Experimental study on RBCC with oxygen/kerosene ejector rocket

To further investigate the combustion performance of the Rocket Based Combined Cycle (RBCC), a series of experiments were performed at a flight Mach number of 4.0. The reliable ignition and steady combustion of the ejector rocket and ramjet combustor were successfully achieved. The gas oxygen and liquid kerosene were injected into the rocket at a fuel equivalence ratio of 1.6, providing the high enthalpy ejection gas at a total pressure of 2.0Mpa. To obtain different ratios of the primary stream mass flow rate to the secondary fuel equivalence ratio, the rocket mass flow rate was regulated by the number of the rocket nozzle. The experimental results demonstrated that the increase of the rocket can lead to a limited improvement on the total pressure in the ramjet combustor. The total pressure recovery was also improved by the higher secondary fuel equivalence ratio, appropriate injection location and optimization of the exhaust nozzle size.