The invention relates to a separating device for a turbomachine, comprising at least one housing (12) that has at least one bearing receiving area (24), which defines at least one bearing axis (26), and at least one wheel-side area (28). The separating device also comprises at least one swirling unit (32), which is arranged on the housing (12) in particular, for deflecting and/or swirling at least one fluid and/or particle flow (34), wherein the swirling unit (32) has at least one flow recess (38) which is delimited by a wall (36) of the housing (12) and which extends within the wheel-side area (28) at a distance from the bearing axis (26). According to the invention, the swirling unit (32) comprises at least one seal gap element (40) which is arranged on a wall (36) of the housing (12) and which is designed to deflect and/or swirl at least one fluid and/or particle flow (34) flowing through the flow recess (38) along the bearing axis (26) and/or towards the bearing axis (26).

A casing treatment for a compressor includes one or more cavities in a casing disposed radially outwardly of tips of the compressor rotor blades. A liner is moveable relative to the casing between a first position and a second position. The liner is shaped to add a volume to the tip clearance gap when moving from the second position toward the first position. The liner is displaceable between the first and second positions in coordination with at least the rotation of inlet guide vanes (IGVs) between IGV positions.

A compressor housing includes: an intake flow path-forming section configured to form an intake flow path; a shroud portion including a shroud surface curved in a protruding manner to face blades of an impeller; and a scroll flow path-forming section configured to form a scroll flow path through which gas is guided outside the compressor housing. A groove portion extending in a circumferential direction is defined in the shroud surface and, in a cross-sectional view taken along an axis of the impeller, the groove portion includes a downstream side wall surface, wherein a distance from the axis of the impeller to the downstream side wall surface increases toward an upstream side from a downstream side end portion of the groove portion, and an upstream side curved surface that is recessed between an upstream end of the downstream side wall surface and an upstream side end portion of the groove portion.

A fairing, in the form of a contoured restriction, submerged on a fluid channel surface of a fluid channel through which liquid flows, re-distributes velocity fields and flow geometries upstream and in some embodiments downstream of a discontinuity, thereby preventing flow separation, reducing cavitation potential and increasing flow capacity. Such discontinuities include, but are not limited to: joints, for example elbow joints, T-joints and Y-joints; valve-trims; entrance regions to centrifugal pumps; and entrance regions to rotary valves, steps, reductions, expansions and ledges. The fairing may be fitted into the channel or integrally fabricated with the channel.

An illustrative example embodiment of a compressor includes an inlet defining an intake passage, a plurality of inlet guide vanes, an impeller, and a plurality of swirl nozzles. Fluid flow through the plurality of inlet guide vanes into the intake passage is selectively adjustable to control fluid flow through at least the portion of the intake passage downstream of the swirl nozzles. The impeller includes a plurality of blades and directs fluid from the intake passage toward an outlet. The swirl nozzles have outlets positioned downstream of the plurality of inlet guide vanes and upstream of the impeller. The swirl nozzles are configured to introduce fluid into the intake passage to cause swirl of fluid in the intake passage between the plurality of inlet guide vanes and the impeller.

A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

A casing treatment for a compressor includes one or more cavities in a casing disposed radially outwardly of tips of the compressor rotor blades. A liner is moveable relative to the casing between a first position and a second position. The liner is shaped to add a volume to the tip clearance gap when moving from the second position toward the first position. The liner is displaceable between the first and second positions in coordination with at least the rotation of inlet guide vanes (IGVs) between IGV positions.

An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow.

A compressor housing (12) for a turbocharger includes a recirculation cavity (4) formed in a portion of the compressor housing (12). The recirculation cavity (4) is defined by an inner cavity wall (2) and an outer cavity wall (5). In addition, an inlet groove (1) and an outlet (7) are formed in the recirculation cavity (4) for circulating airflow from the compressor housing (12) through the recirculation cavity (4), and at least one recirculation noise obstruction (6) is fixedly secured within the recirculation cavity (4) to disrupt air flow through the cavity and reduce noise in the compressor housing (12).

A centrifugal compressor for a chiller system includes a casing having an inlet portion and an outlet portion, a recirculation structure including a recirculation path and a recirculation discharge cavity, an impeller disposed downstream of the recirculation discharge cavity, a plurality of recirculation discharge guide vanes disposed to surround the recirculation discharge cavity, and a diffuser disposed in the outlet portion downstream of the impeller. The recirculation structure is configured to impart a swirl to a flow of refrigerant into the inlet portion. The recirculation path supplies the refrigerant from the diffuser to the recirculation discharge cavity. The recirculation path includes a recirculation pipe that introduces the refrigerant toward the plurality of recirculation discharge guide vanes. An annular groove is disposed between the recirculation pipe and the plurality of recirculation discharge guide vanes. An annular plate is disposed between the annular groove and the recirculation discharge cavity.