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 is provided. The compressor includes a first stage portion with a first impeller assembly and a first diffuser assembly, a second stage portion with a second impeller assembly and a second diffuser assembly, and an interstage portion situated between the first stage portion and the second stage portion. The interstage portion includes a directing vane assembly, a collector passage surrounding the directing vane assembly, and a circumferential insertion slot fluidly coupling the collector passage to the directing vane assembly.

Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a throttle ring disposed between stages of the compressor. The throttle ring can allow or obstruct flow through the side stream injection port. The throttle ring can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. A method of operating a centrifugal compressor can include actuating a throttle ring by rotating a drive ring to adjust a flow of interstage fluid into the second stage impeller.

An air moving device has a housing with a primary flow path and a secondary flow path that extends from a secondary inlet of the housing and empties into an inner outlet adjacent the primary flow path. An impeller assembly rotates a blade to cause air to enter the housing and flow along the primary flow path. The flow of air through the primary flow path creates a low pressure region at the inner outlet of the secondary flow path, causing air to flow through the secondary flow path and mix with the air in the primary flow path. The mixture of air flows through a downstream portion of the primary flow path having an expanded width compared to an upstream portion of the primary flow path and exits the housing. Stator vanes may extend longitudinally within the housing to cause columnar air flow. The device may be used for destratification of thermal gradients of air within an enclosure, such as a home or warehouse.

A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil and a flow separation control device. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body.

A cooling fan includes a fan frame and an impeller. The fan frame includes a substrate, a sidewall connected to the substrate, and a lid connected to the sidewall and opposite to the substrate. An air inlet is formed in the lid. The substrate, the sidewall, and the lid together define at least one air outlet. The impeller is rotatably mounted in the fan frame. A plurality of bulges protrudes from an inner face of the sidewall and/or an inner face of the lid.

Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a capacity control valve that has a curved surface facing a flow of refrigerant from the first stage to the second stage. The capacity control valve can allow or obstruct flow through the side stream injection port. The capacity control valve can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. The side stream injection port and the capacity control valve can be ring-shaped. The side stream injection port and the capacity control valve can allow at least some of the side stream to be introduced on a side of the capacity control valve opposite the curved surface.

Embodiments of a compressor stage, in particular for a turbocharging system and/or a turbocompound, and a process for operating a compressor stage are provided herein. The compressor stage comprises an impeller, and a vaned diffuser arranged downstream of the impeller. The vaned diffuser is in fluid connection with an outlet of the impeller and comprises an injection device configured to inject a secondary fluid into the vaned diffuser. The injection device comprises a displaceable port at least partially arranged between an adjacent pair of vanes of the diffuser.

A compressor capable of generating a swirling flow at a sufficient speed with respect to a main flow of intake air that flows into a compressor impeller without hindering the main flow. The compressor includes a compressor impeller, a shroud covering a tip end edge of the impeller, an intake duct extending along an axial direction of the impeller, a swirling flow passage being annular around a rotating shaft and having a flow passage cross-sectional area that gradually decreases along the same direction as a rotation direction of the impeller from a base end side where a swirling gas introduction portion is disposed toward a front end side, and a swirling gas ejection passage extending along a radial direction of the impeller. The swirling gas introduction portion is connected to a portion on a downstream side of the front edge portion of the impeller in the intake flow passage.

When an apex of a first blade element projecting from the positive pressure surface is A, a distance from the center axis to the apex A is r, and a point having the distance r from the center axis on a front edge in the rotation direction of the first blade element is B, the first blade element among the blade elements that is arranged on a front edge side in the rotation direction of the blade, is formed to have a blade angle equal to or larger than a predetermined first angle and equal to or smaller than a second angle that is larger than the first angle, the blade angle being formed by a direction along a chord of the first blade element along a direction that connects the apex A with the point B, and a plane orthogonal to the center axis.