A cooling fan includes a boss section (12) connected to a rotary drive source, a plurality of blades (13) protruding outward from the boss section in a radial direction, and a cylindrical ring member (14) configured to annularly connect the vicinities of end sections outside in the radial direction of the plurality of blades. The plurality of blades (13) protruding outward from the boss section (12) in the radial direction are connected by the cylindrical ring member (14) in the vicinity of the end section outside in the radial direction. An air inlet groove (16) is formed at an end section in an axial direction of an air suction side of the ring member (14). The air inlet groove (16) is disposed between front regions in the rotation direction of all of the blades (13) on the ring member (14) and front regions in the rotation direction of the blades (13) adjacent thereto. The air flowing from the outer circumferential side passes through the air inlet groove (16) of the ring member (14) and gradually changes a direction to be suctioned between the blades (13).

A seal assembly for use in a turbomachine, the seal assembly comprising an oil seal plate; a rotatable component which defines a central axis and is received in a central aperture of the oil seal plate; and an annular seal which comprises a base and a sealing portion, the base being held by the rotatable component; wherein the sealing portion is configured to form a seal with the oil seal plate when the rotatable component and annular seal are rotating below a predetermined rotational speed; and wherein the sealing portion is configured to move radially outwards with respect to the central axis such that the sealing portion loses contact with the oil seal plate when the rotatable component and annular seal are rotating above the predetermined rotational speed.

A turbine bearing and seal assembly is disclosed. The turbine bearing and seal assembly may have a turbine cartridge. The turbine cartridge may have a compressor end and a turbine end opposite the compressor end. The turbine bearing and seal assembly may also have a bearing attached to the turbine cartridge. The bearing may be disposed between the compressor end and the turbine end. The turbine bearing and seal assembly may further have a seal collar attachable to a shaft. The seal collar may be disposed within the turbine cartridge adjacent the turbine end.

Provided is a sealing device including: an impeller configured to rotate; a casing including a groove portion in a surface facing the impeller; a floating ring configured to float between the casing and the impeller and configured to be inserted into the groove portion; and a centering ring provided inside the groove portion and provided between the casing and the floating ring.

A centrifugal pump includes a rotating shaft, a pump substrate, a housing and an impeller. The pump substrate has a driving unit configured to rotate the rotating shaft. The housing has an inlet and an outlet and forms a pump chamber with the pump substrate. A body fluid sucked from the inlet flows through the pump chamber. The impeller is housed in the pump chamber and is configured to use the rotating shaft as an axis. The pump substrate has a magnetism generating source. The rotating shaft protrudes into the pump chamber from the pump substrate, and is pivotally supported on the pump substrate. A magnetic fluid is disposed on at least one of spaces formed among the pump substrate, the rotating shaft, and the impeller.

Aspects of the disclosure are directed to a seal comprising: a shoe, and at least two beams coupled to the shoe, where a first width associated with the beams exceeds a second width associated with the shoe in a reference direction. Aspects of the disclosure are directed to an engine comprising: a compressor section, a turbine section, and a floating, non-contact seal that includes: a shoe, and at least two beams coupled to the shoe, where the beams extend past an edge of a flowpath surface associated with the shoe in a reference direction.

A multi or single-stage turbocompressor with at least one compressor wheel fastened to a shaft. The shaft is mounted in a turbocompressor housing which, behind the hub disc of the compressor wheel, includes an interior housing region as well as in front of the hub disc of the compressor wheel a front interior housing region. The driven compressor wheel delivers a fluid from an inlet channel to an outlet channel. The front interior housing region includes a wheel lateral space from which an extraction channel for the extraction of fluid is provided.

A fan for a motor vehicle includes an impeller formed by multiple blades (3) extending radially from a hub (4), and a base supporting the impeller. The impeller is rotated about an axis of rotation by an actuator means and is positioned inside a hollow cylindrical cavity having the same axis and formed by an axial wall (25) attached to the base. The base includes an upstream front wall (22) extending externally in a radial plane with reference to the axis, and an outer wall (23) extending axially from the front wall (22). The front wall (22) has a protrusion (24) bordering the impeller, with the protrusion extending axially upstream with respect to the plane of the front wall (22). The upstream end of the protrusion is situated further upstream than the upstream end of the blades (3) of the impeller.

The centrifugal turbo-compressor (2) includes a hermetic casing; a drive shaft (6); a first and a second compression stage (12, 13) configured to compress a refrigerant and respectively including a first and a second impeller (18, 19) connected to the drive shaft (6) and being arranged in a back-to-back configuration; an interstage sealing device provided between the first and second impellers (18, 19). The hermetic casing includes a main casing portion (4) in which are arranged the first and second compression stages (12, 13) and the inter-stage sealing device. The first and second compression stage (12, 13) respectively includes a first and a second aerodynamic member (29, 31) each having an annular disc shape and respectively facing front-sides (21, 22) of the first and second impellers (18, 19).

A fluid transfer assembly for use in a gas turbine engine includes a rotor shaft, a stationary assembly circumscribing the rotor shaft, and a rotating component coupled to the rotor shaft and positioned radially inward of the stationary assembly. The rotating assembly includes a hub coupled to the rotor shaft, a plurality of rotor blades coupled to the hub, and a shroud coupled to the plurality of rotor blades.