A bearing housing for supporting a bearing of a gas turbine engine. The bearing housing comprises an annular body extending around an axis and having an oil inlet and an oil outlet. The bearing housing further comprises an oil manifold integrated into the annular body, the oil manifold having an inner oil channel defined in the annular body and extending circumferentially around the axis, the inner oil channel in fluid communication with the oil inlet and at least one oil jet directed towards the bearing.

A system is presented for directing the flow of cooling fluid in a rotational machine having co-axial rotatable shafts. The system comprises a first shaft rotatable about an axis, a second shaft rotatable about the axis and having a portion axially overlapping with the first shaft, and a fluid catcher. The fluid catcher is coupled between the first shaft and the second shaft. The fluid catcher comprises a first interface region interfacing with the first shaft, a second interface region interfacing with the second shaft, a fluid retention lip at least partly defining an oil capture region; and a body. The body is coupled to the oil retention lip and defines a channel in fluid communication with the oil capture region. The channel is positioned to direct fluid to one of the first interface region or the second interface region.

A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

The purpose of the present invention is to provide a slide component that can exhibit sealing performance and lubricity regardless of rotating direction. A pair of slide components 4, 7 that slide relative to each other have sliding faces S that slide relative to each other, and a sealed fluid-side periphery 16 and a leakage-side periphery 15. The sliding face S of at least one slide component 4 of the pair of slide components 4, 7 includes: a fluid introduction groove 13 in communication with the sealed fluid-side periphery 16; a first pressure generation mechanism 12 of which one end is in communication with the fluid introduction groove 13 and the other end is surrounded by a land portion R1; and a second pressure generation mechanism 11 of which one end is in communication with the leakage-side periphery 15 and the other end is surrounded by an annular land portion R2. The fluid introduction groove 13 and the other end 12e of the first pressure generation mechanism 12 include overlapping portions Lp overlapping circumferentially.

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.

A bearing assembly for a charging apparatus. The bearing assembly comprises a bearing housing and a shaft. The bearing assembly further comprises a compressor-side bearing bushing and a turbine-side bearing bushing which together support the shaft inside a bearing bore of the bearing housing. The bearing assembly is configured to supply unequal amounts of lubricant to a compressor-side outer lubrication gap of the compressor-side bearing bushing and to a turbine-side outer lubrication gap of the turbine-side bearing bushing. The bearing assembly is further configured to supply unequal amounts of lubricant to a compressor-side inner lubrication gap of the compressor-side bearing bushing and to a turbine-side inner lubrication gap of the turbine-side bearing bushing.

A fluid machine includes a rotating body, an operation body rotated integrally with the rotating body, a housing, hydrodynamic plain bearings rotatably supporting the rotating body relative to the housing, and a cooling passage arranged in the housing. The hydrodynamic plain bearings each include a resin coating layer at a portion that is opposed to the rotating body. The hydrodynamic plain bearings include at least one combination of hydrodynamic plain bearings. Each combination includes an upstream hydrodynamic plain bearing and a downstream hydrodynamic plain bearing located at different positions in a direction in which the fluid flows through the cooling passage. The coating layer of the upstream hydrodynamic plain bearing has a lower hardness than the coating layer of the downstream hydrodynamic plain bearing.

An enclosure for a turbomachine includes a turbomachine drive shaft rotating about a longitudinal axis (X) by means of two roller bearings, an upstream bearing and a downstream bearing, each having an inner ring carried by the drive shaft. The two bearings share a single integral outer ring that has an upstream end and a downstream end connected to one another by a section of studs. The single outer ring is carried by an upstream base plate and a downstream base plate of a bearing support configured to be attached to a stationary structure of the turbomachine.

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.

A parallel bearing includes a rotary shaft bearing and a stator bearing, wherein the rotary shaft bearing is a contact bearing, and the rotary shaft bearing is sleeved on a rotary shaft; and the stator bearing is a non-contact bearing, the stator bearing is sleeved on the rotary shaft bearing, and a clearance is provided between the stator bearing and the rotary shaft bearing. The parallel bearing is cost-effective, reduces the relative rotational speed of each stage of bearing, breaks through the limitation of the theoretical DN factor and has the low dependency on the lubricating oil. In the rotor system having the parallel bearing, rotational speeds of multiple parallel bearings on the same rotary shaft can be adaptively adjusted to achieve the synchronous rotation, and thus the rotor system has the desired stability in high-speed operation.