超声速燃烧室内氢气燃烧的三维数值研究  

3-D numerical investigation on supersonic hydrogen combustion in scramjet combustor

作　　者：周建兴[1] 朴英[1] 岂兴明[1] 祝剑虹[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》2007年第12期1984-1988,共5页Journal of Aerospace Power

摘　　要：通过隐式耦合求解可压缩N-S方程及组分方程,对氢气的超声速燃烧进行三维数值模拟,对燃烧室内的冷热态流场,以及氢气喷射压力对燃烧的影响进行了系统分析和研究.研究表明,燃烧放热以及氢气喷射压力提高都会导致燃烧室内波系结构变化,沿周向的流向涡增强,压缩波和膨胀波与氢气核心区的相互作用增强,促进氢气和空气的掺混,更利于氢气的燃烧.3-D numerical simulation for supersonic hydrogen combustion was performed by solving the compressible Navier-Stokes equation and composition equations using implicit finite volume methods. Meanwhile, the effect of hydrogen injection pressure on combustion was analyzed and studied. The results show that, owing to the heat release from combustion and the influences of hydrogen＇s injection pressure, the flow field changes greatly, leading to enhanced streamwise vortex and stronger interaction between waves in the combustor and hydrogen flow, and also facilitating the mixing of hydrogen and air for improved hydrogen combustion performance.

关 键 词：航空 航天推进系统 超声速燃烧 氢气 流向涡 超燃冲压发动机 

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]