An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

An electric compressor for compressing a gas, particularly configured for use in a motor vehicle, comprising a control unit, an electric motor controlled by the control unit, a compressor wheel driven by the electric motor, and a housing at least partially surrounding the electric motor. The housing is produced by an encapsulation method such that a cooling structure is formed integrally with the housing, in particular within the housing, for ensuring cooling of the electric motor and of the control unit. A method for producing the electric compressor of this kind is also disclosed.

An electric compressor for compressing a gas, particularly configured for use in a motor vehicle, comprising a control unit, an electric motor controlled by the control unit, a compressor wheel driven by the electric motor, and a housing at least partially surrounding the electric motor. The housing is produced by an encapsulation method such that a cooling structure is formed integrally with the housing, in particular within the housing, for ensuring cooling of the electric motor and of the control unit. A method for producing the electric compressor of this kind is also disclosed.

Provided is a discharge section structure for a centrifugal compressor provided with a scroll flow passage and a discharge flow passage connected to the scroll flow passage. The discharge section structure includes a tongue section provided in a branching section between the scroll flow passage and the discharge flow passage; a first flow passage section having a center of curvature on an origin side of the scroll flow passage; and a second flow passage section communicating with the first flow passage section and having a center of curvature on an outer side of the scroll flow passage. The first flow passage section includes at least a part of the scroll flow passage, and the second flow passage section includes at least a part of the discharge flow passage. The tongue section faces the second flow passage section and is located in the middle of the second flow passage section.

A turbocharger, with a turbine for expanding a first medium that includes a turbine rotor and a turbine housing, a compressor for compressing a second medium that includes a compressor rotor coupled to the turbine rotor via a shaft and a compressor housing, a bearing housing in which the shaft is mounted, a bearing housing cap delimiting the bearing housing facing the turbine, and a turbine cover delimiting the turbine on a side facing the bearing housing and has a section projecting into a recess of the bearing housing cap. On a section of the bearing housing cap delimiting the recess of the bearing housing cap on the outside, which on the outside follows the section of the turbine cover projecting into the recess of the bearing housing cap, an oil trapping lip is formed on a side of the bearing housing cap facing the turbine rotor.

A turbocharger, with a turbine for expanding a first medium that includes a turbine rotor and a turbine housing, a compressor for compressing a second medium that includes a compressor rotor coupled to the turbine rotor via a shaft and a compressor housing, a bearing housing in which the shaft is mounted, a bearing housing cap delimiting the bearing housing facing the turbine, and a turbine cover delimiting the turbine on a side facing the bearing housing and has a section projecting into a recess of the bearing housing cap. On a section of the bearing housing cap delimiting the recess of the bearing housing cap on the outside, which on the outside follows the section of the turbine cover projecting into the recess of the bearing housing cap, an oil trapping lip is formed on a side of the bearing housing cap facing the turbine rotor.

This invention relates to a compressor 100 for a supercharger 10. The compressor 100 comprises a compressor housing 110 with a compressor inlet 112 and a compressor outlet 114. The compressor 100 furthermore comprises an adjustment mechanism 200 and an actuator device 300. The adjustment mechanism 200 comprises an adjustment ring 210 and a plurality of shutter elements 220 for changing an inlet cross section 112a of the compressor inlet 112. The actuator device 300 comprises a drive unit 310 and a coupling unit 320. The actuator device 300 is thus coupled, via the coupling unit 320, to the adjustment mechanism 200 in order to move the adjustment mechanism 200 between a first position and a second position.

A turbocharger has a turbine housing scroll that is meridionally divided into first and second scrolls. A nozzle ring disposed in the turbine nozzle has an array of circumferentially spaced first vanes and an array of circumferentially spaced second vanes. The first vane passages between first vanes are configured to blow exhaust gas onto the turbine blade leading edges. Likewise, the second vane passages are configured to blow exhaust gas on the turbine blade leading edges. The first and second vanes are circumferentially staggered relative to each other such that the turbine blade leading edges receive exhaust gas from the first and second blade passages in interleaved fashion about a circumference of the turbine wheel.

A turbocharger has a turbine housing scroll that is meridionally divided into first and second scrolls. A nozzle ring disposed in the turbine nozzle has an array of circumferentially spaced first vanes and an array of circumferentially spaced second vanes. The first vane passages between first vanes are configured to blow exhaust gas onto the turbine blade leading edges. Likewise, the second vane passages are configured to blow exhaust gas on the turbine blade leading edges. The first and second vanes are circumferentially staggered relative to each other such that the turbine blade leading edges receive exhaust gas from the first and second blade passages in interleaved fashion about a circumference of the turbine wheel.

A method is disclosed for controlling exhaust gas flow from a combustion engine to a turbocharger. The combustion engine includes a plurality of cylinders each with first and second exhaust valves, and the turbocharger includes first and second volutes with outlets that are separated by approximately 180. The method includes: (i) directing exhaust flow from first and second cylinders into the first volute via a first exhaust channel by opening the first exhaust valve in the first and second cylinders; (ii) directing exhaust flow from third and fourth cylinders into the second volute via a second exhaust channel by opening the first exhaust valve in the third and fourth cylinders; and (iii) apportioning exhaust flow from each cylinder into the first and second volutes via the first and second exhaust channels by moving the second exhaust valve in each cylinder between a variety of positions.