Abstract
In this article, three stochastic separated flow models were applied to predict the dispersion of inertial fuel particles in the supersonic turbulent flows. The flow field of continuous phase was simulated by means of Reynolds-averaged Navier–Stokes method with a two-equation turbulence model. Clift’s expression was used to modify the drag force on the particle considering the compressibility effects. The particle-phase statistics were obtained by a secondary-order time-weighed Eulerian method. The ability of those stochastic separated flow models was then compared for predicting the mean particle velocity and the particle dispersion. For obtaining a statistically stationary solution, the stochastic separated flow model required the largest number of computational particles, whereas the improved stochastic separated flow model was found to need the least. The time-series stochastic separation flow model lay in-between. Compared with the other two models, the particle dispersion was over-predicted by the stochastic separated flow model in the supersonic particle-laden boundary layer flow, while the improved stochastic separated flow model was less predictable for the particle spatial distribution in the particle-laden strut-injection flow. Three models could well predict the mean velocities of the particle phase. This study is valuable for selecting a validated model used for predicting the particle dispersion in supersonic turbulent flows.
Highlights
The low-speed two-phase turbulent flows are commonly encountered in abundant industrial applications, such as energy conversion devices and propulsion systems
As the scramjet engine achieves the supersonic combustion, in which the liquid fuel is atomized into spray droplets before the evaporation and the ignition occur, the supersonic particle-laden flows in the scramjet combustor have attracted increasing attention.[1]
The transverse spray-jet is one of the main fuel injection approaches in the scramjet combustor
Summary
The low-speed two-phase turbulent flows are commonly encountered in abundant industrial applications, such as energy conversion devices and propulsion systems. These incompressible two-phase flows have been successfully studied by means of computation methods. As the scramjet engine achieves the supersonic combustion, in which the liquid fuel is atomized into spray droplets before the evaporation and the ignition occur, the supersonic particle-laden flows in the scramjet combustor have attracted increasing attention.[1] Fuel droplets are quickly transported by high-speed air streams and reside in the combustor within several microseconds. The knowledge based on the dispersion of fuel droplets/particles in supersonic flows is fundamental for illustrating the combustion process in scramjet combustors.[2] the research on the supersonic
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