Experimental and computational studies on Sustained Supersonic Combustion with Ramps and Cavities

The success of future high-speed air transportation will be strongly dependent on the development of hypersonic air-breathing propulsion engines. As effective devices to extend the fuel residence time in supersonic flow and prolong the duration time for hypersonic vehicles cruising in the near-space with power, the backward-facing step and the cavity are widely employed in hypersonic air breathing propulsive systems as flame holders.

The paper deals with the experimental studies on sub-scaled(model) Supersonic combustor with cavities and ramps allowing thorough mixing of fuel and air and flame holding respectively. Mach 2 condition is maintained with aviation kerosene. The combustor performance is evaluated in terms of wall static pressures and temperatures. Before arriving at the size and orientation of ramps and cavities, extensive computational studies are done to arrive at an optimal configuration of combustor. The studies indicated sustained supersonic combustion.