A bearing assembly for supporting rotation of a shaft in a turbocharger includes an inner race extending along an axis. The inner race is configured to be coupled to the shaft. The bearing assembly also includes an outer race spaced radially from the inner race and a cage disposed radially between the inner race and the outer race. The bearing assembly further includes a rolling element disposed radially between the outer race and the inner race. The rolling element is disposed within the cage for supporting rotation of the shaft. The outer race defines a lubricant passageway configured to direct lubricant toward the cage.

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 casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

A turbocharger includes a shaft, a compressor wheel, a turbine wheel, and a bearing assembly including an inner race, a first outer race spaced from the inner race, a second outer race spaced from the inner race, a first rolling element disposed between the first outer race and the inner race, and a second rolling element disposed between the second outer race and the inner race. The bearing assembly includes a first biasing member configured to bias the first outer race toward the second outer race and against the first rolling element, and preload the first rolling element with a preloading force, and a second biasing member configured to bias the second outer race toward the first outer race and against the second rolling element, and preload the second rolling element with a second preloading force. The first preloading force is different than the second preloading force.

An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between a bearing inner side and a bearing outer side. The journal bearing includes a bore, a passage, a groove and a slot. The bore extends axially within the journal bearing and along the bearing inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove extends longitudinally within the journal bearing at the bearing outer side between a groove first end and a groove second end. At least a portion of the slot extends circumferentially about the axis within the journal bearing at the bearing outer side from the groove first end to the groove second end.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between an inner side and an outer side. The journal bearing includes a bore, a passage and a groove. The bore extends axially within the journal bearing and is formed by the inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove is arranged at the outer side. The groove extends longitudinally within the journal bearing between a first end and a second end. The groove extends axially within the journal bearing between a first side and a second side. An axial distance between the first side and the second side changes as the groove extends longitudinally between the first end and the second end.

A seal system for a bearing compartment of a gas turbine engine includes an annular rotating seal seat in contact with the seal element to form a dry seal interface therebetween to separate am oil-wetted zone from a dry zone. The annular rotating seal seat forms a dry zone annular space adjacent to the annular seal element and the rotating component. The annular rotating seal seat having an oil return passageway through the rotating seal seat to provide a communication path from the dry zone annular space outboard of the rotating component back to the oil-wetted zone.

A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.

An actuator assembly for a variable turbine geometry (VTG) turbocharger is disclosed. The actuator assembly may include an actuator and an actuator linkage having a first end coupled to the actuator and a second end defining a linkage joint. The actuator assembly may further include a VTG lever having a ball stud bore extending through the VTG lever. Additionally, the actuator assembly may include a ball stud including a first end partially disposed within the linkage joint and a second threaded end extending axially through the ball stud bore. Furthermore, a nut may be aligned with the ball stud bore and movably attached to the VTG lever prior to extending the ball stud through the ball stud bore, wherein the ball stud engages with the nut and fastens the ball stud to the VTG lever to operatively couple the VTG lever to the actuator linkage.