Variable cycle propulsion engine for supersonic aircraft

A variable cycle turbojet propulsion engine, particularly for supersonic aircraft, comprising:

• a primary unit including a compressor, a combustion chamber, a turbine, a common shaft interconnecting said compressor and said turbine whereby said compressor is driven by said turbine, and an exhaust assembly having at least one adjustable section nozzle, an annular outer casing surrounding said primary unit and defining therebetween an annular cold flow secondary duct, an air intake at the upstream end of said outer casing, a secondary adjustable section exhaust nozzle at the downstream end of the said outer casing, and a compression fan assembly disposed in said secondary duct, said fan assembly including at least one stage of movable rotor blades rigidly connected to said shaft of said primary unit so as to be driven thereby, a stage of fixed inlet guide vanes on the upstream side of said rotor blade stage, a stage of fixed flow straightener vanes on the downstream side of said rotor blade stage, a first adjuster for adjusting the pitch of said inlet guide vanes, and a second adjuster for adjusting the pitch of said fixed flow straightener vanes.