An oil supply assembly for a bearing damper of a gas turbine engine includes an oil supply tube configured to supply oil in a first direction. The assembly also includes a bearing support having a bearing damper path connecting the bearing damper to the oil supply tube and a bearing compartment path connecting a bearing compartment to the oil supply tube. The assembly also includes a check valve disposed within the bearing damper path and configured to allow fluid communication in the first direction from the oil supply tube to the bearing damper and block fluid communication in a second direction opposite the first direction.

An exhaust gas turbocharger for an internal combustion engine may include a rotor with a turbine wheel of a turbine, a compressor wheel of a compressor and a shaft. The shaft may be connected to the turbine wheel and to the compressor wheel in a rotationally fixed manner. A bearing cartridge may be included for mounting the rotor in a housing. The bearing cartridge may have an inner sleeve arranged on the shaft axially between the turbine wheel and the compressor wheel with respect to an axis of rotation and an outer sleeve arranged coaxial thereto. The outer sleeve may be rotatably mounted on the inner sleeve via at least one rolling body. At least two damping rings may be included which are coaxially arranged on the outer sleeve axially spaced from one another and supported on a respective bearing section of the housing.

A bearing structure of a turbocharger includes a rotor shaft, a ball bearing, and a housing. An inner ring of the ball bearing has the rotor shaft inserted therein. The oil film damper is formed between the inner ring and an outer peripheral surface of the rotor shaft. The inner ring rotates with rotation of the rotor shaft via the oil film damper. An oil discharge path for scattering oil discharged from the oil film damper radially outside, is provided at least either on one end surface of the inner ring in an axial direction or on an opposing surface opposed to the inner ring, of a collar. The oil discharge path is formed of a groove that is arranged in a manner to be gradually apart from the oil film damper in the axial direction as going radially outside.

Aspects of the disclosure are directed to a shaft of an engine of an aircraft, an oil scoop coupled to the shaft, a first portion of a sensor integrated with the oil scoop, and a second portion of the sensor coupled to a structure of the engine. In some embodiments, the first portion of the sensor comprises at least one tooth.

A linear guide with lubrication device includes: a elongate rail; a slide module slidably mounted on the elongate rail and including a slide block and two recirculation members, which are respectively mounted to two end faces of the slide block and include a plurality of recirculation passages, in which at least one of the recirculation members includes a lubricant reservoir and a fixing through hole formed therein such that the lubricant reservoir, the recirculation passage, and the fixing through hole are in communication with each other and the lubricant reservoir receives lubricant filled therein; an application member received in the fixing through hole; a transferring member covering the application member and the transferring member absorbing and transferring lubricant to the application member. Rolling bodies, when moving through the recirculation passage, may contact the application member to have lubricant applied thereto.

The present disclosure concerns an oil distribution assembly for a system having rotating components requiring a supply of oil, such as bearing components of a gas turbine engine. Example embodiments include an oil distribution assembly for a gas turbine engine, comprising: an oil distributor mounted for rotation about a rotation axis of the assembly and comprising an internal volume having a plurality of channels extending along an inner radial surface of the oil distributor; and an oil injector arranged to direct a supply of oil to the plurality of channels in a direction having a component in a first direction along the rotation axis; wherein each of the plurality of channels is angled relative to the rotation axis such that a radial distance between each channel and the rotation axis increases along the rotation axis.

A bearing structure of a turbocharger includes a rotor shaft, two angular ball bearings, a retainer, a housing, and an oil film damper. Each of the angular ball bearings includes an inner ring and an outer ring that are supported in relatively rotatable manner. The rotor shaft is inserted into the inner ring. The retainer holds the outer ring. The housing houses therein the rotor shaft, the angular ball bearings, and the retainer to constitute a bearing housing. The oil film damper is formed of oil in a film state and is interposed between the inner ring and an outer peripheral surface of the rotor shaft. The inner ring is configured to rotate with rotation of the rotor shaft via the oil film damper.

Systems and methods for an interaxle differential (IAD) are provided. In one example, the IAD comprises a locking assembly that includes a friction clutch, the friction clutch includes a clutch pack that comprises plurality of plates configured to engage and disengage to inhibit and permit speed differentiation between a first axle differential and a second axle differential. The IAD further includes a supply lubrication passage that comprises an inlet that receives a lubricant from an enclosure surrounding an input gear of an axle differential and a first outlet flowing the lubricant to a gear coupled to the clutch pack.

A bearing assembly for a turbocharger includes a turbine wheel-side ball bearing at a first axial end of a tubular body, a compressor impeller-side ball bearing at a second axial end of the tubular body, and a bearing housing. The bearing housing includes a first opposed wall opposed to an axially outer side of an outer race of the turbine wheel-side ball bearing, and a second opposed wall opposed to an axially outer side of an outer race of the compressor impeller-side ball bearing. The outer race of the turbine wheel-side ball bearing and the outer race of the compressor impeller-side ball bearing have axially outer end surfaces which are axially outwardly displaced from respective axial end surfaces of the tubular body so that oil films are present between the respective outer races and the corresponding opposed walls.

A rolling bearing apparatus includes: a bearing portion having an inner ring, an outer ring, a plurality of balls, and a cage; and a lubrication unit that is provided adjacently to an annular space formed between the inner ring and the outer ring and that has a pump that feeds a lubricant into the annular space. The pump has a main body portion having an internal space in which the lubricant is retained and being open at one end of the main body portion, a metal diaphragm fixed to a fixation portion that is a part of the main body portion so as to close the opening of the main body portion, and a piezoelectric element fixed to the diaphragm. At least the fixation portion of the main body portion is formed of metal, and the fixation portion and the diaphragm are fixed together by metal joining.