The invention relates to a pivot pin (5) for an epicyclic gear train sliding bearing, the pivot pin having a portion (23) forming a central shank, extending around an axial passage (15), and axially opposed, axially open circumferential grooves (25a,25b) which radially separate two axially opposed lateral end portions (230a,230b) of the central shank from two cantilevered lateral portions (27a,27b). With respect to a plane (33) perpendicular to said axis of the axial passage (15) and passing through the axial middle of the axial passage, the axial distance between said plane (33) and the bottom end of one of the circumferential grooves (25a) is smaller than the axial distance between said plane and the bottom end of the axially opposed circumferential groove (25b).

A pivot for a sliding bearing of an epicyclic train includes an annular wall delimiting an axial passage, the annular wall including a first and a second annular groove opening axially in opposite directions and each defined by two coaxial inner and outer annular branches formed at the axial ends of the annular wall. The pivot also includes a plurality of first holes opening at a first end into the first annular groove and at a second opposite end into the second annular groove, these holes being made over an angular sector of between 5° and 330°.

A sliding bearing for a gearbox of a wind turbine, having a support body and a sliding layer which is applied on the support body, and on which a sliding surface is formed, wherein a lubricant distribution groove extending in an axial direction of the sliding surface is formed on the sliding surface. The support body is formed as a bush rolled from a support body strip, wherein a first longitudinal end and a second longitudinal end of the support body strip are connected to one another in a materially bonded manner, in particular by a welding connection, at a joint, wherein the joint is formed in the region of the lubricant distribution groove.

A sliding bearing for a gearbox of a wind turbine, having a support body and a sliding layer which is applied on the support body, and on which a sliding surface is formed, wherein a lubricant distribution groove extending in an axial direction of the sliding surface is formed on the sliding surface. The support body is formed as a bush rolled from a support body strip, wherein a first longitudinal end and a second longitudinal end of the support body strip are connected to one another in a materially bonded manner, in particular by a welding connection, at a joint, wherein the joint is formed in the region of the lubricant distribution groove.

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.

A journal shaft for a journal bearing assembly of an aircraft engine includes a shaft body extending along a longitudinal axis. The shaft body has a radially outer surface and a radially inner surface radially spaced apart from the longitudinal axis to define an inner cavity. An oil pocket is defined in the radially outer surface. One or more passages extend through the shaft body from the radially inner surface to the oil pocket to provide fluid communication between the inner cavity and the oil pocket. The oil pocket includes a radially inner base surface and interconnecting transition surfaces extending between the radially inner base surface of the oil pocket and the radially outer surface of the shaft body. The interconnecting transition surfaces form a fluid-dynamically smooth and edgeless transition to the radially outer surface of the journal 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, 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.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between a bearing inner side and a bearing outer side. The journal bearing includes a bore, a passage, a groove and a slot. The bore extends axially within the journal bearing and along the bearing inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove extends longitudinally within the journal bearing at the bearing outer side between a groove first end and a groove second end. At least a portion of the slot extends circumferentially about the axis within the journal bearing at the bearing outer side from the groove first end to the groove second end.

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.

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.