Effect of fuel temperature on mixing characteristics of a kerosene jet injected into a cavity-based supersonic combustor

To explain the phenomenon observed in previous experiments of kerosene-ignition failure scramjet combustors as kerosene temperature increases, we numerically investigate mixing characteristics a jet injected into cavity-based supersonic combustor at different injection temperatures by using compressible two-phase flow large-eddy simulation based on Eulerian–Lagrangian approach. The results indicate that, upon injecting high temperatures, field preceding leading edge cavity is similar to typical gas crossflow. wall counter-rotating vortex pair (CVP) develops more fully and eventually becomes main pair. This evolution CVP modifies shear layer alters local flow-field near cavity. Upon its evaporation rate increases sharply recirculation zone enlarges, which causes vapor be entrained Because kerosene-vapor lower than that low-speed fluid cavity, significant amount entering not only makes mass fraction exceed fuel stoichiometric but also reduces negatively impacts ignition process. delay time much longer when high, consistent with inability initial flame kernel form experiment.