| Citation: | JI Pengfei, XU Xu, CHEN Bing, et al. Combustion performance investigation of a dual-struts scramjet[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(2): 366-374. doi: 10.13700/j.bh.1001-5965.2016.0097(in Chinese)
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In order to investigate the flame stabilization, combustion state and flame propagation characteristics of scramjet, based on a dual-struts supersonic combustor with staged injections, experiments with continuously adjusted equivalence ratio were conducted. Experiments with combustor inlet Mach number of 2 and total temperature of 1 436 K were conducted to simulate flight Mach number of 5.5. The results show that when injecting fuel is solely from the upstream strut, the extinction equivalence ratio is 0.19 and it is not affected by the downstream combustion. When injecting fuel is solely from the downstream strut, the extinction equivalence ratio is 0.46, and the effect of downstream equivalence ratio change on wall pressure would be reduced by upstream flame, with which the extinction equivalence ratio would be decreased. Transformation between two combustion states could be realized by adjusting the upstream equivalence ratio, and hysteresis could be observed in the transformation process. Experiments with combustor inlet Mach number of 3 and total temperature of 1 899 K were conducted to simulate flight Mach number of 6.5. The results show that as the total temperature of incoming flow increases, ignition and stable flame can be realized by fuel injection solely at the upstream strut, the upstream flame is lifted, back-pressure capability of the combustor can be strengthened, and more fuel can be injected into the flow.
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