SAFRAN TRANSMISSION SYSTEMS

An oil collector for a mechanical reduction gear of a turbomachine includes a body having two opposing side surfaces each configured to extend partly around a planet of said reduction gear, and an internal cavity for oil circulation. The collector also has at least one tongue removably mounted on the body, the tongue extending from the body in the extension of at least one side surface and intended to be at least partially engaged in an annular groove of a sun gear of the reduction gear.

A plain bearing for an aircraft turbomachine, the plain bearing having a tubular body including an outer cylindrical surface, an inner cavity designed to contain oil, a primary lubrification groove formed by a middle portion of the outer surface and a main channel for supplying the primary groove with oil, the plain bearing wherein the outer surface of the body further includes at least one secondary lubrification groove which is formed in an end portion of the outer surface and is independent of the primary groove, and in that the body further includes a secondary channel for supplying the or each secondary groove with oil.

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.

A speed reducer for a turbomachine for an aircraft, of longitudinal axis X, the speed reducer including an external ring gear and a ring gear carrier attached to the external ring gear which comprises a first attachment flange extending radially outwards and attached to a second attachment flange of the ring gear carrier by attachment members. The turbomachine including a gear coupling with axial coupling teeth including a first series of teeth engaging with a second series of complementary teeth, a portion of the first attachment flange including a portion of the gear coupling, the attachment members being arranged so as to clamp the first and second attachment flanges and circumferentially hold each axial tooth of the first series of teeth between two axial teeth of the second series of complementary teeth.

A lubrication wheel for a speed reducer of a turbomachine, including an annular oil passage cavity which extends around the axis, an annular slot for supplying the cavity, and pipes for the passage of oil by centrifuging from the cavity into the pipes, and a frustoconical rim for collecting oil at the level of the slot, the wheel being formed by the assembly of at least two parts.

An aircraft turbomachine includes a speed reduction gear having an input pinion connected to a power shaft and an output pinion connected to a propeller shaft. An electric machine is integrated into the speed reduction gear and is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft. The electric machine has a rotor driven in rotation about an axis coaxial with a longitudinal axis of the turbomachine and a stator connected to a casing. The input pinion includes an input shaft offset from an axis of the output pinion, and the speed reduction gear has two parallel intermediate transmission lines configured to transmit the torque from the input pinion to the output pinion to drive the rotor in rotation.

A circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules including an annular peripheral module and a circular central module.

The invention relates to a turbomachine assembly ( 1 ) extending around a longitudinal axis and comprising a speed reduction gear ( 16 ) having an external ring gear ( 23 ) and a gutter ( 41 ) for recovering a lubricant ejected by centrifugal effect, the gutter ( 41 ) being arranged around the external ring gear and comprising an area ( 43 ) for collecting the lubricant received by ejection. According to the invention, the gutter ( 41 ) is secured in terms of rotation to the external ring gear and in that the assembly comprises a device ( 50 ) for evacuating the lubricant to the outside of the collection area ( 43 ), the evacuation device being intended to be connected to a stator of the turbomachine and extending at least partly into the collection area, the evacuation device being configured so as to evacuate the lubricant located in the collection area to an oil evacuation area located outside the gutter.

A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.

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.