A gas turbine engine rotor assembly comprises a torque tube, turbine stage and stiffening mass. The torque tube comprises a shaft extending from a forward location to an aft end, and a shaft fastening flange disposed at the aft end. The turbine stage comprises a disc, a disc adapter extending forward from the disc, and a disc fastening flange extending from the disc adapter and couplable to the shaft fastening flange at an interface. The stiffening mass is positioned proximate the interface to reduce operational stress in the torque tube. A method of reducing operational stress in a rotor assembly comprises de-stacking a rotor stack, separating a first stage rotor disc adapter from a torque tube, attaching a stiffening mass to an inner diameter of one or both of the disc adapter and the torque tube, attaching the disc adapter to the torque tube, and re-stacking the rotor stack.

The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).

A rotor assembly includes a plurality of wheels and a tie bolt that extends through the plurality of wheels and applies a compressive force to the plurality of wheels. The tie bolt includes a first segment with a first stiffness and a second segment with a second stiffness to allow for thermal growth of the plurality of wheels.

A centrifugal compressor and a refrigerating device. The compressor includes: a shell, which has a fluid inlet at a first position of the shell, and a fluid outlet at a second position of the shell, a motor assembly, which is arranged in the shell and includes a stator and a rotor, the rotor including a vertically arranged rotor shaft, and the rotor shaft including a lower end and an upper end; a centrifugal compression mechanism, an impeller of which is connected with the rotor shaft so as to be driven by the motor assembly; and a guide member, which is located above the centrifugal compression mechanism, and which defines a flow passage alone or together with a top part of the shell.

An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.

A rotating machine (100) of the present disclosure includes: a bearing (10); a rotating shaft (20) having a hollow portion (21) included in a portion (20s) supported by the bearing (10); a fluid element (30) attached to one end portion of the rotating shaft (20); an introduction hole (22) that is provided, in the rotating shaft (20), on a back side of the fluid element (30), and that directs a working fluid to the hollow portion (21); and a discharge hole (23) that is provided, in the rotating shaft (20), at a position distant from the introduction hole (22) beyond the portion (20s) supported by the bearing (10), and that directs the working fluid to an outside of the hollow portion (21).

A ventilation fan includes a shaft, a rotor, a motor housing, a bearing housing, and an air bearing. The shaft has a shaft body that extends between a first shaft end and a second shaft end. The shaft body defines a first port and a bore. The rotor is disposed about the shaft. The motor housing is disposed about the shaft and is axially spaced apart from the rotor. The bearing housing is disposed about the shaft. The air bearing is disposed proximate the second shaft end and is disposed between the bearing arm and the second shaft end.

A system includes a shaft body defining a longitudinal axis. A first internal fluid channel extends axially within the shaft body and includes an inlet opening through the shaft body for fluid communication of external fluid into the first internal fluid channel and an outlet opening through the shaft body for fluid communication of fluid from the first internal fluid channel to an area external of the shaft body. A second internal fluid channel extends axially within the shaft body and includes an inlet opening through the shaft body for fluid communication of external fluid into the second internal fluid channel and an outlet opening through the shaft body for fluid communication of fluid from the second internal fluid channel to an area external of the shaft body. The first and second internal fluid channels are in fluid isolation from one another within the shaft body.