Abstract: A mechanical speed reducer, in particular for a device for driving at least one wheel of an aircraft landing gear, this reducer including a first sun gear including external toothing, first planet gears meshed with the external toothing of the first sun gear, these first planet gears being carried by a first planet carrier, a stationary ring gear meshed with the planet gears, and second planet gears meshed with a ring gear and with an external toothing of said first planet carrier, these second planet gears being carried by a second planet carrier.

Abstract: A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.

Abstract: A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.

Abstract: An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Abstract: A propulsion assembly for an aircraft comprising at least two electric motors configured to be disposed in a wing of the aircraft and each comprising a rotor having a motor shaft movable about a motor axis, at least one propeller borne by a propeller shaft movable about a propeller axis and mechanically coupled to the motor shaft of the at least two electric motors, the propeller axis being perpendicular to the motor axis of the at least two electric motors.

Abstract: An oil recovery device for a reducer of an aircraft turbomachine, the device having a gutter extending around an axis and being intended to be arranged facing oil ejection means formed in a ring gear of the reducer of the turbomachine. The gutter can include at least one oil reception chamber which extends around the axis and which is open towards the axis so as to receive the oil coming from the oil ejection means. The reception chamber can be delimited by a first wall and a second wall arranged facing each other. The first wall can have an axial oil evacuation orifice and the second wall can have a radial dimension relative to the axis which increases increasingly along the axis towards the axial orifice, so as to allow oil ejected by the reducer to be conveyed to the axial orifice.

Abstract: A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.

Abstract: A pivot (14) with a longitudinal axis (Y) for a bearing of a mechanical reduction gear, comprising a first annular part (14a) including an axial passage (17) and a second annular part (14b) mounted around the first annular part (14a), the first annular part (14a) delimiting with the second annular part (14b) a lubrication circuit at least one oil inlet (20) of which opens out inwards of the first annular part (14a) into the axial passage (17) and at least one oil outlet (28) of which opens radially outwards of the second annular part (14b).

Abstract: A turbomachine includes a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing surrounding and coaxial with the first casing, and a drive shaft connected to the motor shaft. The driveshaft is also connected to at least two electric machines via a power transmission angle gear device housed in a housing. The electric machines being intended are configured to take or inject power on the motor shaft. The housing has a coupling surface to which the two electric machines are coupled.

Abstract: A pivot (14) with a longitudinal axis (Y) for a bearing of a mechanical reduction gear, comprising a first annular part (14a) including an axial passage (17) and a second annular part (14b) mounted around the first annular part (14a), the first annular part (14a) delimiting with the second annular part (14b) a lubrication circuit at least one oil inlet (20) of which opens out inwards of the first annular part (14a) into the axial passage (17) and at least one oil outlet (28) of which opens radially outwards of the second annular part (14b).

Abstract: A planet carrier for a speed-reducing unit with a planetary gear set is provided. The planet carrier generally includes a torque transmission part having a longitudinal axis and an annular cage extending about the axis and connected to one longitudinal end of the part. The cage may include two sides extending radially relative to the axis and connected by bridges, and seats extending axially between the flanks and configured to support planetary gears rotatably mounted about the seats. The curved members may include at least two corresponding bars each inclined relative to a longitudinal plane passing both through the axis and substantially through the corresponding bar.

Abstract: A planet carrier for a speed-reducing unit with a planetary gear set is provided. The planet carrier generally includes a torque transmission part having a longitudinal axis and an annular cage extending about the axis and connected to one longitudinal end of the part. The cage may include two sides extending radially relative to the axis and connected by bridges, and seats extending axially between the flanks and configured to support planetary gears rotatably mounted about the seats. The curved members may include at least two corresponding bars each inclined relative to a longitudinal plane passing both through the axis and substantially through the corresponding bar.