Supersonic combustion of kerosene/H-2-mixtures in a model scramjet combustor

Liquid hydrocarbon supersonic combustion has been experimentally investigat ed. Kerosene was burnt in a steady, vitiated Mach 2.15 - air now of a model scramjet combustor. The fuel is injected into the supersonic air stream by means of pylons. The effervescent atomisation method has been employed suc h that the liquid fuel is injected as a spray. By means of the Mie scatteri ng technique the fuel jet structure was visualised and the evaporation rate estimated. The mechanisms of ignition and combustion of the kerosene/H-2-mixture were studied and compared with the case of hydrogen combustion. Combustor igniti on limits have been determined. Fuel-specific combustion phenomena are disc ussed. It was found that for the kerosene combustion a gas dynamic feedback mechanism strongly affects the supersonic combustion process.