Integrated bypass turbojet engines for aircraft and other vehicles

A turbojet engine comprising a turbojet structure with an air intake, a common combustion gas and air ejection nozzle, a rotor disk unit having an air fan with internal compressor passages and radial discharge nozzles, a peripheral combustion chamber having a perforated air plenum wherein the air fan has side apertures proximate the radial discharge nozzles that supply compressed air from the compressor passages to the perforated air plenum, fuel injectors that inject fuel into the peripheral combustion chamber wherein air flow into the air intake divides to bypass air through the air fans and compressed air in the compressor passages that is discharged into the combustion chamber through the radial discharge nozzles and through the apertures and perforated air plenum, wherein the combustion chamber has a variable geometry discharge nozzle for discharging combustion gases into the bypass air for ejection with the bypass air from the common ejection nozzle.

A turbojet engine in a turbojet comprising a turbojet structure with an air intake, a common air and combustion gas injection nozzle, counter rotating air fan rotors each rotor having an air fan, an axial compressor with counter rotating compressor blades driven by the counter rotating air fan rotors, a combustion chamber with fuel injection, wherein compressed air from the compressor mixes with fuel to generate combustion gases, and a combustion gas ejection nozzle, wherein the turbojet structure has a bypass air flow from the air intake through the air fans of the air fan rotors and a compressed air flow through the compressor, the combustion gases from the combustion gas ejection nozzle mixing with the bypass air flow for ejection from the common air and combustion gas ejection nozzle.