Patent ID: 6691504
Filing Date: 2004-02-17
Classification: F02C,F02K

Abstract:
A gaseous-fuel breathing rocket engine comprising:(a) a gaseous-fuel duct defining a gaseous-fuel intake; (b) an axial gaseous-fuel compressor having at least one or more compressor rotor stages, each having a rotor stage wheel with a plurality of compressor blades, disposed within the gaseous-fuel duct for compressing gaseous fuel; (c) one or more nozzles operatively associated with the gaseous-fuel duct to exhaust gases therefrom; (d) at least one annular chamber extending around the gaseous-fuel duct in the plane of said one or more rotor stages; (e) a turbine disposed in the at least one annular chamber comprising: (i) at least one turbine stator vane stage; and, (ii) at least one turbine rotor blade stage with at least one turbine blade operatively associated with each of the compressor blades of each of the compressor stages such that rotation of the turbine rotor stages causes rotation of the at least one pair of compressor rotor stages; (f) a source of liquid oxygen; (g) at least one pump for transporting the liquid oxygen from the source into the annular chamber so as to rotate the turbine rotor stage; (h) an oxygen exhaust from the annular chamber into the gaseous-fuel duct; and, (i) one or more injectors for directing the oxygen from the annular chamber for mixing with the compressed gaseous fuel.