Abstract
Structures of liquid-fuel injection in supersonic crossflow is studied experimentally. Schemes of flush-wall injector and aviation kerosene are selected. The conditions of the supersonic freestream are kept constant (total pressure is 0.5MPa, total temperature is 500K and Mach number is 2) and the diameter of the injector is fixed as 0.5mm, while seven scenarios of injection angle and three scenarios of injection driven pressure are discussed. Both methods of schlieren and planar laser induced fluorescence (PLIF) techniques are implemented to obtain the visual images of the liquid-fuel injection. The penetration height of fuel is analyzed quantitatively with the aid of Photoshop and Origin. The results serve not only the future computational simulation but also combined scheme of flush-wall injector and other combustor configurations.
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