Studies on Combustion in Supersonic Flows

Abstract

Combustion studies are carried out on co-axial supersonic streams by transverse injection of fuel (kerosene) in a combustor using wall mounted axisymmetric cavities. The primary flow is maintained at a Mach number of 1.32 and the secondary flow is sonic. The combustor is attached at the exit of the nozzles. The cavities are attached at the inlet of the combustor. Temperature measurements are made at the exit plane of the combustor. Higher combustion efficiency and rise in stagnation temperature is observed for cavity configurations than for no-cavity under identical operating conditions.