Investigation of strut-based RBCC engine configuration to improve performance in ramjet mode

For two expansion configuration of RBCC combustor, three-dimensional numerical simulation and ground tests have been carried out to study the effects of structural parameters and flame stabilization equipments on RBCC performance in ramjet mode. The result shows that better combustion reaction and less total pressure loss can be achieved with a smaller expansion angle of the second combustor. Pylons for injection with cavities structure in each combustor can effectively enhance combustion organization and expand the range of flame propagation. The better performance through configuration improvement has been verified with direct-connect experiment. Moreover, the sustained burning of fuel after shut down the rocket could be achieved when the cavities location was close to the pylons. Pre-combustion shock system can be more easily established in isolator by reducing the width of strut at high Mach in ramjet mode. Better reaction of subsonic combustion can be ensured.