Ignition and Flame Stabilization in Supersonic Evaporating Fuel Sprays

Abstract eng:
This paper numerically investigates ignition and combustion stabilization in supersonic droplet-laden shear flows. The spatially developing turbulent shear flow separates two hot air streams with different velocities and fuel droplets are injected at the flow inlet to form premixed reactive mixtures. Due to the high compressibility of the present supersonic shear flow, ignition occurs in the high-strain vortex-braid regions but the reactive mixtures entrained in the large eddies are difficult to be ignited at normal atmospheric pressure. Therefore, we increase ambient pressure and introduce oblique shock wave to achieve ignition enhancement and flame stabilization. The results show that the pressure perturbation in the combustion field is enhanced by combustion reaction and increase in internal pressure. The post-shock ignition kernel that is found to exist around the point of maximum temperature, depending on the profiles of the fuel concentration, temperature and Mach number across the shear layer.

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