An aircraft gas turbine engine (10) comprises a main engine spool (22) and a bearing arrangement (36) configured to rotatably support the main engine spool (22). The bearing arrangement (36) includes a damper (41) comprising a static element (42) and a moveable element (39). The gas turbine engine further comprises an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine spool (22), and the stator (32) is mounted to the moveable element (39) of the damper to be moveable with the moveable element (39).

A turbocharger includes a rotor shaft that is rotationally driven, a compressor impeller attached to the rotor shaft, and a cylindrical bearing portion that includes an inner cylinder and an outer cylinder, and that supports the rotor shaft in a rotatable manner. A first damping portion is provided between an axial first end portion of the inner cylinder and an axial first end portion of the outer cylinder, and an axial second end portion of the inner cylinder is connected with an axial second end portion of the outer cylinder. A second damping portion is provided between a housing and the axial second end portion. The housing and the bearing portion are fixed by a flange portion provided at the first end portion of the outer cylinder in such a manner as to restrict movement of the flange portion in a radial direction and in an axial direction.

A turbocharger includes a shaft extending along an axis, a compressor wheel coupled to a first end of the shaft, a turbine wheel coupled to a second end of the shaft and having a first diameter; and a bearing housing extending about the shaft. The bearing housing is disposed between the compressor wheel and the turbine wheel. The bearing housing having a thermal dam having a volume extending circumferentially about the shaft and disposed proximate to the second end of the shaft between the compressor wheel and the turbine wheel. The thermal dam has a second diameter extending radially from the shaft. Moreover, the second diameter of the thermal dam is between 1.1 and 1.2 times greater than the first diameter of the turbine wheel.

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.

The invention relates to an exhaust gas turbocharger having a fluid dynamic bearing having a rotor (10) and a counter-bearing part (50) assigned to the rotor (10), wherein a rotor bearing surface of the rotor (10) and a counterface of the counter-bearing part (50) face each other, to form a fluid dynamic bearing, wherein the rotor bearing surface and/or the counterface form(s) a continuous bearing contour when cut longitudinally and through the axis of rotation (R) in sectional view, which bearing contour(s) are formed of at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to generate fluid dynamic load capacities in both the radial and the axial directions, wherein the bearing surface of the rotor (10) is formed by a rotor part (40), which is connected to a rotor shaft (11) and is secured on the rotor shaft (11), and wherein the rotor part (40) is supported relative to the rotor shaft (11) in the area of a support section (14) of the rotor shaft (11). In order to be able to provide such an exhaust gas turbocharger with a compact and efficient bearing arrangement having a fluid dynamic bearing, wherein at the same time the fluid dynamic bearing can be easily mounted using few parts, provision is made according to the invention that the support section (14) and at least one of the contour sections (53.1 to 53.3) of the counter-bearing part (50) at least sectionally overlap in the direction of the axis of rotation (R).

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.

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.

The present application provides a journal bearing assembly for use with a rotor shaft of a turbine engine. The journal bearing assembly may include an outer shell, an internal oil feed port on a first side of the outer shell, an external oil feed port on a second side of the outer shell, and a connecting bore in communication with the internal oil feed port and the external oil feed port.

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 bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.