This invention discloses a hoisting sheave shaft, a hoisting sheave and a lubricating device thereof, where the hoisting sheave shaft is provided with a first oil injection channel extending axially; an oil inlet of the first oil injection channel is arranged on an end surface of the hoisting sheave shaft; the hoisting sheave shaft is also radially provided with at least one second oil injection channel; the second oil injection channel intersects with the first oil injection channel; and an oil outlet of the second oil injection channel is arranged on an outer circular surface of the hoisting sheave shaft.

A maintenance-free bearing system having self-lubricating features, seals, grooves and slots for use in a cushion hitch assembly for a hitch pull scraper vehicle. An interconnected bearing linkage system having two or more horizontal two-axis combined journal and thrust bearings with self-lubricating liners therein, two or more vertical single-axis sleeve bearings with self-lubricating liners therein and one or more vertical thrust bearing with self-lubricating liners therein, that cooperate with one another to accommodate vertical and horizontal angular movement relative to one another.

A turbo machine of the present disclosure includes a rotation shaft, a first bearing, a casing, an impeller, a first space, a second space, a storage tank, a first outlet passage, a supply passage, a pump, a main passage, and a sub-passage. The second space is in communication with a space formed between a bearing surface of the first bearing and an outer surface of the rotation shaft. The main passage is in communication with the second space and extends in the rotation shaft from an end of the rotation shaft in an axial direction of the rotation shaft. The sub-passage is formed in the rotation shaft and allows communication between the space between the bearing surface of the first bearing and the outer surface of the rotation shaft and the main passage.

A planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft, this planet-carrier having a rotation axis and comprising axes for guiding the planet gears that are arranged around and parallel with the rotation axis, each guiding axis having a general tubular shape of which the outer periphery comprises only two coaxial and adjacent cylindrical tracks of the respective rollers of two annular rows of rollers, wherein each axis has an inner periphery that is substantially bi-conical and comprising two coaxial and adjacent frustoconical surfaces, these inner frustoconical surfaces converging towards one another and extending respectively radially inside the tracks.

A lubricating oil distributor for a turbine engine mechanical reduction gear, for example of an aircraft, has an annular shape about an axis X and is formed of one single part. The distributor includes first and second independent oil circuits, the first oil circuit having a first oil inlet connected by a first annular chamber to several oil outlets distributed over a first circumference C1 about the axis X, and the second oil circuit having a second oil inlet connected by a second annular chamber to several oil outlets distributed over a second circumference C2 about the axis X, the first and second circumferences having different diameters.

A spur gear arrangement includes a spur gear, and two flange bushings configured to rotatably support the spur gear on a shaft, with each flange bushing including a flange. A lubricating film is provided between an inner side of the spur gear and each of the flange bushings. Two supporting bodies are arranged on the shaft, with the flange bushings being respectively arranged with their flange on the supporting bodies for axially bracing the spur gear.

An actuator of a variable compression ratio mechanism for an internal combustion engine includes an arm link 13 configured to change a posture of the variable compression ratio mechanism for the internal combustion engine by swinging, a second control shaft 11 fixed to the arm link 13, and a housing 20 including a first bearing hole 301a supporting the second control shaft 11. The housing 20 includes a lubricant oil supply oil passage 202 opened to a pressure-receiving range over which a contact pressure is received at the first bearing hole 301a from the second control shaft 11 during an expansion stroke of the internal combustion engine.

A plain bearing for a mechanical reducer for a turbomachine is integrally formed and includes a cylindrical body. The cylindrical body has an external cylindrical guide surface, a first axial mounting extension, a first circumferential edge extending around the first extension, a second axial mounting extension, and a second circumferential edge extending around the second extension. The plain bearing further includes an attachment cover connected to the first axial extension and extending axially opposite said first edge.

The invention relates to a planetary gearing (1) for a wind turbine, comprising a sun gear (3), a hollow gear (17), a planetary carrier (9) with a first bolt receiving element (10) having at least one first bolt seat (12), at least one planetary gear bolt (8) and at least one planetary gear (5). The bearing assembly (19) has a first planetary gear receiving bushing (20) and a second planetary gear receiving bushing (21), which planetary gear receiving bushings (20, 21) are coupled to the planetary gear (5) in a rotationally fixed manner, and between which planetary gear receiving bushings (20, 21) an axial bearing gap (25) is formed. The bearing assembly (19) has at least one bearing running sleeve (28), which is accommodated on the planetary wheel bolt (8) in a rotationally fixed manner, and on which an axial positioning flange (29) is formed, which is accommodated in the axial bearing gap (25) between the planetary gear receiving bushings (20), and an axial position fixing, in particular an axial bearing, of the planetary gear (5) on the planetary gear bolt (8) is thereby carried out.

A bearing bushing for a track has an annular shape including an inner peripheral surface, an outer peripheral surface, a first end face, and a second end face located axially opposite the first end face. The bearing bushing for a track includes an inner peripheral surface-side hardened layer formed to include the inner peripheral surface, an outer peripheral surface-side hardened layer formed to include the outer peripheral surface, a first end face-side hardened layer formed to include the first end face and having a region with a hardness of 63 HRC or more that has a thickness of 3 mm or more from the first end face, and an unhardened region lower in hardness than the inner peripheral surface-side hardened layer, the outer peripheral surface-side hardened layer, and the first end face-side hardened layer, and including at least the second end face. The bearing bushing is made of steel.