Measurement of heat flux distribution of supercritical kerosene fueled supersonic combustor

Heat flux distribution of supercritical kerosene fueled, single-side expanded supersonic combustor with two dislocated cavities was experimentally studied. The effects of inlet Mach number, total temperature, mass flow rate and fuel equivalence ratio on the combustion and heat transfer characteristics in the supersonic combustor were analyzed. The isolator inlet Mach number is 2.0 and 2.5, the total temperature is 1305 K to 1701 K and the mass flow rate is 2.0 kg/s to 3.0 kg/s. Pilot hydrogen and liquid or supercritical (773±20 K) China No.3 kerosene were injected in front of the cavities with the equivalence ratio ranges from 0.52 to 0.88. Results show that heat flux increases with the inlet temperature and mass flow rate, however, the influence of equivalence ratio is non-monotonic in the range of this study. The two inlet Mach numbers also trigger different combustion modes, which further complicates the heat flux distribution. In the end, a three parameter correlation is proposed and fitted to normalize the experiment results for comparison and discussion. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.