Abstract: With the numerical computation of the 3-D model of RBCC,the change of mass flow of primary rocket,which impacts the whole combustion flow area is studied in detail.The research shows that the cavity could not achieve a sufficient effect on flame stabilization and combustion of the whole flow area in gradually divergent combustor of RBCC,when it is in commix-combustion mode.The flame plume of primary rocket works as a lead flame in commix-combustor mode,which changes the combustion.Cooperating with cavity,it mixes the secondary fuel and cold inflow sufficiency and achieves combustion stabilization of the whole flow area,which also offers the research direction of experiment.Through the study of RBCC experiment,it can be seen that when the rocket with small mass flow works,the flame stabilization could be improved and the combustion performance could be improved obviously.The mass flow of primary rocket should be dominated in the certain flow range,which can not only improve the flame stabilization and the ability of flame diffuser,but also ensure the inlet channel starts.

Key words: RBCC;Commix-combustion mode;Flame stability;Primary rocket

摘要： 通过RBCC三维构型的数值计算,详细研究了一次火箭流量变化对于整个燃烧流场的影响。研究表明,对于RBCC逐级扩张型燃烧室,处于混合燃烧模态时,仅依靠凹腔作为火焰稳定器很难实现整个流场有效的燃烧组织和火焰稳定;一次火箭火焰羽流可以为混合燃烧模态提供引导火焰,改变燃烧组织形式,跟凹腔配合实现二次喷注燃料与来流的充分掺混,提高流场的燃烧稳定性能,为实验研究提供了明确的方向。通过RBCC实验研究,也证明了开启小流量一次火箭能够促进整个流场的燃烧稳定,燃烧性能有很明显提高。一次火箭流量还需控制在一定流量范围内,才能既有效提高燃烧室火焰稳定和火焰传播能力,又能够保证进气道的稳定工作性能。

关键词: 火箭基组合循环;混合燃烧模态;火焰稳定;一次火箭