超音速燃烧室凹槽流动特性研究  

Study on cavity flow characteristics of supersonic combustor

作　　者：肖隐利[1] 陈亮[1] 宋文艳[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《固体火箭技术》2008年第6期583-587,共5页Journal of Solid Rocket Technology

基　　金：西北工业大学博士论文创新基金资助项目(W016107)

摘　　要：对超音速燃烧室内各种构型的凹槽流场进行了数值模拟,研究了凹槽的后壁面斜角、凹槽长高比及凹槽前后壁面高度比等参数对凹槽流场的影响,计算了各种构型凹槽的阻力、停留时间等。研究结果对定量认识凹槽流场、优化凹槽构型、设计高效率的火焰稳定器具有一定借鉴作用。The flow field in the cavities of various configuration of the supersonic combustor was numerically simulated, and the effects of some parameters on flow field in the cavity were investigated, including back-wall oblique angle, length-to-depth ratio, height ratio between front-wall and back-wall, and so on. Resistance and standing time of cavities of various configurational were calculated. The investigation results can be used as a reference for quantitatively describing cavity flow field, optimizing cavity configuration and designing high-efficiency flame stabilizer.

关 键 词：超燃冲压发动机 火焰稳定器 凹槽 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]