旋转发动机燃烧室头部气-固两相流场结构分析  

Structural Analysis on the Gas-Solid Two-Phase Flow Field in the Headof a Spinning Motor Combustion Chamber

作　　者：冯喜平[1] 赵胜海[1] 李进贤[1] 唐金兰[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》2010年第9期33-36,共4页Computer Simulation

基　　金：武器装备预研基金项目(9140C5201120801)

摘　　要：在固体火箭发动机性能的研究中,采用N-S方程、Reynolds湍流模型和颗粒随机轨道模型建立了旋转固体火箭发动机头部区域气-固两相流数学模型,针对安全性,使用FLUENT软件对不同转速发动机头部区域流场进行了数值仿真,分析和比较了有无旋转两种状态下燃烧室头部区域流场结构,研究了转速对燃烧室头部流场结构及热环境的影响。结果表明:发动机的旋转使燃烧室内部流动与传热发生显著变化,导致燃烧室头部压强升高,热防护环境恶化,而且,变化随着转速的增加而迅速加剧,影响发动机内弹道性能和头部热防护性能,为发动机设计提供安全保障的依据。Using the N-S equations,Reynolds turbulence model and the particle stochastic trajectory model,the gas-solid two-phase flow mathematical model of a spinning SRM heading area was established and the flow of the SRM heading area was numerically simulated by FLUENT software under different spinning rates of SRM. Then,the heading flow field structural features between spinning and non-spinning states were compared and analyzed. Furthermore,the influence on the flow and thermo-structure in the head of motor because of different spinning speeds was investigated. The results show that the rotation changes the engine combustion chamber flow and heat transfer significantly,and results in the increasing pressure of head chamber and the deteriorated thermal protection conditions. The changes with the speed of rotation increasing are rapidly enhanced,which seriously effects the performance of interior ballistics and thermal protection. A high degree of attentions should be related to engine designers.

关 键 词：固体火箭发动机 旋转 两相流动 流场结构 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]