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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
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
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
solid rocket motor
flame-spreading
ignition rule
thermo-fluid-solid interaction
ignition process
作者简介
唐金兰（1966-），女，博士，研究方向为固体火箭发动机内流场与热结构。E-mail：FJL302@sohu．com
