A seal assembly for a gas turbine engine, may be manufactured in two pieces, the first piece is a seal plate with a cavity around its inner wall and the second piece is a sleeve that mounts in the cavity of the seal plate. The sleeve may have oil distribution channels that deliver oil to subsequent components and apertures that deliver oil to the seal plate. The volume of oil delivered to the seal plate can be set by the number of apertures and related radial holes in the sleeve. Because the sleeve delivers oil through the apertures and radial holes to an annulus in the cavity of the seal plate, cooling bores in the seal plate need only be drilled into the annulus and the number of cooling bores can be independent of the number of radial holes in the sleeve.

A turbocharger includes a two-piece thrust collar that includes inner and outer portions disposed around a rotatable shaft. The inner portion is engaged with a bushing disposed in and connected to the center housing by a retainer. The outer portion is disposed adjacent the inner portion along the rotatable shaft and connected to the rotatable shaft such that it rotates therewith. The outer portion forms an annular channel that extends in a radial direction relative to the rotatable shaft and peripherally around the shaft. An oil deflector is connected to the compressor back-plate and includes a base flange and a raised portion disposed at least partially over the annular channel.

An exhaust-gas turbocharger (1) comprising a compressor (2); a turbine (3); and a bearing housing (4), in which there is arranged a bearing cartridge (5), secured against axial displacement and twisting; and a single fixing element (6) securing the bearing cartridge (5) both against axial displacement and also twisting in the bearing housing (4). Also a method for assembling a bearing cartridge (5) in a bearing housing (4) of an exhaust-gas turbocharger (1).

The present disclosure relates to 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 comprising: 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.

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 couples to the drive shaft that is rotatably supported by the least one bearing assembly. A lubricant passageway can provide lubrication to the at least one bearing assembly.

A bearing housing for supporting a bearing of a gas turbine engine. The bearing housing comprises an annular body extending around an axis and having an oil inlet and an oil outlet. The bearing housing further comprises an oil manifold integrated into the annular body, the oil manifold having an inner oil channel defined in the annular body and extending circumferentially around the axis, the inner oil channel in fluid communication with the oil inlet and at least one oil jet directed towards the bearing.

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 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.

The invention relates to an exhaust gas turbocharger with a manifold-flow casing, in particular a dual-flow casing (47) and a turbine wheel (34) which is rotatably arranged within said manifold-flow casing, onto which an exhaust gas flow (14; 16) may be led via at least one of several flow channels (18, 26), and an outlet opening (78; 80) following said one flow channel (18, 26) and covering an angle of 180° max. about an axis of rotation (44) of the turbine wheel (34), so that a shaft (38) is rotating which is arranged coaxially and non-rotationally relative to the turbine wheel (34), which is supported in a shaft bearing (42).

An apparatus for sealing an internal environment of a turbomachine includes a first chamber connectable in fluid communication with a high pressure environment of a turbomachine so that a working fluid can flow from the high pressure environment to the first chamber; and a second chamber in fluid communication with a lubrication circuit so that a lubricant can flow from the lubrication circuit to the second chamber. The first and second chambers are arranged in fluid communication with each other so that the working fluid can flow from the first to the second chamber. A return line for the working fluid is in fluid communication with the first chamber and connectable in fluid communication with a low pressure environment of the turbomachine so that the working fluid can flow from the first chamber to the low pressure environment. A pressure regulating device is included along the return line and is configured to provide a predetermined pressure drop.