A rotating machine includes a hub portion, wherein the hub portion comprises a forward face and an aft face. The rotating machine further includes a cooling channel formed on either the forward face or the aft face and configured to direct cooling air to a location on the rotating machine, wherein the cooling channel extends from a radially inner location along the face to a radially outer location along the face, and wherein the cooling channel is configured as a recess formed into an outer surface of the face.

A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.

A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.

An exhaust-gas turbocharger for an internal combustion engine has a turbine housing, in which a turbine wheel with a shaft is arranged rotatably. The shaft is mounted rotatably in a bearing housing via at least one piston ring adjacently with respect to the turbine wheel. The bearing housing has a lubricant inflow and a pressureless lubricant outflow for lubricating the shaft, wherein an insulating washer is provided which is clamped in by the turbine housing and the bearing housing and has an opening which is connected to the lubricant outflow in a manner which conducts a lubricant. Passage of lubricant out of the bearing housing into the turbine housing is avoided.

A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

A bearing housing cover for a gas turbine engine having an impeller. The bearing housing comprises an annular collar having a flange mountable to an exterior surface of a bearing housing. The bearing housing further comprises an impeller baffle integrated with the annular collar, the impeller baffle having an annular body with a front baffle face positionable adjacent a rear face of the impeller, a rear baffle face having a plurality of stiffening elements extending between the rear baffle face and the annular collar, and a central baffle opening.

There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.