三种不同结构超声速燃烧室流场的数值研究  

Numerical study on flow field in three supersonic combustors

作　　者：周建兴[1] 朴英[1] 陈美宁[1] 岂兴明[1] 刘兆舒[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《航空动力学报》2008年第1期150-155,共6页Journal of Aerospace Power

摘　　要：采用有限体积法求解可压缩N-S方程及组分方程,对三种不同结构的超声速燃烧室进行了数值研究.研究结果表明,凹槽改变了燃烧室波系结构,促进氢气和空气的混合,利于燃烧,所形成的相对稳定的回流区可用于点火和稳定火焰;喷射二次氢气可消除仅一次喷氢所带来问题,进一步促进氢气和空气的混合及燃烧,但带来比较大的总压损失.The supersonic combustion in three different combustors was numerically investigated by solving the compressible Navier-Stokes equations with implicit finite volume method. The results show that the cavity can change the waves in combustors,and facilitate the mixing of hydrogen and air for easier combustion. Besides, the relatively steady reversing area in cavity can be used to ignite and stabilize the flame;ejection of secondary hydrogen can neutralize the problems induced by injecting hydrogen only one time, and also improve the mixing and combustion of hydrogen and air, in despite of slightly larger total pressure loss.

关 键 词：航空 航天推进系统 凹槽 二次氢气 超声速燃烧 超燃冲压发动机 数值模拟 

分 类 号：V231.26[航空宇航科学与技术—航空宇航推进理论与工程]