Combustion Experiment to Evaluate a LOX Vaporization Nozzle for a Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine with a 1500N-Thrust

Abstract

The authors have proposed a LOX vaporization nozzle for swirling-oxidizer-flow-type hybrid rocket engines to increase engine performance. In this study, we developed the LOX vaporization nozzle for this type of a hybrid rocket engine with a 1500N-thrust. Vaporization experiments, using a LOX supply system for the nozzle to be independent of a GOX supply system for the engine, were conducted. The test runs at little oxygen mass flow rates and low combustion pressures at the design point showed that LOX could be vaporized safely through the nozzle. It was confirmed that the design of the LOX vaporization nozzle was proper. Vaporization and burning experiments using vaporized O₂ through the LOX vaporization nozzle showed that reliable and rapid ignition and stable combustion without combustion oscillation were achieved. The LOX vaporization nozzle increased the engine performance of the swirling-oxidizer- flow-type hybrid rocket engine.