Numerical Simulation on Two Phase Combustion Characteristic in Solid Rocket Ramjet Afterburning Chamber

Abstract

Numerical simulation on two-phase combustion characteristic in afterburning chamber of solid rocket ramjet was carried out by applying particle trajectory model. It was analyzed that the nozzle number of secondary combustion chamber, inlet angle of air and particles diameter impact on efficiency of combustion. Results show that the combustion efficiency in the afterburning chamber is highest, achieving 99.6% when the angle between both air inlets is 180°, particle diameter is 15μm, and 5-hole nozzle is used. By contrary, when the angle between both air inlets is 90°, particle diameter is 5μm, and 5-hole nozzle is used, the afterburning chamber has a lowest combustion efficiency of 70.3%.