Vaporization and Combustion of LOX Droplets at Supercritical Conditions

摘要

For the large propulsion LOX/GH_2 rocket engine, LOX and GH_2 undergo a sequence of atomization, evaporation, mixing, and combustion processes at the supercritical conditions. Supercritical droplet vaporization and combustion have great effects on the combustion process of a LOX/GH_2 rocket engine and have inspired almost worldwide interest recently. The present work attempted to conduct a comprehensive investigation into LOX droplet vaporization and combustion in supercritical hydrogen streams under various conditions, including pressure and temperature of the surrounding gaseous hydrogen, and the injection velocity and diameter of the LOX droplet. The three-dimensional computational domain adopted a single injector configuration. The mechanism of supercritical droplet vaporization and combustion was analyzed. The work supplies the basal data for a new-style large-thrust LOX/GH_2 rocket engine designing.