Abstract: A turbine engine for aircraft includes a gas generator as well as to a receiver driven by a power turbine, and to an electric power generator, the rotor of which centered on a rotor axis distinct from the longitudinal axis, is driven into rotation by the power turbine, via a mechanical gear transmission, including a toothed drive wheel centered on the axis. Further the receiver includes a first propeller driven by a free power turbine and the toothed drive wheel is attached on an outer case of this power turbine.

Abstract: A turbomachine fan duct is disclosed. The fan duct includes two coaxial cylindrical walls, these being an internal wall and an external wall, respectively. The internal wall includes a framework to which panels are removably attached, and the external wall includes a single support structure with openings closed by removable panels. The openings in the external wall have dimensions that allow the panels of the internal wall to pass and allow these panels to be fitted onto and removed from the framework of the internal wall.

Abstract: In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.

Abstract: A twin-spool gas turbine turbojet comprising a high-pressure rotor; a low-pressure rotor; a low-pressure rotor shaft connected to a fan housed in a fan casing; and a fixed cowl element centered on the axis of the engine, upstream of the fan, on which there is mounted an electric current generator designed to take mechanical power off the low-pressure rotor shaft and convert it into electrical power.

Abstract: The present invention relates to a turbine engine for aircraft comprising a gas generator as well as to a receiver driven by a power turbine (34), and to an electric power generator (60), the rotor (62) of which centred on a rotor axis (62?) distinct from the longitudinal axis (2), is driven into rotation by the power turbine, via a mechanical gear transmission (80), comprising a toothed drive wheel (82) centred on the axis (2). Further the receiver comprises a first propeller driven by a free power turbine (34) and the toothed drive wheel (82) is attached on an outer case (40) of this power turbine (34).

Abstract: A turbine engine for an aircraft is disclosed. The engine includes a gas generator and a receiver driven by a power turbine. The receiver includes a propeller driven by a free power turbine provided with an outer case. The propeller includes a propeller case located radially outwards relatively to the outer case, and from which blades protrude radially outwards. The engine also includes an electric power generator. The rotor of the generator is centered on the longitudinal axis of the turbine engine, and is driven into rotation by the power turbine while being attached on the propeller case.

Abstract: The present invention relates to a turbine engine (100) for aircraft comprising a gas generator (14) as well as a receiver (30) driven by a power turbine (34, 38), this receiver comprising a propeller (32) driven by a free power turbine (34) provided with an outer case (40), the propeller (32) having a propeller case (46) located radially outwards relatively to the outer case (40), and from which blades (48) protrude radially outwards. According to the invention, it comprises an electric power generator (60), the rotor (62) of which centred on the longitudinal axis (2) of the turbine engine, is driven into rotation by the power turbine (34) while being attached on the propeller case (46).

Abstract: The invention relates to thrust reversers comprising at least one mobile element (3), at least one locking device (7) comprising a hook (8) cooperating with a hookable part (6) in order to keep the mobile element (3) in the closed position, and a double detection system (10) detecting closure and locking comprising a sensor (15) for indicating, in particular by a signal, if the mobile element (3) is in the closed position and if the device (7) is in a locked position. According to the invention, the double detection system detecting closure and locking of a mobile element of a turbojet thrust reverser comprises a means (16) of detection of the hookable part (6) and of activation of a second means (17) of detection of the crooked end (13) of the hook (8).

Abstract: The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and a power take-off module in direct mesh with the drive pinions, driving the transmission shafts. By virtue of the invention, the transmission shafts run coaxial with one another and therefore pass through a single arm. The use of a power take-off module simplifies the mechanism. The turbine engine is simpler to assemble.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.

Abstract: In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.

Abstract: The invention relates to a twin-spool gas turbine turbojet comprising a high-pressure rotor (1) and a low-pressure rotor, the low-pressure rotor shaft (2) being connected, at its upstream end, to a fan (10) housed in a fan casing (14), which turbojet comprises, upstream of the fan (10), a fixed cowl element (12) centered on the axis (X3) of the engine and on which there is mounted an electric current generator (20) designed to take mechanical power off the low-pressure rotor shaft (2) and convert it into electrical power.

Abstract: A system for cooling the lubricant of the speed reducer of an aircraft turboshaft-engine during high-speed flight and during low-speed taxying. The cooling system includes a radiator through which the lubricant flows. An air supply duct delivers cooling air over the radiator. An air discharge duct discharges the air into the exhaust nozzle of the engine. The air supply duct is fed by an arcuate air take-off slot disposed in the air intake of the engine. The air discharge duct is provided with a flap for slowing air flow through the cooling system, and with an ejector-mixer, which is fed by compressed air, taken from the engine compressor, for creating a Venturi effect to increase air flow through the cooling system when required.