Numerical Analysis of Supersonic Flow Past a Double Cavity Scramjet Combustor

The fundamental physics involved in cavity flows are of great academic interest. The cavity flows are characterized by an unstable shear layer, vortex formation, its mutual interactions, acoustic generation and its propagation. Dual cavities have lots of applications in flame holders of combustors due to their remarkable potential to stabilize the process of combustion. The present study gives an understanding of the fundamental flow features when flow past a dual flame holder cavity is of aspect ratio 3.0 for a Mach number of 3.0. The results were then compared with the flow features around a single cavity of similar inflow and geometric conditions to study the influence of change in the shape of the geometry on flow dynamics. It is observed that combustor geometry has a considerable influence on flow dynamics and the acoustic behavior of fluid flow in the combustor. All the simulations were done using ANSYS FLUENT 19.2 using k-epsilon model. Most of the research work till date is limited to single cavity flow analysis and flow control methods. However, there are limited research works found on flow dynamics around a scramjet combustor. The present simulation resolves hydrodynamic and acoustic flow features in and around during supersonic flow past a dual cavity.