A fuel cell fluid machine includes a rotary shaft, an electric motor, a compression unit, and a rotation assist unit. The rotation assist unit includes a turbine wheel and a turbine housing. Exhaust gas discharged from a fuel cell stack is introduced to the turbine chamber. The exhaust gas then flows in the radial direction of the rotary shaft and is discharged in the axial direction of the rotary shaft. This rotates the turbine wheel. A diameter of the turbine wheel and a diameter of the shroud surface gradually increase from an upstream side to a downstream side in a flowing direction of the exhaust gas.

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.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

A compressor wheel for a compressor of a turbocharger has a hub and a multiplicity of blades on the hub. In intermediate spaces of the multiplicity of blades, a channel is in each case formed between a suction side and a pressure side. The channel guides fluid that flows in axially in relation to a rotation axis radially or radially-axially outward. The hub in relation to the rotation axis is contoured such that the hub has a rotationally symmetrical portion and a non-rotationally symmetrical portion. On the non-rotationally symmetrical portion, a transition between the hub and each of the blades is embodied with a radiused connection and facing the suction side has a region of modified thickness. A region formed by control rays is generated in at least one channel between the suction side and the pressure side on the hub. A method produces the compressor wheel.

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 system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

An assembly is provided for a turbine engine. This assembly includes a static structure and an impeller rotor housed within the static structure. The impeller rotor includes a vane structure and a shroud. The vane structure includes a first sidewall, a second sidewall and a plurality of vanes arranged circumferentially about a rotational axis. The vanes include a first vane. The first vane includes a first portion, a second portion and a third portion. The first portion is axially between the first sidewall and the second sidewall. The second portion is radially between the first sidewall and the shroud. The third portion is radially between the second sidewall and the shroud. The shroud circumscribes the vane structure. A gap is formed by and extends between the shroud and the static structure. A dimension of the gap changes as the gap extends along the shroud.

This impeller is provided with: an impeller body having a disk-like shape and rotating about an axis together with a rotating shaft; and compressor blades (25) provided so as to protrude from the hub surface (31b) of the impeller body, the hub surface (31b) being formed on the front surface side of the impeller body, the compressor blades (25) each having a pair of side surfaces (26) which faces the circumferential direction of the rotating shaft and along which fluid flows. Each of the compressor blades (25) is formed in a tapered shape so that, within a range in which stress in the direction of the axis of at least the rotating shaft is maximum, the pair of side surfaces (26), when viewed in a cross-section perpendicular to the axis, approach each other as the pair of side surfaces (26) extends radially outward of the rotating shaft.

A radial expander having a rotor mounted in a housing and comprising multiple blades. The blades together with a radially inner hub contour of a rotor hub and a radially outer housing contour define flow channels for the process gas, which process gas to be expanded enters in a radial direction and from which expanded process gas exits in the axial direction. The radially inner hub contour of the rotor includes a curvature change at least in some circumferential positions seen in the meridional section such that adjacent to a flow leading side of the rotor, the radially inner hub contour, seen in the meridional section, is curved radially to the outside and adjacent to a flow trailing side of the rotor, the radially inner hub contour, seen in the meridional section, is curved radially to the inside.

A method for creating an impeller and an impeller of a radial turbo fluid energy machine includes a wheel disc, cover disc, blades, and hub. The hub is mounted on a shaft which extends along an axis, the wheel disc extends substantially radially from the hub, and the cover disc is connected to the wheel disc by the blades such that flow channels separated from one another in the circumferential direction are defined by the blades. The impeller has a first flow passage in a substantially axial direction in the radial proximity of the hub, and the impeller has a second flow passage in a substantially radial direction radially farther away from the hub than the first flow path passage. The cover disc surface facing the wheel disc has a lower degree of roughness at least in some regions than the wheel disc surface facing the cover disc.