The invention relates to a wind turbine gearbox (1) having at least one gearwheel (2) which is mounted on an axle (5), wherein a bearing point with a plain bearing (4) is arranged between the gearwheel (2) and the axle (5), and wherein, in the axle (5), there is formed a recess for the supply of a lubricant to the plain bearing (4). In the region of a contact surface of the plain bearing (4), a groove (18) is formed in the gearwheel (2) or an intermediate space (7) is formed between the plain bearings (4), which groove or intermediate space is connected via at least one connecting line (16) to the surrounding atmosphere.

The present disclosure relates to a mechanical assembly of two mechanical parts rotatable relative to each other and enabling a self-centering fluid bearing to be obtained; it comprises a first part provided with a cylindrical cavity, a second part (34) having at least one cylindrical portion engaged in the cylindrical cavity of the first part, a gap separating the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement in rotation between the first part and the second part (34), and a lubricant distribution network (37, 38) configured for feeding said gap with a fluid lubricant so as to form a fluid bearing; a first surface (34s) selected from the inside surface of the cylindrical cavity of the first part and the outside surface of the cylindrical portion of the second part is provided with at least two lubricant admission orifices (39a, 39b) that are spaced apart from each other by not less than 120° about the main axis (F) of the first surface (34s), and the first surface (34s) also presents at least one circumferential groove (40a) extending circumferentially from the vicinity of a first lubricant admission orifice (39a) over at least 100° and in the direction of rotation of the second of said surfaces relative to the first surface (34s).

A product may be provided for use with a turbocharging system. A housing may be configured to house a bearing. A shaft may extend through the bearing. A turbine wheel may be connected to one end of the shaft. The housing may include a wall forming an opening and defining a surface facing the opening. The bearing may have a segment extending into the opening and mating with the surface. The wall may include an oil spray groove opening through the surface and having an outlet directed at the shaft.

A half thrust bearing for a crankshaft of an internal combustion engine is formed of a back metal layer and a bearing alloy layer to have a slide surface and two thrust reliefs. Each thrust relieve includes a first region, where the back metal layer is exposed, on a circumferential end surface side, and a second region and a third region, where the bearing alloy layer is exposed while the slide surface includes a fourth region. A circumferential end region consists of the first and second regions. The bearing alloy layer includes a uniform thickness portion, and a decreased thickness portion adjacent to an inner-diameter-side end surface in a cross-section of the second region and includes a uniform thickness portion and an increased thickness portion adjacent to the inner-diameter-side surface in cross-sections of the third and fourth regions.

A half thrust bearing for a crankshaft of an internal combustion engine is formed of a back metal layer and a bearing alloy layer to have a slide surface and two thrust reliefs. Each thrust relieve includes a first region, where the back metal layer is exposed, on a circumferential end surface side, and a second region, where the bearing alloy layer is exposed, on the slide surface side while the slide surface includes two third regions adjacent to the second region, and a fourth region between the two third regions. A circumferential end region consists of the first, second and third regions. In the second region and the third regions, the bearing alloy layer includes a uniform thickness portion at a radial center, and a decreased thickness portion adjacent to an inner-diameter-side end surface.

A bearing structure has a crankshaft rotatably supported by a crankshaft bearing part, formed of a cylinder block of an internal combustion engine and a first bearing cap, through a bearing metal, a second shaft rotatably supported by a second shaft bearing part formed of the first bearing cap and a second bearing cap, wherein the bearing metal has a bearing metal planar portion for rotatably supporting the crankshaft with an entire inner peripheral surface of the bearing metal, the inner peripheral surface at which the bearing metal planar portion is formed, a bearing metal oil groove portion formed with an oil groove formed to extend circumferentially in an inner peripheral surface of the bearing metal, the inner peripheral surface at which the bearing metal oil groove portion is formed, a first oil hole opening at the oil groove, and a second oil hole opening at the oil groove.

A seal assembly including at least one conduit configured to allow a medium to flow therethrough, an annular retaining means operably coupled to the conduit, and an annular resilient seal member disposed in the annular retaining means. A method of sealing a dispensing system containing a food product creating a food product pressure, wherein the dispensing systems includes a drive shaft operably coupled to a seal assembly, the seal assembly including an annular resilient seal member disposed in an annular retaining member, the annular retaining member being operably coupled to at least one conduit, the method including the steps of: dispensing a medium through the at least one conduit to enter the annular resilient seal member to create a seal pressure greater than or equal to the food product pressure.

A hydrostatic bearing assembly for a shaft is disclosed, which consists of a base ring, two side rings enclosed up the base ring at both sides, and a plurality of hydrostatic blocks fixed respectively on surfaces of the base ring and of the side rings corresponded to the shaft, as result to hold the shaft to resist against loadings from the axial direction and/or the radial direction and provide lubrication through oil passages inside. These hydrostatic blocks are locked with screws or bolts on the base ring and on the side rings in order to be replaced individually on site.

A thrust washer is provided with a ring-shaped portion that surrounds an insertion hole, the thrust washer is provided with a sliding surface and an oil groove configured to allow lubricating oil to flow in, the oil groove is provided with an opening portion configured to allow the lubricating oil to flow in from the insertion hole side in an inner peripheral end side, an outer periphery end side of the ring-shaped portion of at least one of the oil groove is provided with an oil stop wall which is configured to suppress flow of the lubricating oil toward an outer periphery side of the ring-shaped portion, and a sliding area ratio of each of the sliding surfaces to a projection plane in plan view of the ring-shaped portion is provided within a range of from 60% to 85%

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.