Effects of Injector-Combustor Geometry on the Performance of Supersonic Combustor

Abstract

Experimental studies were made on supersonic combustion in a two dimensional combustor using Hydrogen as fuel. A Hydrogen vitiation air heater with oxygen replenishment was used for simulating high temperature air entering the supersonic combustor. Transverse fuel injection was employed from the walls (Single wall and Double wall)of the combustor at upstream (Pilot injection) and downstream (Primary injection) of backward-facing step. Experiments were also conducted with single wall injection and in the absence of step and pilot injection. Ignition and pressure drop characteristics of the combustor were determined. Wall static pressures were considered as a measure to find the advantages of pilot and double wall injections. The effects of pilot injection, double wall injection and the step on the performance of the supersonic combustor were studied in terms of combustion efficiency and stagnation pressure drop. It is found that the combustor with pilot fuel and step configuration, employing double wall injection yielded better results.

Keywords:

• Supersonic combustion
• backward-facing step
• pilot injection
• double wall injection
• combustion efficiency
• pressure drop factor

Additional information

Notes on contributors

B. V. N. CHARYULU

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