Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet including a gas generator, a first unducted propeller connected to a shaft of the gas generator via first reduction gearing, and a second unducted propeller connected to a shaft of the gas generator via second reduction gearing, wherein the first propeller and the first reduction gearing are mounted at the front of the gas generator, and wherein the second propeller and the second reduction gearing are mounted at the rear of the gas generator.

Abstract: A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.

Abstract: A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.

Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

Abstract: A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.

Abstract: A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, is disclosed. The shaft includes an external portion that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade in order to adjust its pitch, and an internal portion, independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing in order to pivot the shaft about a radial axis, and to close an oil enclosure in which the bearing is housed, the external and internal portions of the shaft being coupled to each other. A method of mounting such a shaft and a control device including such a shaft are also disclosed.

Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.

Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet comprising a gas generator (3-8), a first unducted propeller (21) connected to a shaft (81) of the gas generator (3-8) via first reduction gearing (23), and a second unducted propeller (91) connected to a shaft (81) of the gas generator (3-8) via second reduction gearing (93), wherein the first propeller (21) and the first reduction gearing (23) are mounted at the front of the gas generator (3-8), and wherein the second propeller (91) and the second reduction gearing (93) are mounted at the rear of the gas generator (3-8).

Abstract: A reduction gear having an epicyclic gear train for a turbine engine, in particular of an aircraft, comprising: a planetary shaft having an axis of rotation A; a ring gear having an axis A extending around said planetary shaft; planet gears distributed around said axis A, which mesh with said ring gear and the planetary shaft; and a planet carrier including members for supporting bearings of the planet gears, having axes of rotation B, which are evenly distributed around the axis A, as well as a part holding each supporting member substantially by the middle thereof along the axis B thereof, wherein said supporting members are made as a single part having means for supplying lubricating oil to said bearings. A method for assembling said reduction gear is also provided.

Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

Abstract: A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.

Abstract: The invention relates to a radial control shaft (48) for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, the shaft comprising an external portion (52) that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade (26) in order to adjust its pitch, and an internal portion (50), independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing (40) in order to pivot the shaft about a radial axis (Z-Z), and to close an oil enclosure in which said bearing is housed, the external and internal portions of the shaft being coupled to each other. The invention also relates to a method of mounting such a shaft and to a control device including such a shaft.

Abstract: Propulsion assembly, comprising a turbine engine surrounded by a nacelle comprising an annular air inlet lip, the propulsion assembly further comprising a circuit for lubricating elements of the turbine engine and a circuit for de-icing the air inlet lip, characterised in that said de-icing circuit comprises a heat exchanger comprising a primary circuit of oil supplied by said lubrication circuit and a secondary circuit of a heat transfer fluid for supplying at least one de-icing channel extending into said air inlet lip, said de-icing circuit further comprising a pump for circulating the heat transfer fluid into said at least one channel.