A bearing including a generally cylindrical sidewall including an electrically conductive substrate, and an electrically non-conductive or low-conductive sliding layer coupled to the substrate, where the generally cylindrical sidewall includes a plurality of protrusions protruding radially inward or radially outward from a bore defining a central axis, where at least one protrusion is adapted to contact an opposing component such that at a point of contact the bearing has a void area free of sliding layer so as to provide electrical conductivity between the bearing and the opposing component, and wherein at least one protrusion has a spring rate of not greater than 30 kN/mm, such as not greater than 25 kN/mm, such as not greater than 15 kN/mm, or such as not greater than 10 kN/mm.

A sintered bearing (1) contains as main components iron, copper, a metal having a lower melting point than copper, and a solid lubricant. The sintered bearing (1) includes a surface layer (S1) and a base part (S2). The surface layer (S1) is formed mainly of flat copper powder arranged so as to be thinned in a thickness direction. In the base part (S2), an iron structure (33) and a copper structure (31c) brought into contact with the iron structure are formed of partially diffusion-alloyed powder in which copper powder is partially diffused in iron powder. Thus, a sintered bearing which achieves a balance between wear resistance of a bearing surface and strength of the bearing, and realizes low cost can be provided.

A radial bearing apparatus including a housing with a housing bore defining a radial bearing housing surface, a shaft extending through the housing bore and defining a radial bearing shaft surface, and a radial bearing contact interface between the radial bearing housing surface and the radial bearing shaft surface for bearing a variable side force applied to the shaft. The radial bearing contact interface includes an oblique section in which the radial bearing housing surface and the radial bearing shaft surface are oblique to each other when the side force is zero and progressively increase in contact in an axial direction in response to an increasing magnitude of the side force.

A bearing for a gear pump includes a bearing body defining a bearing bore defined therethrough along an axis for receiving a gear shaft. The bearing bore defines a cylindrical bearing inner diameter surface. The bearing body defines an outer mating surface configured for mounting to another bearing body. A groove is defined in the inner diameter surface along an axial direction relative to the axis to provide clearance for gear journal motion between the inner diameter surface and the gear shaft. The groove is defined in a portion of the inner diameter surface opposite the mating surface.

Bearing 11 has base material 110 and coating layer 111. Base material 110 contains crank shaft 13 on an inner circumferential surface side. The inner circumferential surface of base material 110 is coated with coating layer 111. The inner circumferential surface side of base material 110 is coated with a resin with a thickness t, the resin is dried, and thereafter surface treatment is carried out such that multiple grooves C are provided on the surface of the resin so as to intersect with the direction of crank shaft 13, whereby coating layer 111 is formed. Peak portions B formed between adjacent grooves C come into contact with the outer circumferential surface of crank shaft 13 to support crank shaft 13. With bearing 11, the thickness of peak portions B at the center in the direction of the crank shaft 13 differs from the thickness of peak portions B at the end.

A track roller assembly includes a split inner ring, a split outer ring, a one piece inner ring and/or a one piece outer ring and a liner or plurality of rolling elements engaging therewith, the track roller assembly being disposed in a structure of an Airbus A-350 aircraft, an Airbus A-320 aircraft, an Airbus A320Neo aircraft, an Airbus A330 aircraft, an Airbus A330Neo aircraft, an Airbus A321 aircraft, an Airbus A340 aircraft, and an Airbus A380 aircraft.

A sintered bearing (1) contains as main components iron, copper, a metal having a lower melting point than copper, and a solid lubricant. The sintered bearing (1) includes a surface layer (S1) and a base part (S2). The surface layer (S1) is formed mainly of flat copper powder arranged so as to be thinned in a thickness direction. In the base part (S2), an iron structure (33) and a copper structure (31c) brought into contact with the iron structure are formed of partially diffusion-alloyed powder in which copper powder is partially diffused in iron powder. Thus, a sintered bearing which achieves a balance between wear resistance of a bearing surface and strength of the bearing, and realizes low cost can be provided.

A bushing may include a support surface and a sliding surface having a perimeter midpoint. The sliding surface of the bushing may have a convex profile in relation to a cross section of the bushing. The convex profile may be offset from the perimeter midpoint of the sliding surface of the bushing.

A connecting rod for an internal combustion engine may include a big end passage for receiving a pin journal of a crankshaft, a small end passage for receiving a piston pin, and a beam extending between the big and small end passages. The small end passage may extend along a passage axis and be delimited by opposed edges. The small end passage may include an inner passage surface with a cylindrical surface portion having a first diameter. The small end passage may extend along the passage axis between the opposed edges. The inner passage surface may comprise profiled regions adjacent to the opposed edges and extending at least over a part of a circumference of the opposed edges. The profiled regions may begin from the cylindrical surface portion and increase into a maximum second diameter at the opposed edges. Further, a plurality of dimples may be positioned along the cylindrical surface portion of the inner passage surface.

An actuation system for deploying and retracting a lift assisting device of a leading edge of a wing of an aircraft including a track pivotally coupled to the lift assisting device. The track has first and second outer surfaces and side surfaces. The actuation system includes a shaft rotationally coupled within the wing of the aircraft and operable, in response to flight control signals, to deploy or retract the lift assisting device. The actuation system includes an actuator for actuating the lift assisting device, coupled to the shaft, between a retracted position to a deployed position along an arcuate path. The actuation system includes a plurality of track roller bearings rotatably contacting the first and second outer surfaces of the track to guide the track along the arcuate path. The plurality of track roller bearings includes one or more lined track roller assembly.