A centrifugal compressor includes a rotary shaft of a compressor impeller, a gas bearing structure that supports the rotary shaft, a motor that rotates the rotary shaft, a motor housing that houses the motor, a compressor housing that houses the compressor impeller and includes an intake port and a discharge port, a gas bleed port that is provided closer to the discharge port than the compressor impeller in a flow direction in the compressor housing, a bearing cooling line that connects the gas bleed port to the gas bearing structure, and a heat exchanger that is disposed on the bearing cooling line. The heat exchanger is mounted on at least one of the motor housing and the compressor housing.

The turbomachine comprises a casing arrangement and a shaft supported for rotation therein. The shaft is rotatingly supported by a first and second bearing unit. First and second compressor sections are provided in the casing arrangement. The first compressor section comprises a first compressor impeller mounted on the shaft for rotation therewith, and the second compressor section comprises a second compressor impeller mounted on the shaft for rotation therewith. The turbomachine further comprises a first turboexpander and a second turboexpander mounted on the shaft for rotation therewith in the casing arrangement.

The gas turbine engine described includes a first centrifugal compressor, a second centrifugal compressor, and intercompressor pipes extending therebetween. The intercompressor pipes fluidly interconnect an exit of a first impeller of the first centrifugal compressor and an inlet of a second impeller of the second centrifugal compressor. The intercompressor pipes have heat transfer structures on outer surfaces thereof to increase convective heat transfer.

The aspects of the disclosed embodiments are directed to a fan for displacing a fluid, which fan includes a rotor rotating around its axis of rotation and surfaces, such as blades, forming a flow when the rotor rotates. The rotor is arranged to displace fluid simultaneously with at least two different flows (F1, F2).

A heat transfer system (e.g., a heat pump) can include at least a first fin array and at least a first pump disposed in fluid communication with the first fin array and configured to cause a first fluid to flow through the first fin array. The system can include at least a first heat transfer layer attached to and/or in thermal communication with the first fin array. The first heat transfer layer can define a second fluid flow path therein for a second fluid to flow fluidly isolated from the first fluid. The first heat transfer layer and the first fin array can be configured to cause heat transfer between the first fluid and the second fluid.

A turbo fluid machine includes: a housing; an electric motor; an impeller that compresses fluid; and a drive shaft connecting the impeller and the electric motor in the housing. The impeller chamber includes a first impeller chamber and a second impeller chamber distanced from each other in an axial direction of the drive shaft. The impeller includes: a first impeller that compresses the fluid to produce first compressed fluid; and a second impeller that compresses the first compressed fluid to produce second compressed fluid. The turbo fluid machine further includes: a compressed fluid passage through which the first compressed fluid is supplied to the second impeller chamber; and a plurality of flow straightening passages that extends inside the compressed fluid passage in a direction in which the compressed fluid passage extends, and through which the first compressed fluid is straightened and supplied to the second impeller chamber.

The disclosure relates to a compressor housing of a radial compressor. The compressor housing includes a radially inner housing region which forms an axial inflow channel in an intake region of the radial compressor. The compressor housing also includes a diffusor region which adjoins the radially inner housing region. The diffusor region is designed to deflect a radial flow downstream of a compressor impeller into an axial direction counter to an inflow direction of the inflow channel. The compressor housing also includes a radially outer housing region which adjoins the diffusor region, extends axially counter to the inflow direction and provides one or more charge air manifolds.

An aircraft propulsion system comprises an engine, a propeller drive shaft drivingly engaged with the engine, a propeller for propelling an aircraft and a fan driving cooling air along a flow path in thermal communication with the engine. The engine may be an internal combustion engine or other engine type having heat rejection requirements and the fan may facilitate cooling of the engine. The propulsion system may have a pusher configuration.

A method and apparatus for breathing, in which a blower is mounted in a specific part made of silicone, which reduces blower immissions and emissions. Moreover, the conducting structure influences the flow of the respiratory gas in order to reduce interference when measuring the volumetric flow.

Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits.