A vapor compression system comprising a centrifugal compressor (22) having: an inlet (24); an outlet (26); a first impeller stage (28); a second impeller stage (30); and a motor (34) coupled to the first impeller stage and second impeller stage. A first heat exchanger (38) is downstream of the outlet along a refrigerant flowpath. An expansion device (56) and a second heat exchanger (64) are upstream of the inlet along the refrigerant flowpath. A bypass flowpath (120; 320) is positioned to deliver refrigerant from the compressor bypassing the first heat exchanger. A valve (128) is positioned to control flow through the bypass flowpath, wherein: the bypass flowpath extends from a first location (140) intermediate the inlet and outlet to a second location (142; 342) downstream of the first heat exchanger along the refrigerant flowpath.

The invention relates to a stabilizer of a compressor, in particular of a radial compressor or diagonal compressor. The stabilizer comprises a first annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel. The stabilizer further comprises a second annular stabilizer chamber which encloses the first annular stabilizer chamber. The invention further relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer according to the invention, and to a turbomachine, in particular a turbocharger, comprising the compressor.

A two stage chiller includes first and second stage centrifugal compressors, at least one motor, a return channel flow path, and a plurality of injection ports. The first and second stage centrifugal compressors include first and second impellers, and first and second diffusers downstream from the first and second impellers. The at least one motor rotates the first impeller and the second impeller. The return channel flow path connects the first diffuser to the second impeller. The plurality of injection ports are located circumferentially around the second diffuser and within at least one of the first diffuser, and the return channel flow path. The plurality of injection ports located within the second diffuser are downstream of the second upstream edge of the second diffuser to deliver liquid refrigerant to the second diffuser.

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 compressed vaporous discharge stream is de-superheated in a de-superheater system. The de-superheater system comprises a de-superheater heat exchanger configured to bring at least a portion of the compressed vaporous discharge stream in indirect heat exchanging contact with an ambient stream. A de-superheater bypass line comprising an temperature-controlled valve is configured to selectively bypass the de-superheater heat exchanger. A combiner is configured downstream of the de-superheater heat exchanger for rejoining the bypass portion with the portion of the compressed vaporous discharge stream that has passed through the de-superheater heat exchanger. A mixer is configured downstream of said combiner, to receive and mix the rejoined stream, and discharge the rejoined stream into a de-superheater discharge conduit as a de-superheated stream.

A diffuser of a compressor of centrifugal or mixed type includes two end plates which enclose a plurality of regularly distributed circumferential blades, and at least one transverse upstream passage produced in lower or upper surfaces of the blades. An injection/withdrawal coupling is achieved by a recirculation of a stream in an air passage of the diffuser on the basis of injection of air from at least one point in a leading edge zone of an upstream side of the diffuser. Blowing of air is then effected in at least one groove formed along a lateral flank of each blade by withdrawal of the air stream in a region of a trailing edge. Thereby, effectively separation of the air in a boundary layer in a gas turbine compressor diffuser is realized by re-energizing the boundary layer with air at a higher pressure by a suction/re-injection coupling.

The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

Centrifugal turbomachines, such a centrifugal compressors, centrifugal blower, and centrifugal pumps, having unique treatments that enhance their performance ranges. In one arrangement, the treatment involves injecting a relatively high-momentum flow proximate to the blade-tip clearance gap at the inlet to the impeller of the turbomachine in a manner that reenergizes flow at the gap. The injected high-momentum flow can be taken from a location downstream of the outlet of the impeller and/or from a flow external to the turbomachine. In another arrangement, the non-self-bleed-type treatment involves providing the centrifugal turbomachine with a secondary flow path upstream of the inlet to the impeller. In one example, the flow of working fluid to the secondary flow path is modulated according to the mass flow of the working fluid. During times of higher flow, the secondary flow path is opened, and at times of lower flow, the secondary flow path is closed.

A compressor housing for a radial compressor includes: an accommodation chamber for a compressor impeller; an outflow region; a collecting cavity; a fluidic connection between the collecting cavity and the outflow region; and a valve device structured and arranged to change a flow cross-section of the fluidic connection between the collecting cavity and the outflow region.

An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 200 configured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine 19 in the event of a shaft break to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The pressure equalization apparatus comprises a sensor 216 configured to directly detect a shaft break event. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.