Influence of combustion stabilization by primary rocket under commix-combustion mode in RBCC

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.