The centrifugal compressor (1) includes: an impeller (3); and a casing (2) accommodating the impeller (3). The casing (2) includes: an inlet (6); an impeller-accommodating portion (14) in which the impeller (3) is disposed; an annular chamber (11) formed around the inlet (6); a downstream groove (13) communicating a downstream end portion of the annular chamber (11) with the impeller-accommodating portion (14); and an upstream groove (12) communicating an upstream end portion of the annular chamber (11) with the inlet (6). In addition, the downstream groove (13) is provided in a predetermined range in a circumferential direction of the impeller (3) so as to communicate with a high-pressure part to occur in part of the impeller-accommodating portion (14), and the upstream groove (12) is provided over the entire circumference of the inlet (6).

A centrifugal compressor includes: an impeller (compressor impeller); a main flow passage, which has the impeller arranged therein, and extends in a rotation axis direction of the impeller; an auxiliary flow passage formed on a radially outer side of the impeller with respect to the main flow passage; an upstream communication passage configured to allow the auxiliary flow passage and the main flow passage to communicate to each other; a downstream communication passage configured to allow the auxiliary flow passage and the main flow passage to communicate to each other on a side closer to the impeller with respect to the upstream communication passage; and a partition portion (rib or fin) configured to partition the auxiliary passage in a circumferential direction while maintaining a gap larger than a flow passage width of the downstream communication passage in the auxiliary flow passage.

A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.

A centrifugal compressor for a chiller system includes a casing, an inlet guide vane, an impeller disposed downstream of the inlet guide vane, a motor and a diffuser. The casing has inlet and outlet portions with the inlet guide vane disposed in the inlet portion. The impeller is attached to a shaft rotatable about a rotation axis, and the motor rotates the shaft in order to rotate the impeller. The centrifugal compressor further includes a casing treatment bypass having an entrance port and an exit port. The casing treatment bypass injects refrigerant from a gap between the impeller and the inlet portion of the casing toward an area between the impeller and the inlet guide vane. The exit port of the casing treatment bypass is positioned upstream in a direction of a refrigerant flow with respect to the entrance port of the casing treatment bypass.

An inline axial flow fan includes a first fan including a first impeller, a first motor portion, and a first case, and a second fan including a second impeller, a second motor portion, and a second case, the first fan and the second fan being positioned in sequence from one axial side to another axial side. The first case includes multiple first slits, and the second case includes multiple second slits. The inline axial flow fan includes a flange extending radially outward from an outer peripheral surface of the first case or the second case located between the first slit and the second slit in the axial direction.

A turbocharger is provided and includes a compressor housing and a recirculation slit and a recirculation passage provided at an inlet of the compressor housing to enable air flowing into the compressor to be recirculated. A gas supply part supplies blow-by gas towards the inlet of the compressor housing to allow blow-by gas to be joined with air recirculated through the recirculation slit and the recirculation passage and to guide recirculating air towards a compressor wheel.

A turbine section of a turbomachine includes a housing that houses and supports the rotating group for rotation about an axis. The housing defines a circumferential inlet passage that extends about the axis. The housing defines a turbine wheel upstream area that is disposed downstream of the circumferential inlet passage and upstream of the turbine wheel. The housing defines an outlet that is downstream of the turbine wheel. Furthermore, the turbine section includes a first flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, across the turbine wheel, to the outlet. Moreover, the turbine section includes a recirculation flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, and back to the circumferential inlet passage.

Compressor for charging a combustion engine, comprising a compressor housing (1) with a volute (2), a compressor wheel (3) being arranged in the compressor housing (1), the compressor wheel (3) turning about an axis (A) and transporting gas into the volute (2), and an inlet channel (4), at least an end portion of the inlet channel (4) being oriented in the direction of the axis (A) in order to direct gas towards the compressor wheel in the axial direction, wherein an exhaust gas channel (5) terminates into the inlet channel (4) upstream of the compressor wheel (3), and wherein the exhaust gas channel (5) can be shut off by means of a valve (6), wherein a housing (8) of a driving device (7) of the valve (6) is integrally formed with the compressor housing (1).

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.

There is provided a turbocharger comprising a compressor housing having an inner surface defining a flow path between an inlet and an outlet of a compressor of the turbocharger. The compressor housing is configured to support a compressor wheel supported therewithin. The inner surface of the compressor housing comprises an indent formed into the inner surface. At least a portion of the indent is located upstream of the compressor wheel in an assembled configuration. The indent comprises a portion that is undercut into the housing towards the inlet.