涡流冷壁推力室传热模型分析计算  

A Heat Transfer Model for Vortex Cool-wall Rocket Engine Chamber

作　　者：孙得川[1] 白荣博[1] 刘上[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2011年第4期87-91,共5页Computer Simulation

基　　金：国家863基金(2007AA0168);航天创新基金(CASC0309)

摘　　要：研究发动机燃烧室温度优化控制问题,由于燃烧室温度控制较难,为了预估新型涡流燃烧冷壁火箭发动机的壁面温度,根据发动机内部流动和传热分析,对组合化学平衡、辐射传热和热传导特性,提出了一维传热模型。采用模型对以氢氧为推进剂的涡流燃烧室进行了传热过程和影响因素的仿真分析,获得了稳定状态下的壁面温度,以及燃烧室压力、氧化剂喷注速度、燃烧室长度等参数对壁温的影响关系,仿真结果与实验一致。证明模型为涡流燃烧发动机设计提供了重要工具,对进一步的实验研究有指导意义。To predict the wall temperature of the vortex cold-wall thruster of a new type of rocket engine,a one-dimensional heat transfer model based on the analysis of the flowfield structure and the heat transfer in vortex combustor was proposed.This model was used to calculate the wall temperature and analyze the influence parameters of a small thruster with hydrogen and oxygen as the propellant.The wall temperature and the relations between wall temperature and the parameters such as chamber pressure,inlet velocity of oxidant,and length of combustor were obtained by simulation.The results agree with the experiments.This model is the basis of design of the vortex thruster and useful for future experimental research.

关 键 词：涡流冷壁推力室 传热模型 数值模拟 影响因素 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]