Propellant Atomization and Ignition Phenomena in Liquid Oxygen/Gaseous Hydrogen Rocket

Abstract

The mixing and combustion processes in a liquid oxygen/gaseous hydrogen rocket combustor were studied. The research focused on observtions of atomization phenomena during steady-state combustion and ignition transients of a rocket engine. Cold-flow atomization as encountered before ignition has been studied using liquid oxygen/gaseous hydrogen and simulation fluids liquid nitrogen/helium. The theoretical assessments show that for binary- and multicomponent systems a transcritical region exists where surface tension is present event at pressuresabove the critical pressure of one component as long as the critical mixing temperature is not exceeded. Also, hot-fire tests utilizing liquid oxygen/gaseous hydrogen demonstrate the strong influence of the flame on the atomization process. The flame propagation during ignition could be identified by the change of the atomization phenomenology before and during the ignition process.