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.

To provide a rolling bearing having a hard film on an inner ring raceway surface and an outer ring raceway surface of the rolling bearing that improves peeling resistance of the hard film, shows the original property of the hard film, and suppresses the attackability to a mating material. A rolling bearing 1 has an inner ring 2 having an inner ring raceway surface 2a on an outer circumference, an outer ring 3 having an outer ring raceway surface 3a on an inner circumference, and rolling elements 4 that roll between the inner ring raceway surface 2a and the outer ring raceway surface 3a. A hard film 8 includes a foundation layer formed directly on the inner ring raceway surface 2a or the outer ring raceway surface 3a and mainly formed of Cr and WC, a mixed layer having a gradient composition formed on the foundation layer and mainly formed of WC and DLC, and a surface layer formed on the mixed layer and mainly formed of DLC. In a roughness curve of a surface on which the foundation layer is formed, the arithmetical mean roughness Ra is 0.3 μm or less and the root mean square gradient RΔq is 0.05 or less.

Provided are bearing assemblies including one or more substrate assemblies, such as thrust bearing assemblies. The substrate assemblies include a bearing element fixed to a substrate. The bearing elements are formed from a thermally stable material such as a ceramic-bonded diamond composite. Methods for manufacturing the bearing assemblies are also provided.

A method for machining ribs or grooves on a workpiece such as a shaft or an air or gas axial bearing intended to be rotated about a longitudinal axis of a centrifugal compressor. All of the ribs or grooves are obtained at once by the machining tool on a workpiece portion driven such that it rotates, by moving the workpiece or the tool holder in a longitudinal machining direction, the machining tool moving back and forth with a machining position in contact with the workpiece and a position wherein it is not in contact with the workpiece from the start to the end of the workpiece portion. The back-and-forth movements of the machining tool are synchronised with the sinusoidal program set up in the machining unit, as well as with the desired, programmed arrangement of the ribs or grooves to be produced on the workpiece portion.

Embodiments disclosed herein relate to bearing assemblies and methods of manufacturing. In an embodiment, a bearing assembly includes a support ring and bearing elements. The bearing elements are mounted to and distributed circumferentially about an axis of the support ring. At least one of the bearing elements includes a polycrystalline diamond table, a substrate bonded to the polycrystalline diamond table, bonding region defined by the substrate and the polycrystalline diamond table, and a corrosion resistant region. The corrosion resistant region includes a corrosion resistant material that covers at least a portion of at least one lateral surface of the bonding region. The corrosion resistant region prevents corrosion of at least some material in the bonding region covered by the corrosion resistant region (e.g., during use). Other embodiments employ one or more sacrificial anodes as an alternative to or in combination with the corrosion resistant region.

A propeller blade comprises a fibre reinforced blade structure spar having a blade retention section formed at one end thereof, and at least one metallic formation spray deposited onto said blade retention section.

Among other things, a bearing assembly comprising a hybrid coating is provided. A bearing assembly may comprise a substrate having a surface and a hybrid wear resistant coating over the surface of the substrate. In an example, the substrate may be an inner radial bearing and/or and outer radial bearing within a bearing assembly. The hybrid wear resistant coating may comprise a high wear resistant coating and a low wear resistant coating. The high wear resistant coating may comprise a wear resistant matrix over the surface and a set of wear resistant elements within the wear resistant matrix. In an example, wear elements within the set of wear elements may comprise tungsten carbide. The low wear resistant coating may be over a low wear area of the surface. In an example, the low wear resistant coating may be positioned between the first high wear resistant coating and a second high wear resistant coating.

The present disclosure provides a bearing design that accommodates misalignment of a rotatable shaft in the bearing and is well suited to usage in a particulate-laden fluid. The bearing can be shaped with a curved surface along a longitudinal axis of the bearing, such as in a curved barrel shape or a ball shape, to provide a point contact instead of a line contact as is the case with conventional plain bearings. The point contact allows the bearing to adjust with a misalignment between ends of the shaft or between the external supports and facilitates the assembly and disassembly of the rotating shaft. Because the bearing compensates for misalignment, the bearing surfaces can have closer tolerances for a smaller gap between the bearing surfaces, which can result in improved performance.

Bearing assemblies, apparatuses, and motor assemblies using the same are disclosed. In an embodiment, a bearing assembly may include a plurality of superhard bearing elements distributed circumferentially about an axis. Each of the superhard bearing elements may include a bearing surface. The bearing assembly may also include a support ring structure having a support ring that carries the superhard bearing elements. The support ring structure may include at least one erosion resistant region exhibiting a higher erosion resistance than another region of the support ring.

Embodiments disclosed herein relate to bearing apparatuses including a bearing assembly having a continuous superhard bearing element including a continuous superhard bearing surface and a tilting pad bearing assembly. The disclosed bearing apparatuses may be employed in pumps, turbines or other mechanical systems. In an embodiment, the bearing apparatus includes a first and second bearing assembly. The first bearing assembly includes a first support ring and a plurality of tilting pads. Each tilting pad is tilted and/or tiltably secured relative to the first support ring. The second bearing assembly includes a continuous superhard bearing element. The continuous superhard bearing element includes a continuous superhard bearing surface facing the plurality of tilting pads and exhibits a maximum lateral width greater than about 2 inches.