Experimental study on combustion characteristics of kerosene-fueled scramjet combustor

Kerosene-fueled ignition combustion test was carried out in a scramjet combustor under the condition of total temperature of 810 K, Mach number of 2.0 and different total pressures of 600, 700, 800 and 900 kPa. The combustor model was a dual-mode combustor with double cavity flameholder. Hydrogen was injected in the first cavity, and kerosene was injected in front of the first cavity. Hydrogen, being pilot flame, was the first to be ignited by the spark plug, and then kerosene was ignited by hydrogen. Kerosene was kept burning solely after hydrogen was stopped injecting. Combustion luminosity images were pictured in tests. The test results showed that all the combustion modes of kerosene and hydrogen were upstream cavity stabilization mode under different fueling conditions. Under the higher entrance pressure or the higher kerosene equivalence ratios, the kerosene combustions were upstream cavity stabilization mode. Under the lower entrance pressure or the lower kerosene equivalence ratios, the combustions were downstream cavity stabilization combustion mode. Under the middle entrance pressure or the kerosene equivalence ratios, oscillations of combustion mode occurred. The flameholding capacity of the kerosene-fueled combustor increases with the increase of the entrance total pressure.