Abstract: A variable cycle propulsion unit comprises at least two turbojet engines of the bypass type in which the low pressure compressor of each engine is in two parts connected by a shaft, and the flow of compressed air issuing from the first part of the low pressure compressor of a first of the engines is supplied to the second part of the low pressure compressor of a second of the engines and the flow of compressed air issuing from the first part of the low pressure compressor of the second engine is supplied to the second part of the low pressure compressor of the first engine. At full throttle operation the combustion chambers of the two engines are both ignited, and at operation at reduced engine speeds the combustion chamber of one of the engines is extinguished and the engine windmills while the other engine continues to run normally.

Abstract: The invention relates to a propulsion engine, particularly for supersonic aircraft. An internal propulsion system comprises an envelope displaying a tapered center portion, around which is coaxially mounted an external propulsion system which lacks a separate compressor. According to the invention, mechanisms are provided to divert toward the combustion chamber of the external propulsion system an adjustable fraction of the compressed air arriving from the last compressor stage of the internal propulsion system. A blower which is driven by the external turbine exhausts in parallel with the latter into an annular conduit which emerges between the internal nozzle and external nozzle and an exhaust nozzle, all of these nozzles being of variable geometry. The purpose of the invention is to improve variable cycle propulsion engines for second-generation supersonic aircraft.

Abstract: A variable volume gas generator for charging a self-contained power turbine having heat engines for generating hot compressed gases including a first and second module each forming motor for the production of the hot compressed gases, a third module connected to the first and second modules and which forms an air compressor to charge the heat engines, the modules comprising a fixed housing delimiting an annular space, a plurality of pistons which rotate in the same direction noted in the annular space, wherein four of the pistons are mounted in each module, first and second rods diametrically connecting the pistons in pairs and being further propelled by a cyclical speed variation which causes a volume variation in the space delimited by the radial surfaces of the pistons, a first and second shaft which are coaxial wherein the first rod of each module is mounted on the first shaft and the second rod of each module is mounted on the second shaft such that single connecting rod mechanism rotors of the modules h

Abstract: An internal combustion rotary volumetric motor operating on a four stroke cycle including a fixed exterior housing which delimits an annular space, a plurality of pistons that rotate in the same direction mounted in the annular space, a rod having a shaft integral therewith diametrically connecting the pistons in pairs and propelling the pistons by cyclical speed variation which causes a volume variation in the space delimited by radial surfaces of the pistons, the spaces between the pistons forming chambers of the motor operating on a four stroke cycle, a rotary crown having a plurality of ports formed therein, wherein the annular space within which the pistons move is delimited by the housing and the rotary crown having the ports through which the rods are engaged and which provide an angle of clearance for the rods for advancing and receding of the pistons, the rotary crown forming part of an outlet motor shaft, and a transmission mechanism attaching the rotary crown to the shafts.

Abstract: An optimized propulsion system for aircraft whose flight range extends over wide range of speeds. It comprises an outer turbojet engine and an inner turbojet engine housed within a single engine nacelle and arranged concentrically, the outer turbojet engine extending axially and around a narrow portion of the casing of the inner turbojet engine. The invention may be used in the field of variable-cycle engines, and particularly in the field of supersonic transport aircraft.