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.

An example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

An example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

A gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.

A compressor 1 includes a casing 2 that covers a rotating shaft 4 and an impeller 6 and is provided with a diffuser 66 for guiding the working fluid discharged from the impeller 6 to an outside in a radial direction, a heat exchanger 71 that is cools at least a portion of the working fluid compressed by the impeller 6, a cooling fluid supplying unit 7 that supplies the working fluid cooled by the heat exchanger 71 into the casing 2 as a cooling fluid for cooling a motor 5 disposed in the casing 2, and a cooling fluid circulating unit 8 that discharges the cooling fluid that has passed through the motor 5 to an outside of the casing 2, and supplies the discharged cooling fluid downstream of an outlet 6o of a first impeller 6A and upstream of the diffuser 66.

An airflow arrangement for a gas turbine engine in which air can be selectively directed to and from a bypass channel of the engine and into a duct communicating air into a compressor of a gas turbine engine.

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.

A centrifugal compressor for a chiller includes an impeller, a motor, a diffuser, and at least one injection port. The impeller is attached to a shaft rotatable about a rotation axis. The motor is arranged and configured to rotate the shaft in order to rotate the impeller. The diffuser is disposed downstream from the impeller. The at least one injection port is located within the diffuser. The at least one injection port is configured and arranged to supply liquid refrigerant into the diffuser from a condenser or an economizer of the chiller.

Turbomachine casing treatments are described. A turbomachine that includes an example of a turbomachine casing treatment includes a wheel, a casing, and a fluid pressurizer. The wheel has a hub that defines a rotational axis and a plurality of blades. The casing has a first end, a second end, and defines an inner surface that surrounds the plurality of blades, an inlet opening, an outlet opening, a passageway, and a channel that extends from the inlet opening to the outlet opening. The passageway extends from a first passageway opening that is defined on the inner surface and a second passageway opening that is defined on the inner surface and is disposed between the first passageway opening and the first end of the casing. The fluid pressurizer is disposed within the passageway.

An internal combustion engine having a turbocharger with variability at the compressor inlet, and a turbocharger. An internal combustion engine having a turbocharger, and a turbocharger, are described. A device which both performs a change in the cross section of the compressor inlet and brings about an adjustment of the exhaust gas recirculation rate is arranged in the region of the compressor inlet. As a result, the turbocharger is of space-saving and low-cost construction in the compressor inlet region.