An air starter for an engine, such as a turbine engine, that includes a turbine for rotatably extracting mechanical power from a flow of fluid. The turbine includes a drive shaft that can be coupled to an output shaft to provide a rotational output. The interface between the drive shaft and the output shaft can be offset.

A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

A rotary electric machine system making part of a combined power system is equipped with a rotary electric machine having a rotor including a rotating shaft and a rotary electric machine housing in which the rotary electric machine is accommodated. In such a rotary electric machine, a first bearing and a second bearing are disposed between the rotary electric machine housing and the rotating shaft. The gas supplied from the gas supply source flows on an upstream side through a terminal casing in which electric terminal portions are accommodated, and on a downstream side through the first bearing and the second bearing inside the rotary electric machine housing.

An impeller attach mechanism for a turbocharger including a stud extending from a central bore of a compressor impeller toward a turbine wheel, the stud having a first threaded region and a second threaded region; a shaft coupled to the turbine wheel and extending toward the compressor impeller, the shaft having a leading portion, the leading portion having a threaded interior configured to engage the second threaded region of the stud; and an insert having an internal portion and an external portion, the internal portion having a threaded external surface to engage the compressor impeller, the internal portion having a threaded internal surface to engage the first threaded region of the stud, the external portion configured to surround the leading portion of the shaft.

An impeller attach mechanism for a turbocharger including a stud extending from a central bore of a compressor impeller toward a turbine wheel, the stud having a first threaded region and a second threaded region; a shaft coupled to the turbine wheel and extending toward the compressor impeller, the shaft having a leading portion, the leading portion having a threaded interior configured to engage the second threaded region of the stud; and an insert having an internal portion and an external portion, the internal portion having a threaded external surface to engage the compressor impeller, the internal portion having a threaded internal surface to engage the first threaded region of the stud, the external portion configured to surround the leading portion of the shaft.

A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.

A turbine rotor in an embodiment is configured by joining a rotor component member and a rotor component member together by bolt fastening with an abutting end surface of the rotor component member and an abutting end surface of the rotor component member abutting on each other. The turbine rotor includes: a cylindrical recessed portion that is formed at the abutting end surface and is recessed in an axial direction; an axial passage bored from a bottom surface of the cylindrical recessed portion in the axial direction; an introduction passage introducing the cooling medium into the axial passage; a discharge passage discharging the cooling medium from the axial passage; and a sealing member that is arranged in the cylindrical recessed portion and seals one end of the axial passage.

Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at least in part extends through one of the rotor shafts of the rotor structure. Disclosed embodiments may further benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of the process fluid being processed by the compressor. In operation, the flow loop may be appropriately pressurized to keep any residual seal leakage that may develop in one or more of the seal elements from travelling onto the hirth couplings

A rotor shaft cap for a gas turbine has a disk-shaped body defining a first axial face, a second axial face, and an outer radial face. The disk-shaped body has a first annular jaw provided on the first axial face. The first annular jaw includes a plurality of teeth projecting from the first axial face. A plurality of apertures are defined by the disk-shaped body, each aperture of the plurality of apertures extends through the disk-shaped body along an axial direction.

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas and a gear train is drivingly coupled with the turbine member. A drive shaft is operably coupled with the gear train, and a decoupler is selectively coupled to the drive shaft for decoupling the air turbine starter from the engine.