摘要
为实现固冲发动机二次燃烧模型验证,结合固冲发动机工作条件,设计了一种带透明观察窗燃烧实验装置;营造了简单的燃烧环境,实现了燃烧过程掺混作用的弱化;借助高速摄像进行了以空气速度作为单一变量的含硼富燃燃气燃烧可视化测量,获得了火焰形态结构;采用高速数据采集,获得了燃烧室压力;将实验数据与数值模拟结果进行了对比和分析。结果表明,燃气与空气速度相近时,火焰呈锥角结构,硼粒子的点火距离较长;燃气与空气速度差较小时,同一位置燃烧室压力较大;燃气与空气速度近似程度决定火焰的形态;数值模拟结果与实验结果基本吻合。
A test facility,which has transparent observation windows,was designed to solve the verification of secondary com-bustion models according to the working conditions of solid rocket-ramjet motor（SRRM）.This facility was made to shorten the effect of mixing and form simple combustion environment.The combustion phenomena of fuel-rich gas containing boron particles,which was based on the single variable of air inlet velocity,were studied with the help of high-speed photographer and data acquisition. The shape of fire and pressure of combustion chamber were observed and numerical simulation was then compared with the experiment data.The experiment results indicate that the diffusion flame has a cone-shape contour,the distance of secondary ignition of boron particles is longer and the pressure of combustion chamber in the same location is higher when the air inlet velocity is approximate to the gas velocity.The contour of the diffusion flame is determined by the approximate level of air inlet velocity and the primary gas velocity and the results of numerical simulation are basically matched with the experiment outcome.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2014年第6期787-791,共5页
Journal of Solid Rocket Technology
基金
973支持项目
关键词
硼粒子
透明观察窗
高速摄像
点火距离
born particles
transparent observation window
high speed photographer
distance of ignition
