A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a planet gear carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. Each planet gear is rotatably mounted in the planet gear carrier. The planet gear carrier comprises a plurality of axles arranged parallel to the axis of the gearbox. The axially spaced ends of each axle are secured to the planet gear carrier. Each planet gear is rotatably mounted on a corresponding one of the axles by a bearing arrangement. Each bearing arrangement comprises a journal bearing and a rolling element bearing and each planet gear is rotatably mounted on a journal bearing and each journal bearing is rotatably mounted on an axle by at least one rolling element bearing.

A free-wheel comprising a driving part and a driven part that are able to rotate about an axis of rotation, the free-wheel comprising at least one rotational connecting member arranged in a connection space, a driven connection section of the driven part surrounding a driving connection section of the driving part, the connection space being located radially, with respect to the axis of rotation, between the driving connection section and the driven connection section. The free-wheel comprises at least one barrier, the geometry of which varies depending on the speed of rotation of the driving part, arranged radially between the driving part and the driven part and longitudinally against the connection space, the barrier being constrained to rotate with the driving connection section.

A oil supply unit includes an axial body including an axial through hole along an axis and disposed so as to be rotatable around the axis, a pipe member disposed along the axis inside the axial through hole, a support member supporting an axial end of the pipe member, and a partitioning member partitioning a circular space between the axial body and an the pipe member to an axial direction. A first through hole and a second through hole are respectively formed to penetrate the pipe member and the axial body so that an oil supplied to an inside of the pipe member flows to a radial outside of the axial body through the circular space, and the partitioning member includes a tapered portion extending toward a radial inside and the axial direction of the axial body from the inner circumferential surface of the axial body.

A crank assembly for displacing a load includes a motor and a displacement arm assembly. The motor includes a rotatable output shaft that defines a rotation axis. The displacement arm assembly includes a swingable crank arm and a support roller bearing. The swingable crank arm is coupled to the output shaft to swing about the rotation axis when the output shaft rotates. The swingable crank arm defines a pivot end adjacent the rotation axis and an opposite displacement end. The support roller bearing is rotatably supported on the swingable crank arm proximate the displacement end. The support roller bearing is configured to engage the load. The support roller bearing defines a bearing axis, which is substantially parallel to and offset from the rotation axis.

A bearing assembly includes at least two bearings each having an inner ring and outer ring, the inner rings being mounted on a shaft, and a balancing piston being disposed between the two bearings. The balancing piston includes a first part and a second part, the first and second parts each contacting the outer rings of the two bearings in an axial direction. The balancing piston further includes an inlet for directing a pressure fluid between the first and second parts to provide pressure to the first and second parts such that the balancing piston adjusts or exerts axial force on at least one of the two bearings. The balancing piston includes an outlet for directing the pressure fluid to lubricate at least one of the two bearings. Also, the outer diameter of the balancing piston is greater than the outer diameter of the outer rings of the two bearings.

Devices for distributing oil from a rolling bearing for an aircraft turbine engine include a rolling bearing including two rings, respectively an inner ring and an outer ring, an oil distribution ring configured to be mounted on a turbine engine shaft, said distribution ring including a first outer cylindrical surface for mounting the inner ring of the bearing, an oil recovery scoop supplying a lubricating circuit of the bearing, and an annular track of a dynamic seal. The distribution ring and the track are formed by a single-piece body, and the lubricating circuit is formed in said body and extends into the distribution ring and the track.

An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.

Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said body comprising: i) a first outer cylindrical surface (5a) for mounting the inner ring (12) of the bearing, ii) a ring-shaped scoop (11) for recovering oil, iii) a ring-shaped track (26) of a dynamic seal (22), iv) a circuit (7) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop (11a) which supplies a first portion (7x) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop (11b) for recovering oil, which scoop supplies a second portion (7y) of the circuit with a view to lubricating the bearing.

Rolling-element bearing for a turbomachine of an aircraft, comprising an inner ring (3) defining a first raceway (112), and an outer ring (4) defining a second raceway (124), characterized in that the bearing has at least one loop circuit (21, 22) for forced recirculation of lubricant, this loop circuit comprising a first recirculation circuit (21) comprising at least one lubricant inlet (1200) located on the second raceway (124), and connected by at least one duct (120, 166) created in the outer ring (4) to at least one lubricant outlet (1661) which discharges into a second recirculation circuit (22) of the loop circuit (21, 22), this second recirculation circuit (22) comprising at least one duct (152, 1134, 1136; 1135, 1136) created in the inner ring (3).

Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: - a rolling bearing (8), an oil distributor ring (5) and - an annular track (26) of a dynamic seal (22), characterised in that it further comprises a nut (16) screwed on to a thread (5d) of the distributor ring and bearing axially against an axial end of the inner ring so as to clamp it axially, and in that the annular track is configured to bear axially against the distributor ring and comprises rotating locking elements (27) engaging with the additional elements (28)of the nut.