A centrifugal compressor includes a low-speed shaft, an impeller, a speed increaser, a housing, a separation wall, a shaft insertion hole, a seal member, an oil pan, an oil supply passage, an oil return passage, and a pressure reduction passage. The impeller is integrally rotated with a high-speed shaft. The housing has therein an impeller chamber accommodating the impeller and a speed increaser chamber accommodating the speed increaser. The centrifugal compressor includes a bypass passage having a first end communicating with the speed increaser chamber and a second end communicating with the oil pan.

The invention relates to a turbocharger which contains a bearing device which is arranged between a compressor and a turbine and which is designed to support a shaft. This bearing device has a bearing housing, in which an oil-lubricated bearing for supporting the shaft is arranged. The shaft has a slinger element extending in the circumferential direction for centrifugally dispersing lubricating oil. The bearing housing has an oil drainage channel for discharging the lubricating oil from the bearing housing. The inner region of the bearing housing forms an oil delimitation chamber, which is sealed off by seals arranged between the shaft and the bearing housing. The oil delimitation chamber has a deflection means which is formed in such a way that, during operation of the turbocharger, lubricating oil that is centrifugally dispersed by the slinger element is deflected by the deflection means and is conducted in the opposite direction to the seals. The oil delimitation chamber is formed in the vicinity of the slinger element in such a way that the lubricating oil centrifugally dispersed by the slinger element during operation of the turbocharger can be transferred directly from said slinger element to the deflection means. A collection channel prevents lubricating oil centrifugally dispersed from the slinger element from flowing back into the seal region. The slinger element is formed in such a way that the lubricating oil sprayed away from the slinger element has a radial and an axial directional component, and the axial directional component runs in the opposite direction to the seals.

A seal assembly includes a carbon seal that has a sealing surface. A seal seat has a sealing surface and is positioned for rotation relative to the carbon seal. A diamond-like carbon coating at least partially forms the sealing surface on the seal seat.

Sealing gas systems and related methods are provided. The sealing gas system includes a machine having a first end, a bearing carrier, and a shaft seal vent, wherein the machine receives a sealing gas flow; and at least one processor, wherein the at least one processor includes or is in communication with a temperature controller for detecting a temperature of a vent gas flow at the shaft seal vent; wherein the at least one processor and/or the temperature controller are configured to detect a process gas flow through the shaft seal vent based on the detected temperature of the vent gas flow at the shaft seal vent.

An assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure extends circumferentially about the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F. The bushing is radially between the rotating structure and the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F. The mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bearing material, where the bearing material is engaged with and rotatably supports the rotating structure. The bearing material is or otherwise includes copper.

A turbocharger includes a shaft extending between first and second shaft ends. A turbine wheel is coupled to the first shaft end, and a bearing housing defines a bearing housing interior and is disposed about the shaft. A turbine housing defines a turbine housing interior and is disposed about the turbine wheel. A sealing assembly includes a case disposed about the shaft and extending between a first case end proximate to the turbine wheel and a second case end distal from the turbine wheel. The sealing assembly also includes a ring disposed between the shaft and the case such that the ring is unobstructed by the case radially between the shaft and the ring. The sealing assembly further includes a deformable component coupled to the second case end and to the ring, and is moveable with the ring to seal the bearing housing interior and the turbine housing interior.

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.

A gas turbine engine includes a first bearing compartment and a seal assembly within the first bearing compartment that includes a rotatable seal seat, a gutter radially outward of the seal seat and fixed against rotation. The gutter includes a channel on its radially inner face. A second bearing compartment is also included. A scavenge pump is in communication with a first supply line configured to supply the first bearing compartment and a second supply line configured to supply the second bearing compartment. The gutter is in communication with the scavenge pump through a gutter scavenge line.

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 method of operating a gas turbine engine in a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing and a gearbox connected to the engine shaft for torque transmission therebetween, includes axially preloading the bearing using an axially biasing element disposed between the gas turbine engine and the gearbox. The axially biasing element reacts against the gearbox to exert an axial preload force on the bearing and the engine shaft of the gas turbine engine.