A turbocharger is provided with: a rotational shaft; a rolling bearing rotatably supporting the rotational shaft; an oil film damper disposed radially outward of an outer ring of the rolling bearing; and a housing having a first axial retaining portion and a second axial retaining portion, disposed adjacent to both ends of the oil film damper in the axial direction, respectively, for restricting movement of the outer ring in the axial direction. An axial end surface of the outer ring, or a facing surface of the first axial retaining portion or the second axial retaining portion facing the axial end surface of the outer ring has: a coefficient of static friction smaller than that of a portion of the housing excluding the first axial retaining portion and the second axial retaining portion; or has a recess where oil of the oil film damper can enter.

A compressor wheel is provided for the output shaft. Air bleed ports are formed in a shroud case that surrounds the compressor wheel. A plurality of air bleed passages are formed in the engine housing that surrounds the shroud case. An annular chamber is formed between the air bleed ports and the air bleed passages, for storing compressed air that is extracted from the air bleed ports.

In a rotary electric machine housing, a first bearing and a second bearing are provided for supporting a rotating shaft. A lubricating oil is supplied to the first bearing and the second bearing. At least one of the first bearing or the second bearing is sandwiched between the compressed air supplied from one side of the rotating shaft in an axial direction thereof and the compressed air supplied from another side of the rotating shaft in the axial direction.

A turbo device provides a flow-path arrangement in a generator device. Part of a working fluid are used to lubricate at least one of a first bearing part, a second bearing part and a bearing assembly, or the working fluid of an auxiliary flow channel is led to a generator housing for cooling the generator device. In addition, a circulatory system is also provided to include bearing loops and auxiliary loops for leading the working fluid to lubricate at least one of the first bearing part, the second bearing part and the bearing assemble part, and to cool the generator device.

A turbo device provides a flow-path arrangement in a generator device. Part of a working fluid are used to lubricate at least one of a first bearing part, a second bearing part and a bearing assembly, or the working fluid of an auxiliary flow channel is led to a generator housing for cooling the generator device. In addition, a circulatory system is also provided to include bearing loops and auxiliary loops for leading the working fluid to lubricate at least one of the first bearing part, the second bearing part and the bearing assemble part, and to cool the generator device.

A service tube assembly comprises a service tube having a threaded end portion and a ratchet hub spaced from the threaded end portion. The threaded end portion of the service tube is threadably engaged with a mating part. The assembly further comprises a locking member having a cantilever extending from a fixed end held relative to the mating part to a free end. A ratchet pawl is provided at the free end for engagement with the ratchet hub on the service tube.

A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.

A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.

A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.

A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.