Mass, momentum, and heat transfer characteristics at the interface were investigated. The results show that heat transfer at the gas-liquid interface in a rocket combustion chamber with insulated wall is mainly dominated by the convection of the free stream and transport of latent heat associated with the evaporation of the liquid film. In addition, the effects of the radiation and sensible heat transfer cannot be ignored. Various effects on the liquid film length were also examined. The numerical predictions agree well with the experimental data for the liquid film length.

关 键 词：燃烧室 液膜冷却 界面 湍流 数值模拟 

分 类 号：TK124[动力工程及工程热物理—工程热物理]