Inlet Geometry Effects on the Internal Performance of a Variable Flow Ducted Rocket Combustor

Abstract

Connected pipe combustion experiments and numerical simulations of the internal reacting flow in a ducted rocket combustor at various conditions were conducted. The effect of the air inlet configuration was investigated. The considered equivalence ratio in experimental and numerical investigation varied between 0.35 to 1.57 in order to reflect the variable flow conditions of the ducted rocket. Three kinds of combustors have been used in order to evaluate the air inlet geometry effect; a two-inlet combustor with inlet angle of 90°, a two-inlet with inlet angle of 180° and a four-inlet with inlet angle of 90°. The carbon particles within the fuel rich gas stream were treated as a separated stream from the main fuel stream to reflect the influence of carbon particle reaction. The recirculation stream of the carbon particles and the burned carbon mass fraction were found to have a major effect on the temperature rising. The four inlet combustor exhibited the best combustion efficiency and the two inlet combustors did not show large differences in terms of performance.