气氧/甲烷涡流冷壁燃烧室流场与壁面耦合传热分析  

Heat transfer analysis for a GOX/CH_4 vortex cold-wall combustor

作　　者：孙得川[1] 杨建文[1] 白荣博[1] 

机构地区：[1]西北工业大学航天学院/燃烧流动和热结构国家级重点实验室,陕西西安710072

出　　处：《推进技术》2011年第3期401-406,共6页Journal of Propulsion Technology

基　　金：国家"八六三"基金(2007AA0168);航天创新基金(CASC0309)

摘　　要：针对涡流燃烧室的试验模型,耦合计算了其中的燃烧、流动和传热过程。湍流模型采用RNG k-ε两方程模型,辐射传热采用P1辐射模型,化学反应采用有限速率模型。数值模拟了涡流燃烧室在20s内的传热过程,得到了燃烧室和喷管的壁面温度分布随时间的变化。燃烧室侧壁面和头部温度在4秒内就达到较稳定状态,在涡流保护下侧壁面最高温度在650K左右,头部最高温度在785K左右。对于热沉喷管,壁面温度随时间基本呈缓慢线性上升,在一定的时间内可以满足实验要求。For the vortex cold-wall combustor,its working process including inner flowfield,combustion,and heat transfer between flow and structure was simulated by a coupling method.RNG k-ε turbulence model,P1 radiation heat transfer model,and the finite rate reaction model were used in the numerical simulation.The temperature distribution of the structure of the test thruster within 20 seconds was obtained.Temperature of head and side wall increases rapidly and soon tend to be stable within 4 seconds.Under the protection of the vortex of the cool oxidant,the maximum temperature of side wall is about 650K and highest temperature of head wall is under 785K.The temperature of the heat sink nozzle increases linearly and slowly,fulfilling the testing requirement.

关 键 词：涡流燃烧室 数值仿真 传热 耦合 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]