Experimental Investigation of Kerosene Fuel Combustion in Supersonic Flow

An experimental investigation of kerosene fuel ignition and combustion stabilization in a two-dimensional scramjet combustor duct was conducted. The purpose of the study was to demonstrate scramjet operational parameters (flameholder design, ignitor technique, and area ratio) with kerosene fuel. The model was tested at the freejet Mach number Mx of 6. Hydrogen piloting was used for ignition and stabilization of kerosene combustion. Conditions were found where the kerosene combustion was sustained after the hydrogen pilot was no longer being injected. Distributions of gas-thermodyn amic parameters along the duct, stability, and joint inlet-combustor operation are discussed. Nomenclature ER = equivalence fuel-air ratio hc = inlet entry height, 0.2 m M = Mach number p = pressure, Pa T = temperature, K x = xlhc = relative distance along the x axis T = time, s