A seal system for a bearing chamber of a turbomachine includes a baffle element encircling the axis of the machine. The baffle element is formed with front surface including a plurality of gutter surfaces which are angularly spaced about the rotational axis. The seal system can thus be mounted in any one of a plurality of orientations with respect to the direction of gravity, such that in any of the orientations one of the gutter surfaces is directed downwardly.

A positive pressure generating mechanism comprising a positive pressure generating groove is provided to a high-pressure side of one of two sliding surfaces that slide relative to each other in a pair of sliding components, and a negative pressure generating mechanism comprising a negative pressure generating groove is provided to a low-pressure side. The positive pressure generating groove and negative pressure generating groove are communicated with a high-pressure fluid side and separated from a low-pressure fluid side by a seal surface.

A turbocharger assembly can include a center housing that includes a compressor side, a turbine side, a bore that extends between the compressor side and the turbine side and a socket at the compressor side; a journal bearing disposed in the bore; and a lubricant deflector disposed at least partially in the socket. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

A gas turbine engine having a bearing housing with a housing cavity and a shaft rotating about a rotation axis. One or more bearings support the shaft. A housing supporting the bearing and defining a chamber axially adjacent to the bearing. A seal assembly is in the housing between the chamber and an exterior of the chamber. The seal assembly includes a seal supported by the housing and surrounding the shaft so as to define an annular gap between an inner surface of the seal and an outer surface associated to the shaft, the gap defining a part of a sealing path of the seal assembly for air to flow from said exterior into the chamber. An impeller rotates with the shaft and located radially inward of the gap relative to the rotation axis, the impeller oriented to drive oil toward the bearing.

An assembly is provided for a turbine engine. This turbine engine assembly includes a journal bearing and a filter. The journal bearing has an internal bearing bore. The filter is arranged within the internal bearing bore. The filter includes a tubular filter element and a first end cap. The tubular filter element extends axially along an axis between a first end and a second end. A perforated portion of the tubular filter element is radially disposed away from the journal bearing by a cavity. The first end cap is mounted to the tubular filter element at the first end. The first end cap is sealed radially against the journal bearing by a first interference fit.

An air starter for starting a turbine engine that includes a housing, a turbine member, a drive shaft, and at least one bearing assembly. The housing can define an interior where the turbine member rotatably couples to the drive shaft, where the drive shaft or turbine member are rotatably supported by the least one bearing assembly. A scoop wheel located in the interior of the housing provides lubrication to the at least one bearing assembly.

An exhaust gas turbocharger may include a shaft mounted in a bearing housing carrying a compressor wheel and a turbine wheel. The shaft may include a sealing bush arranged on the shaft in a rotationally fixed manner. The sealing bush together with a bearing housing cover may at least partially delimit an annular oil centrifuging space arranged coaxially to the sealing bush. The bearing housing cover may include a guiding nib located radially outside the sealing bush partially covering the sealing bush in axial direction. The guiding nib may be configured to guide oil separated in the oil centrifuging space onto the rotating sealing bush. The rotating sealing bush may be configured to direct the oil into the oil centrifuging space in response to centrifugal force creating an oil swirl.

Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: 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.

A turbocharger system can include a housing that includes a through bore, a plurality of lubricant bores, a plurality of lubricant bore to through bore openings and a recessed compressor-side surface that defines in part a passage that fluidly couples at least two of the lubricant bores; a rolling element bearing unit disposed at least in part in the through bore of the housing; and, a plate that covers at least a portion of the recessed compressor-side surface of the housing.

A turbine bearing and seal assembly is disclosed. The turbine bearing and seal assembly may have a turbine cartridge. The turbine cartridge may have a compressor end and a turbine end opposite the compressor end. The turbine bearing and seal assembly may also have a bearing attached to the turbine cartridge. The bearing may be disposed between the compressor end and the turbine end. The turbine bearing and seal assembly may further have a seal collar attachable to a shaft. The seal collar may be disposed within the turbine cartridge adjacent the turbine end.