超燃冲压发动机二次喷氢燃烧的数值研究  

Numerical simulation on reburning of secondary hydrogen in scramjet's combustor

作　　者：周建兴[1] 朴英[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《推进技术》2008年第2期129-134,共6页Journal of Propulsion Technology

摘　　要：采用有限体积法求解可压缩N-S方程及组分方程,对直壁扩张燃烧室内二次喷氢补燃进行系统的数值模拟,对燃烧室内冷热态流场以及二次氢气的喷射角度、压力和温度等因素的影响进行了系统研究。研究结果表明,喷入二次氢气可以在一定程度上改善只喷一次氢气带来的问题,二次氢气的参数变化影响到燃烧室内的波系结构,能够使得氢-空气混合更加充分,更利于氢-空气的完全燃烧。The supersonic combustion of secondary hydrogen flow in a eombustor with constant and expanded section area was numerically investigated by solving the compressible Navier-Stokes equations with implicit finite volume methods. The results show that secondary hydrogen can neutralize the problems induced by only one piece of hydrogen which jets into the combustor. It also reveals that because of the heat release due to combustion, the influences of the secondary hydrogen jetting angle, static pressure and static temperature, the flow field changes greatly, thus making the hydrogen and air mixed more fully and easier to burn.

关 键 词：超音速冲压喷气发动机 氢气 超音速燃烧 数值仿真 

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]