Abstract: A separator-diffuser for a gas turbine engine is disclosed wherein the diffuser includes axial walls which function as a guide vane stage for the oxidizer compressor. By incorporating the last, or downstream, guide vane stage into the diffuser structure, the overall axial length and bulk of the gas turbine engine may be significantly reduced. The separator-diffuser has a wall defining a generally annular oxidizer flow passage extending around the central axis of the gas turbine engine, the passage having an oxidizer inlet located downstream of the last rotor stage of the oxidizer compressor so as to enable the oxidizer to pass from the oxidizer compressor into the oxidizer flow passage. A generally annular separator member is located in the oxidizer flow passage downstream of the oxidizer inlet so as to divide the oxidizer flow passage into at least two separate oxidizer flow paths, each flow path having a separate oxidizer outlet.

Abstract: A turbopump system for pumping two separate fluids is disclosed having a r of concentric turbine rotors located within a turbine casing, each directly connected to a pump impeller. The centrifugal pumps, which may be located on opposite sides of the turbine casing are separately connected to their respective fluids such that the two fluids may be pumped simultaneously. A propellant fluid is directed through a generally annular space defined between the concentric turbine rotors to rotate them in opposite directions. Turbine blades attached to each of the turbine rotors extend into this annular space in order to drive the turbine rotors. The pitches of the turbine blades are such that the rotors are driven in opposite directions and one of the turbine rotors may be driven at a different speed than the other.

Abstract: A cooling system is disclosed including a drive shaft interconnecting a turbine rotor wheel with a compressor rotor wheel, a heat exchanger, and an auxiliary air compressor formed as part of the drive shaft which draws air from a portion of the compressor, through the heat exchanger and directs it onto portion of a gas turbine. The auxiliary air compressor may be a mixed-flow air compressor having a plurality of axial flow stages located upstream of a rotor portion with an impeller wheel to direct the cooling air onto portions of the gas turbine rotor and the stationary vanes. The heat exchanger may also be located externally of the gas turbine engine to improve the cooling of the cooling air before it is directed onto the gas turbine.