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Abstract
Liquid hydrocarbon supersonic combustion has been experimentally investigated. Kerosene was burnt in a steady. vitiated Mach 2.15 - air flow 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 such that the liquid fuel is injected as a spray. By means of the Mie scattering technique the fuel jet structure was visualised and the evaporation rate estimated.
The mechanisms of ignition and combustion of the kerosene/H2-mixture were studied and compared with the case of hydrogen combustion. Combustor ignition limits have been determined. Fuel-specific combustion phenomena are discussed. It was found that for the kerosene combustion a gas dynamic feedback mechanism strongly affects the supersonic combustion process.
