Experimental investigation of performance of a strut-cavity based scramjet combustor in clean air

Experiments were performed to study the performance of a strut-cavity based scramjet combustor in clean air. The fuel was liquid kerosene that was injected from the side walls of the strut or both of the strut and the side walls of the combustor. The results show that, when the fuel was injected upstream from strut alone or the fuel equivalence ratio increased by 0.1, the overall wall pressure and the peak wall pressure were higher. When the total fuel equivalence ratio was fixed, the overall wall pressure of the injection from strut alone were higher than that from both of the strut and the side walls of the combustor, but the original pressure rise was up-stream. A one-dimensional analysis code was used to obtain the axial Mach number and the combustion efficiency. The minimum combustor Mach number was lower than 0.5, and most area of the center of the combustor was subsonic. When the fuel was injected upstream from strut alone, the combustion efficiency was higher. When the total fuel equivalence ratio was fixed, the combustion efficiency of the injection from strut alone was higher than that from both of the strut and the side walls of the combustor.