An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.

The present disclosure relates to a diffuser for a radial compressor. The diffuser may comprise a diffusor duct portion formed by first and second side walls that are arranged so as to diverge at least partially from one another in a direction of flow, a blade ring having a number of blades arranged at least partially in the diffusor duct portion with each blade having a pressure side and a suction side delimited by a blade leading edge and by a blade trailing edge of the respective blade, a number of pressure equalizing openings incorporated into at least one of the first and second side walls of the diffuser duct portion in a region where the first and second side walls diverge from one another with each of the pressure equalizing openings being arranged between the pressure side of one blade and the suction side of an adjacent blade of the blade ring, and a first annular duct arranged behind the pressure equalizing openings and fluidically connected to the diffuser duct portion via at least two of the pressure equalizing openings, such that a number of regions between two adjacent blades of the blade ring in the diffuser duct portion are fluidically connectable together.

A centrifugal compressor for a chiller includes a first stage impeller, a first stage diffuser, a second stage impeller, a second stage diffuser, and a second stage volute. The first stage impeller is arranged to receive refrigerant from an inlet. The second stage volute is disposed downstream of the second stage diffuser to receive the refrigerant after the refrigerant has been compressed. The second stage volute has a reverse overhung configuration.

Turbochargers include a compressor comprising a compressor body extending from a compressor back face and a plurality of blades extending from the compressor body, a turbine comprising a turbine body extending from a turbine back face and a plurality of blades extending from the turbine body, and a shaft coupled at a first end to the compressor back face and at a second end to the turbine back face. The shaft includes an internal passage extending from the first end towards the second end in fluid communication with the compressor blades and one or more fans disposed within the internal passage and configured to draw air toward the second end of the shaft. The internal passage of the shaft is in fluid communication with the compressor blades via one or more bleed air passages, which can be biased towards an outer diameter of the compressor body.

A bore basket assembly for a gas turbine engine. The assembly includes an outer cylindrical member. The assembly also includes an inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, one of the cylindrical members operatively coupled to an aft rotor stage, the other of the cylindrical members operatively coupled to a forward rotor stage, the cylindrical members moveable in an axially telescoping manner relative to each other.

The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

An air distribution system for cooling a component in a heated gas environment may be provided, where the air distribution system includes a wall and a plate. The wall includes an inner surface, an outer surface configured to be exposed to the heated gas environment, and a protrusion extending from the inner surface of the wall. The plate is fixedly coupled to the protrusion and is space apart from the inner surface of the wall. The plate includes an outer edge. A passage is defined between the plate and the inner surface of the wall. The inlet of the passage is defined by the outer edge of the plate.

A turbocharger includes a bearing housing, a compressor housing connected to the bearing housing via a seal plate, a compressor impeller, a diffuser passage, a diffuser surface, and a cooling passage. The bearing housing has a first facing surface, and a first extending surface that is formed continuously with the first facing surface. The seal plate has a second facing surface that faces the first facing surface, and a second extending surface that is formed continuously with the second facing surface. The second extending surface faces the first extending surface in a radial direction of the impeller shaft. The cooling passage is defined by the first facing surface, the first extending surface, the second facing surface, and the second extending surface.

A process for compressing a gaseous fluid comprising a step (a) of injecting refrigerant during which a refrigerant substance is sprayed into the gaseous fluid to be compressed, and also a compression step (b), during which the passage of said gaseous fluid loaded with refrigerant substance is forced through said compressor in order to compress said gaseous fluid, the mass flow rate (Q3) of the refrigerant substance injected into the gaseous fluid represents between 1% and 5% of the mass flow rate of the gaseous fluid to be compressed, and the refrigerant substance is sprayed in the form of particles having a maximum dimension of less than or equal to 25 pm, and preferably less than or equal to 10 pm.