A compressor system includes an electric motor having a rotatable output shaft extending from either end thereof. The compressor system further includes multiple compression stages fluidly coupled to one another in series and mechanically connected to the output shaft. The first compressor stage includes two split impellers with each impeller discharging approximately one half of the fluid flow at a desired pressure to the second compressor stage.

An air mixing system includes a building superstructure having an open space therein and an attic. An air mixing unit mounted to the ceiling draws air from the open space and the attic, mixes the air and discharges the mixed air outwards from the fan.

A compressor, which includes a housing and a rotor, in which the rotor includes a compressor wheel on at least one side, a compressor chamber being formed between the compressor wheel and the housing, the rotor being rotatably supported, an annular sealing channel being formed between the rotor and the housing, the sealing channel being routed from the compressor chamber to an area having a lower pressure, a connecting channel being routed from an area having a higher pressure to a first section of the sealing channel.

A compressor having a housing and a rotor, the rotor having an impeller at least on one side; a compressor chamber being formed between the impeller and the housing, the rotor being rotationally mounted, an annular sealing channel being formed between the rotor and the housing, the sealing channel being routed from the compressor chamber to a zone having a lower pressure; a throttling section being provided in the sealing channel; the sealing section being configured in closer proximity to the low-pressure zone than to the compression chamber.

A forward curved blower wheel has fan blades having relatively small leading edge blades angles and a relatively lengthy mean camber lines. The blower wheel also comprises leading edge notches adjacent its blower wheel inlet. The leading edge notches eliminate buffeting that would occur with such blades if such notches were not present.

A compressor having a housing and a rotor, the rotor having a compressor impeller at least on one side; a compressor chamber being configured between the compressor impeller and the housing; the rotor being rotationally mounted; an annular sealing channel being configured between the rotor and the housing; the sealing channel being routed from the compressor chamber to a lower-pressure zone; at least two throttling sections being provided in the sealing channel; in each of the two throttling sections, in the direction of flow viewed from the compressor chamber to the lower-pressure zone, a first section having a reduction in the cross section of the sealing channel being first provided, and a second section having an enlargement of the cross section of the sealing channel being subsequently provided.

A high-speed dual turbo machine enabling cooling thermal equilibrium. The high-speed dual turbo machine maximizing the cooling efficiency thereof by compressing and discharging external air suctioned therein at both ends, cooling an air compressor in a suction air-cooling method, decreasing a flow path of air for cooling the inside of the dual turbo machine and the air compressor, and optimizing the flow path. Accordingly, the present invention uses the suction air-cooling method and guides the flow of air for cooling the turbo machine through a specific path, so that it 15 maximizes the efficiency and durability of the turbo machine, the cost reduction owing to the structural simplification of the turbo machine, and the easiness of maintenance by preventing an increase in temperature of the inside of the turbomachine casing (100) and the air compressor (200).

A fluid machine includes a housing and a motor. The motor includes a rotor and a stator having a stator core. The rotor includes a tubular portion, a magnetic member, and a plug that is provided at one of a first end a second end of the tubular portion. The tubular portion includes first and second portions that protrude in an axial direction in relation to opposite ends of the stator core and opposite ends of the magnetic member. The first and second portions of the tubular portions are rotatably supported by two bearings, respectively. The magnetic member is spaced apart in the axial direction from the plug so that a space is defined in the tubular portion by the tubular portion, the magnetic member, and the plug. One of the two bearings is provided on a radially outer side of the space.

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, a rotating member, and a motor. Part of fluid compressed by a compressor impeller is introduced into a motor accommodation space through an inlet-side flow passage that has an inlet-side fixed throttle, and is discharged from the motor accommodation space through an outlet-side flow passage that has an outlet-side fixed throttle. The outlet-side flow passage includes a connection part connecting to the motor accommodation space. The connection part is formed separately from a clearance between a second partition wall and a shaft, and is located opposite to a connection part of the inlet-side flow passage connecting to the motor accommodation space across the motor in an axial direction of the shaft. The inlet-side fixed throttle and the outlet-side fixed throttle are configured such that pressure in the motor accommodation space is higher than pressure in a turbine-wheel back pressure region.