大长径比SRM头部复杂结构三维纯气相火焰传播过程  

3D pure gas flame-spread process in complicated head structure of SRM large L/D ratio

作　　者：唐金兰[1] 樊建龙[1] 李进贤[1] 冯喜平[1] 

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072

出　　处：《固体火箭技术》2010年第2期167-170,共4页Journal of Solid Rocket Technology

基　　金：重点实验室基金项目及武器装备预研基金项目

摘　　要：以N-S方程,RNGk-ε湍流模型、P1辐射模型为基础,以美国"大力神-Ⅳ"运载火箭助推发动机PQM-1为算例,采用流固耦合传热的火焰传播边界条件,建立了大长径比SRM头部复杂结构的三维纯气相火焰传播模型,分析了发动机点火瞬态头部径向和轴向翼槽内的火焰传播过程。结果表明,对于采用单喷管点火发动机点火的大长径比SRM,头部翼槽的初始发火点在轴向翼槽末端,且头部轴向翼槽内的冷空气影响径向翼槽内的火焰传播,而轴向翼槽内的火焰传播过程对药柱锥形通道内的火焰传播影响不大。Based on the N-S equation,RNG k-ε turbulence modeling and P1 radiant modeling,the pure gas flame-spread 3D model was established by using flow-solid coupling boundary condition.By taking PQM-1 the boost motor of Titan-Ⅳ as an example,the flame-spread about radial-fin and axis-fin during SRM ignition transient was analyzed.The results show that initial ignition point is at axis-fin end for SRM with single nozzle ignition-motor,the flame-spread in radial-fin is affected by cool air from axis-fin,the flame-spread of axis-fin doesn＇t affect the flame-spread of cone channels.

关 键 词：固体火箭发动机 火焰传播 点火准则 热流固耦合 点火过程 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]