Study of low-temperature ignition characteristics in a supersonic combustor

The Ignition combustion experiment in a supersonic combustor was carried out under the conditions with the incoming flow Ma = 2.0, the total temperature at 700 K and the total pressure at 520 KPa(corresponding to the flight Mach number at 3.5). Spray blocks without struts and with struts (with the blockage ratios as 20%, 10%, 7.3% and 5% respectively) were used in the supersonic combustor. The experimental result showed that when there was no strut in the combustor, kerosene could be ignited but was unable to burn stably alone after hydrogen was removed. The addition of struts achieved the independent and stable combustion of kerosene. However, due to the addition of struts, the combustion during the strut test using the blockage ratios at 20%, 10% and 7.3% induced the back pressure to be spread towards the upstream to the entrance of the isolator; When the blockage ratio of the strut was 5%, kerosene could burn stably alone, and the back pressure induced by combustion failed to be spread to the entrance of the combustor. In this paper, the stable flame mode using the cavity and struts was used to achieve stable ignition under the condition with Ma = 2.0, total temperature at 700 K and total pressure at 520 KPa. (C) 2020 Elsevier Ltd. All rights reserved.