针对固体火箭超燃冲压发动机,设计了多级小角度扩张的超燃冲压发动机燃烧室结构,采用凹腔和扰流装置两种混合增强及火焰稳定方式,通过包含简化动力学的数值模拟方法,研究了不同构型燃烧室摻混燃烧性能。结果表明,燃烧室扩张角度对燃烧效率的提高有影响,但作用效果有限;凹腔结构虽然促进了燃烧反应的进行,有利于提高燃烧效率,同时也带来了较大的内部阻力;扰流装置较大的提高了一次燃气与来流空气间的掺混度,对于燃烧效率的提高意义明显。

For increasing the performance of mixing and combustion, the scramjet was developed, which consists of axisymmetric combustor with expanding degree. The numerical simulation including simple chemical mechanism was developed to investigate the reactive flow characteristics for supersonic combustion in circular combustor solid rocket scramjet which is combined with vortex generator and cavity. It is indicated that the expanding degree of combustor can increase the combustion efficiency to a certain extent: The combustion reaction would be improved by using cavity configuration whereas the internal resistance would be great; The combustion efficiency is obviously enhanced due to the vortex generator can augment the mixing intensity of the fuel-rich gas.