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 line scanner assembly includes a cam with a cam surface, where the cam rotatable about a cam axis of rotation and includes a first ferromagnetic material. A mirror with a planar surface is configured to tilt about a mirror axis of rotation. A follower is attached to the mirror and has a second ferromagnetic material, where the first magnetic material and/or the second magnetic material includes a permanent magnet and where the follower maintains contact with the cam due to a magnetic attraction between the first ferromagnetic material and the second ferromagnetic material.

Systems and methods are provided for a compound bearing assembly including an offset coupler supporting an inner bearing and an outer bearing for distributing a rotational loading of the compound bearing assembly. In some embodiments, at least one of the bearings comprises a bearing cage with a plurality of elongated openings for receiving a respective plurality of balls. The compound bearing assembly is configured to support a drive shaft of a supercharger system of a vehicle or some other rotational system.

A bearing component includes a black-oxide layer having metallic additional elements integrated in the structure of the black-oxide layer. Also a method of forming such a black-oxide layer that includes immersing the bearing component in a bath having the metallic additional element prior to immersing the bearing component in a black oxidation solution.

A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec).sup.1/2 and three hundred (ft/sec).sup.1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

A method of forming a bearing cage is generally disclosed herein. The method includes (i) forming a bearing cage from either titanium or a titanium alloy; and (ii) applying a plasma-nitriding treatment to at least one surface of the bearing cage to form a compound layer of titanium nitride including TiN and Ti.sub.2N on an outer region of the at least one surface. Step (ii) further forms a diffusion zone adjacent to the outer region, in one aspect. A surface hardness of the bearing cage that is treated by the plasma-nitriding step is at least 1000 HV. The bearing cage is configured to be used in a turbofan, turboprop, or turboshaft engine or in a helicopter gearbox, in one aspect.

A blood flow assist system can include an impeller assembly including an impeller shaft and an impeller on the impeller shaft, a primary flow pathway disposed along an exterior surface of the impeller. The system can include a rotor assembly at a proximal portion of the impeller shaft. A secondary flow pathway can be disposed along a lumen of the impeller shaft. During operation of the blood flow assist system, blood can be pumped proximally along the primary flow pathway and the secondary flow pathway. The system can include a sleeve bearing distal the impeller. The system can include a drive unit having a distal end disposed distal a proximal end of the second impeller. The drive unit comprising a drive magnet and a drive bearing between the drive magnet and the impeller assembly.

A self-lubricating bearing includes an outer ring having a concave inside surface that defines an interior area of the outer ring. The bearing includes an inner member having a convex exterior surface. The inner member is disposed in the interior area, and the convex exterior surface has a physical vapor deposition coating thereon. A self-lubricating liner is bonded to the concave inside surface. The outer ring is made from a first metallic alloy, and the inner member made from a second metallic alloy.

A mechanical part configured to be placed under torque. The mechanical part includes an inner tube having, a corrugated web, and an outer shell. The inner tube has an outer tube circumference, a tube axial direction, and a tube length. The corrugated web has a plurality of peaks and a plurality of troughs, a height measured as a difference between one of the peaks and one of the troughs, and a web length perpendicular to the height and in the tube axial direction. The outer shell has an inner shell circumference, an outer shell circumference, and a shell length. The plurality of troughs is affixed to the outer circumference of the inner tube. The plurality of peaks is affixed to the inner shell circumference of the outer shell. The web length is aligned with the tube length and the shell length.

A method of forming a bearing cage is generally disclosed herein. The method includes (i) forming a bearing cage from either titanium or a titanium alloy; and (ii) applying a plasma-nitriding treatment to at least one surface of the bearing cage to form a compound layer of titanium nitride including TiN and Ti.sub.2N on an outer region of the at least one surface. Step (ii) further forms a diffusion zone adjacent to the outer region, in one aspect. A surface hardness of the bearing cage that is treated by the plasma-nitriding step is at least 1000 HV. The bearing cage is configured to be used in a turbofan, turboprop, or turboshaft engine or in a helicopter gearbox, in one aspect.