Patent ID: 6148609
Filing Date: 2000-11-21
Classification: B64B,B64C,B64G,F02K

Abstract:
A gaseous-fuel breathing, stored-oxidizer turbo-rocket thruster comprising:(a) a gas duct defining a gaseous-fuel intake;(b) a source of gaseous fuel;(c) a source of stored oxidizer;(d) a compressor means for compressing gaseous fuel, the compressor means being disposed axially within the gas duct;(e) injector means to inject oxidizer into the compressed gaseous fuel so that the oxidizer mixes with the compressed gaseous fuel;(f) a turbine means operatively associated with the compressor means to drive the compressor means, the turbine means being disposed axially within the gas duct, wherein the turbine means is driven by the gaseous fuel burning with the oxidizer; and(g) a nozzle means operatively associated with the gas duct to exhaust gasses from the gas duct.