The present disclosure relates to a media gap motor for a turbocharger. The proposed media gap motor contains a rotor and a stator, wherein the stator comprises multiple fins which extend from an inner portion radially towards the rotor in a flow chamber formed between the stator and the rotor. The fins do not extend by means of their inner portions as far as the rotor, and therefore a gap is formed between an inner end of the fins and the rotor, wherein in internal diameter of the fins is at least 1.2 times and at most 3 times an external diameter of the rotor.

An intake system for use with an internal combustion engine having one or more cylinders. The intake system including a compressor assembly having an inlet and an outlet, and where the outlet is configured to be open to and in fluid communication with at least one of the one or more cylinders. The intake system also includes a passageway extending between and in fluid communication with the inlet and the outlet and configured to direct a first flow of gasses and a controller in operable communication with the compressor assembly. Where the intake system is operable in a first mode in which the majority of gasses of the first flow of gasses flow through the passageway toward the outlet, and a second mode in which the majority of gasses of the first flow of gasses flow through the passageway toward the inlet.

An intake system for use with an internal combustion engine having one or more cylinders. The intake system including a compressor assembly having an inlet and an outlet, and where the outlet is configured to be open to and in fluid communication with at least one of the one or more cylinders. The intake system also includes a passageway extending between and in fluid communication with the inlet and the outlet and configured to direct a first flow of gasses and a controller in operable communication with the compressor assembly. Where the intake system is operable in a first mode in which the majority of gasses of the first flow of gasses flow through the passageway toward the outlet, and a second mode in which the majority of gasses of the first flow of gasses flow through the passageway toward the inlet.

A pump assembly for a motor vehicle, comprising at least one mechanical drive, at least one electric drive, and at least one planetary gearbox, wherein the mechanical drive and the electric drive are coupled to one another via the planetary gearbox, the electric drive comprising a rotor shaft that is designed as a hollow shaft, wherein the rotor shaft is mounted at one side on a housing of the pump assembly via a ball bearing and at the other side in a gear stage of the planetary gearbox.

A pump assembly for a motor vehicle, comprising at least one mechanical drive, at least one electric drive, and at least one planetary gearbox, wherein the mechanical drive and the electric drive are coupled to one another via the planetary gearbox, the electric drive comprising a rotor shaft that is designed as a hollow shaft, wherein the rotor shaft is mounted at one side on a housing of the pump assembly via a ball bearing and at the other side in a gear stage of the planetary gearbox.

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 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.

A supercharger transmission case that includes both small and large impeller shaft bearing bores in a single component to avoid potential misalignment, and to allow the bores to be machined during the same machining setup by the same tool. The supercharger transmission case may be fabricated of low thermal expansion material, such as a hypereutectic metal matrix comprising aluminum and silicon, to further reduce thermal expansion of the transmission case and bearings.

A supercharger transmission case that includes both small and large impeller shaft bearing bores in a single component to avoid potential misalignment, and to allow the bores to be machined during the same machining setup by the same tool. The supercharger transmission case may be fabricated of low thermal expansion material, such as a hypereutectic metal matrix comprising aluminum and silicon, to further reduce thermal expansion of the transmission case and bearings.

Electric multiple stage variable forced air induction systems are disclosed herein. A housing defines a conduit therethrough with an exit (output) opening and an entry (intake) opening. The exit opening is to couple to and provide airflow to an air intake opening of a combustion engine. The entry opening is to receive air for delivery through the conduit to the exit opening. A plurality of stages generate thrust to increase airflow through the conduit and to the air intake opening of the combustion engine. Each stage can comprise a turbine housing component, a turbine rotor to rotate about an axis and generate thrust on air as it passes through the conduit in a direction parallel to the axis, and a motor coupled to and configured to turn the turbine rotor. One or more processing devices receive inputs indicating engine parameters and control the motor of each stage.