Methods and systems are provided for lubrication of a transmission. In one example, the transmission system may include a pair of shielded bearings attached to a first transmission shaft, each of the shielded bearings including at least one shield that forms a restriction between the shield and a race of the bearing and a cavity positioned axially between the pair of shielded bearings, wherein the restrictions tune lubricant pressurization in the cavity. The transmission system further includes a radial passage in the first transmission shaft in fluidic communication with the cavity and a lubricated transmission component.

A diffuser for an oil drainback system drain tube includes a flow chamber configured for attachment to an open end of a drain tube, wherein the flow chamber has a side wall and an end wall, and openings in at least the side wall.

A rolling-element bearing for a device lubricated with a fluid includes first and second bearing rings defining an interior therebetween in which rolling elements support the first ring for rotation relative to the second ring. A pumping device is located at the interior for pumping the fluid into and/or out of the interior when an element of the rolling-element bearing rotates and the rolling-element bearing is at least partially submerged in the fluid. The pumping device may be a ring having vanes that is attached to the first bearing ring or to a cage of the bearing.

Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.

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.

The present disclosure discloses an oil-lubrication mechanism for a fore bearing of a water-cooled electric motor and an electric-motor driving assembly, which solves the problems of conventional grease lubrication of the fore bearing of water-cooled electric motors such as serious bearing heat generation and bearing failure and low life caused by easy outflowing of the grease. The oil-lubrication mechanism includes a gear-splashing oil-storage structure provided in a gearbox or a reduction gearbox, and a bearing-baffle oil-storage structure provided at a front end of the water-cooled electric motor; and a gear in the gearbox or the reduction gearbox in operation throws a lubricating oil into the gear-splashing oil-storage structure, and the lubricating oil is delivered via the oil conduit into the bearing-baffle oil-storage structure, thereby lubricating the fore bearing of the water-cooled electric motor, and subsequently the lubricating oil flows back into the gearbox or the reduction gearbox via the oil return tube. In the present disclosure, the lubricating oil that splashes inside the gearbox or the reduction gearbox is introduced into the fore bearing of the water-cooled electric motor, which enables the fore bearing of the water-cooled electric motor to be lubricated by the oil, thereby reducing the heat generation of the fore bearing of the water-cooled electric motor, and improving the life of the fore bearing and the reliability of the electric motor.

The invention relates to a compressor (20) for generating a compressed air flow for a fuel cell (10), having a compressor element (21), in particular a compressor wheel, wherein the compressor element (21) is coupled in a to a drive shaft (23) for co-rotation, the drive shaft (23) being driven by a motor (22), in particular an electric motor, wherein at least one hydrodynamic or hydrostatic bearing (24, 25) is used to mount the shaft (23) in a rotatable manner, wherein the plain bearing (24, 25) is connected to a lubricant supply means (30), which is used to supply a lubricant for hydrodynamic or hydrostatic pressure generation to the plain bearing (24, 25), wherein the lubricant is water or a fluid mixture, predominantly comprising water, wherein the plain bearing (24, 25) has a lubricant inlet and a lubricant outlet, wherein the lubricant can be routed to the plain bearing (24, 25) via the lubricant inlet and the lubricant can be discharged from the plain bearing (24, 25) via the lubricant outlet, and wherein a discharge area of the circulation system (30) is disposed in the area of the lubricant outlet. An operationally safe design can be implemented for such a compressor if provision is made for the cross-section area of the outlet of the liquid outlet of the plain bearing (24, 25) to be completely covered by the lubricant held in the discharge area.

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.

A seal assembly and method of directing fluid flow away from a seal. The seal assembly comprises an inner seal member coupled to a rotatable shaft and an outer seal member which is either rotatable or static. The inner seal member has a plurality of knives spaced apart from each other and extending radially away from the shaft. The outer seal member has a rub surface disposed to abut a terminal edge of at least one of the plurality of knives to thereby form a seal. An outer knife of the plurality of knives of the inner seal member extends axially at an angle and is adapted to direct fluid flow away from the seal.

A unique compressor system may include a compressor having a compressor housing. The compressor housing may include an oil drainage passage formed therein. The passage may be configured to drain oil from bearings and other oil-lubricated components of the compressor. The compressor may be coupled to a gearbox or an oil tank. The gearbox or oil tank may include a passage that is in fluid communication with the oil drainage passage. The gearbox or oil tank passage may be operative to receive the drained oil and to direct the drained oil to an oil tank.