An internal combustion engine, including a pair of opposed pistons, a pair of opposed cylinders, and an output shaft, wherein each of the pistons is arranged for reciprocating motion within a respective one of the cylinders, driven by combustion, and the pistons are coupled to the output shaft by a coupling such that said reciprocating motion of the pistons drives rotation of the output shaft, wherein the coupling includes a connecting rod coupled to the opposed pistons, and the coupling further includes a crankshaft rotatably mounted within a slider bearing, the slider bearing being formed of separable parts and having unitary sides for sliding contact within the connecting rod.

Provided is a sliding component having a low coefficient of friction and capable of exerting stable sliding characteristics from the initial stage of sliding, and a manufacturing method capable of easily manufacturing the sliding component. A sliding component (1) includes an iron substrate (10), in which graphite particles (13) are dispersed in an iron base (11), and a tin coating (20) formed on the iron substrate (10), the tin coating (20) including tin as a main material. The graphite particles (13) of the sliding component (1) are exposed through the tin coating (20). The manufacturing method includes: a preparation step of preparing an iron substrate (10) including graphite particles (13) dispersed in an iron base (11); and a film forming step of forming a tin coating (20) on the surface of the iron substrate (10), the tin coating (20) including tin as a main material. The film forming step forms the tin coating (20) so that the graphite particles (13) are exposed through the tin coating (20).

A torsion bushing includes a body portion defining a torsion rod-receiving bore, one or more helical flexion ribs defining at least a portion of the torsion rod-receiving bore, and a helical lubrication reservoir adjacent to the one or more helical flexion ribs. The torsion bushing may be included in a torsion busing assembly that further includes a bracket. The bracket may have a saddle to receive the torsion bushing, and one or more flanges for coupling the bracket to a frame. The torsion bushing may be included in a torsion rod assembly that further includes the bracket and a torsion rod.

A greaseless pivot center swivel and bearing device includes an outer housing having a sidewall with top and bottom portions, a top plate coupled with the top portion that includes an opening therein, and a bottom plate coupled with the bottom portion that includes an opening therein. The sidewall cooperates with the top and bottom plates to define an interior volume. A single, unitary bushing member formed of a low-friction material is positioned within the interior volume and includes a surface cylindrically curved about an axis extending between the top and bottom plates of the housing. The cylindrically curved surface cooperates with the openings in the top and bottom plates to define a cylindrical passage through the interior volume sized and shaped for receiving a cylindrical tube that rotates therein, e.g., a tube configured to connect with a water supply column of a mechanized irrigation system.

The invention relates to a tilting pad bearing for supporting a shaft having a longitudinal axis, the tilting pad bearing having—at least two tilting pads which are spaced apart from one another and each have a bearing surface and—at least one hot oil drainer which is arranged in an intermediate space between the at least two tilting pads, the at least one hot oil drainer being supported so as to be movable in the direction to and from the shaft.

A diffuser for an oil drainback system drain tube includes a flow chamber configured for attachment to an open end of a drain tube, wherein the flow chamber has a side wall and an end wall, and openings in at least the side wall.

An assembly is provided for a turbine engine. This turbine engine assembly includes a journal bearing and a filter. The journal bearing has an internal bearing bore. The filter is arranged within the internal bearing bore. The filter includes a tubular filter element and a first end cap. The tubular filter element extends axially along an axis between a first end and a second end. A perforated portion of the tubular filter element is radially disposed away from the journal bearing by a cavity. The first end cap is mounted to the tubular filter element at the first end. The first end cap is sealed radially against the journal bearing by a first interference fit.

A semi-floating bearing (multilobe bearing) including: an annular main body through which a shaft is inserted; and a radial bearing surface formed on an inner peripheral surface of the main body, the radial bearing surface including a plurality of arc surfaces having different curvature centers and disposed adjacent to each other in a circumferential direction of the main body, and a minimum distance Ra between a central axis of the shaft and the arc surface, a curvature radius Rb of the arc surface, and a radius Rs of the shaft satisfying relationships expressed by the following Formulas (1) and (2). Ra/Rs≥1.001 . . . (1), (Rb−Ra)/0.9≤(Rb−Rs)≤(Rb−Ra)/0.6 . . . (2) provided that Ra is the minimum distance between the central axis of the shaft and the arc surface, Rb is the curvature radius of the arc surface, and Rs is the radius of the shaft.

An aircraft landing gear includes a landing gear provided with a yoke supporting a spindle on which is mounted a capture pin to be hooked by a hook of a locking box to be mounted on a structure of an aircraft to immobilize the landing gear in a given position with respect to the structure. The capture pin includes a body provided with a longitudinal opening enabling the capture pin to be mounted on the spindle, and an outer surface of revolution having a central portion having a convex profile to cooperate with the hook. A central portion of the outer surface is formed on a central ring which is mounted so as to rotate freely on a central portion of the body.

An aircraft landing gear includes a landing gear provided with a yoke supporting a spindle on which is mounted a capture pin to be hooked by a hook of a locking box to be mounted on a structure of an aircraft to immobilize the landing gear in a given position with respect to the structure. The capture pin includes a body provided with a longitudinal opening enabling the capture pin to be mounted on the spindle, and an outer surface of revolution having a central portion having a convex profile to cooperate with the hook. A central portion of the outer surface is formed on a central ring which is mounted so as to rotate freely on a central portion of the body.