Influencing factors of strut-based RBCC performance in ramjet mode

Aiming at two expansion configurations of RBCC combustor, three-dimensional numerical simulation and ground tests were carried out to study the effects of structural parameters and flame stabilization devices on engine performance in ramjet mode. The results show 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 flame holder in each combustor can effectively enhance combustion of fuel and extend the range of flame propagation. The better performance of thrust increased by 682 N through configuration improvement has been verified with direct-connect test. Moreover, the sustained combustion of fuel after shutting down the rocket could be achieved when the cavities location is close to the pylons, in such a case the specific impulse has a nearly 50% increase with rocket off. Pre-combustion shock train can be more easily established in isolator by reducing the width of central strut at Ma=4 and better reaction of subsonic combustion can be ensured, in this case the engine performance has improved by 418 N.