中文摘要：

在极超音速的推进技术的保持火焰的机制是在延长极超音速的车辆的持续时间时间的最重要的因素。反应建模的二维的联合含蓄的平均 Reynolds 的海军司烧方程，砍压力运输 k- 骚乱模型和 finite-rate/eddy-dissipation 被用来模仿一间典型基于神气的超音速冲压式喷气发动机燃烧室的燃烧流动地。我们在燃烧室在参量的分布上调查了氢空气反应机制和燃料注射温度和压力的效果。数字结果与试验性的数据显示出质的同意。氢空气反应机制沿着燃烧室，和扩大的墙在参量的分布有仅仅细微差别波浪和冲击波同时在燃烧室存在。而且，扩大波浪在冲击波前被形成。当注射压力或温度增加时，转变从冲击波发生到正常冲击波，并且反应地区变得更宽广。当注射压力和温度两个都增加时，波浪与亚声的流动从燃烧室被推。当波浪在神气前被产生时，分离地区被形成在因为冲击波和边界层的相互作用，近加倍燃烧室的墙。分离地区变得更小并且与冲击波的消失消失。因为水平燃料注射，涡度在神气的基础脸附近被产生，并且这个区域是为狂暴的燃烧的主要起源。

英文摘要：

The flame-holding mechanism in hypersonic propulsion technology is the most important factor in prolonging the duration time of hypersonic vehicles. The two-dimensional coupled implicit Reynolds-averaged Navier-Stokes equations, the shear-stress transport k-ω turbulence model and the finite-rate/eddy-dissipation reaction models were used to simulate the combustion flow field of a typical strut-based scramjet combustor. We investigated the effects of the hydrogen-air reaction mechanism and fuel injection temperature and pressure on the parametric distributions in the combustor. The numerical results show qualitative agreement with the experimental data. The hydrogen-air reaction mechanism makes only a slight difference in parametric distributions along the walls of the combustor, and the expansion waves and shock waves exist in the combustor simultaneously. Furthermore, the expansion wave is formed ahead of the shock wave. A transition occurs from the shock wave to the normal shock wave when the injection pressure or temperature increases, and the reaction zone becomes broader. When the injection pressure and temperature both increase, the waves are pushed out of the combustor with subsonic flows. When the waves are generated ahead of the strut, the separation zone is formed in double near the walls of the combustor because of the interaction of the shock wave and the boundary layer. The separation zone becomes smaller and disappears with the disappearance of the shock wave. Because of the horizontal fuel injection, the vorticity is generated near the base face of the strut, and this region is the main origin for turbulent combustion.