The provided is a bearing device for a crankshaft of an internal combustion engine including: a crankshaft having a plurality of journal portions; main bearings for supporting the crankshaft; and a bearing housing, wherein a range in which the oil groove of the upper-side halved bearing of the second main bearing is formed in the circumferential direction includes at least a range of a circumferential angle of 20° within the ±45° region, a circumferential end portion of the oil groove on a rotationally forward side communicates with the crush relief at a minimum, and is open to a circumferential end face at a maximum, and a circumferential end portion of the oil groove on the rotationally backward side of the journal portion is positioned on a circumferential center portion side of the upper-side halved bearing from a circumferential end face of the upper-side halved bearing.

A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

A bushing for aircraft landing gear includes a cylindrical wall having an interior surface defining a bore extending between a first and second axial end thereof and a cylindrical recess extending into the interior surface. The bushing includes a cylindrical self-lubricating liner which is substantially flush with the interior surface is disposed in the recess. The cylindrical wall includes a flange that has an annular recess that receives an annular self-lubricating liner that has a planar axial bearing surface. The planar axial bearing surface is coplanar with an inboard axial surface of the flange. The bushing has an electrically conductive path that conducts electrical current and that extends around the cylindrical self-lubricating liner and the annular self-lubricating liner and through the cylindrical wall and the flange.

Disclosed herein is a sliding member having an alloy overlay layer that comes into sliding contact with a counterpart member thereof and has improved fatigue resistance. The sliding member comprises a base material layer and an alloy overlay layer formed on the base material layer, in which the alloy overlay layer has a soft metal phase made of tin and precipitated in a metallic matrix phase made of aluminum, and when an average aspect ratio of the soft metal phase is defined as A, and its standard deviation is defined as Aσ, A+Aσ is 3.0 or less. In this case, the soft metal phase has a shape close to a sphere without elongating in a certain direction.

The present invention provides a sliding member which enables further reduction of friction and improvement of seizure resistance without deteriorating wear resistance of a sliding surface. The sliding member includes a porous metal base material, and a resin material with which the porous metal base material is impregnated. The sliding member includes an exposed sliding surface. The sliding surface includes a top surface made of the resin material, and a bottom surface made of the porous metal base material. A height from the bottom surface to the top surface is 10 to 30 μm, and the resin material includes fluorine resin.

A metal foam ball, several millimeters in diameter, is manufactured to have an open-pore structure to absorb fluid (e.g., gas and liquid) such as water or lubricant. As an example, a copper foam ball is manufactured via a freeze casting method using prepared oxide powder slurry where a spherical silica gel mold is used to freeze the slurry, which is subsequently dried at low temperature in vacuum and then sintered at high temperature. For improved oxidation, copper alloy foam ball or copper foam ball coated with tin can also be manufactured through the same method. For improved strength, steel, copper-nickel alloy, or titanium foam ball can also be manufactured through the same method.

A Plain bearing having an outer ring and an inner ring, the outer ring and the inner ring providing respectively an inner surface and an outer surface intended to cooperate with each other for the relative movement of the outer and inner rings, the inner surface of the outer ring and the outer surface of the inner ring each including a coating including at least one layer. The hardness of the coating on the inner surface of the outer ring is less than the hardness of the outer ring, and the hardness of the coating on the outer surface of the inner ring is greater than the hardness of the inner ring.

A sintered bearing is made of a sintered compact containing nickel silver (Cu—Ni—Zn) as a base. In the sintered bearing, P is not added in the sintered compact. Alternatively, a content of P in the sintered compact is less than 0.05 mass % in terms of mass ratio to a total mass. Consequently, crystal grains constituting the sintered compact can be micronized. In particular, in the sintered bearing, an average crystal particle diameter of the crystal grains constituting the sintered compact is 20 μm or less. Consequently, the mechanical strength and the vibration resisting properties can be improved, and the rotation shaft can be prevented from being damaged.

The present invention relates to a mechanical system (1), comprising a bearing (4) and a shaft (10) coupled to the bearing (4), especially for an internal combustion engine, being subjected to average contact pressures of less than 200 MPa. The shaft (10) has at least one area (12) provided with an anti-seizing surface coating (20), having a surface hardness at least twice that of the bearing (4), and a microtexturation (30) comprised of a set of individual microcavities (31), distributed in said area (12). The invention also relates to a method for manufacturing such a mechanical system (1).

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.