Abstract: A current-compensated inductor for filtering interference signals which are transmitted between two high-voltage components of a high-voltage on-board electrical system of a motor vehicle, includes a toroidal, in particular circular ring-shaped or oval ring-shaped, magnet core which surrounds an inner opening, and has at least two busbars for electrically connecting the two high-voltage components. The busbars are routed axially through the inner opening of the magnet core and are arranged at a distance from one another in the inner opening so as to form an air gap. An inner side of the magnet core, which inner side faces the inner opening, and regions of outer sides of the busbars, which regions face the inner side of the magnet core, have shapes which correspond to one another.

Abstract: A rotor for an electric motor includes an even number n of pole pairs arranged on a rotor body with rotor windings connected in series between two electrical connections to supply or conduct away current through the rotor windings. The series circuit has a first section including n/2 rotor windings arranged first in the series circuit, and a second section including n/2 rotor windings and arranged upstream of the second electrical connection. During application of a direct-current voltage between the two connections in each of the rotor windings of the first section, the radial component of the direct-current flow in the series circuit extends through the entire respective rotor winding, from an outer side to an inner side of the rotor winding, and in each of the rotor windings of the second section, in reverse, from an outer side to an inner side of the rotor winding.

Abstract: A current-compensated inductor for filtering interference signals which are transmitted between two high-voltage components of a high-voltage on-board electrical system of a motor vehicle, includes a toroidal, in particular circular ring-shaped or oval ring-shaped, magnet core which surrounds an inner opening, and has at least two busbars for electrically connecting the two high-voltage components. The busbars are routed axially through the inner opening of the magnet core and are arranged at a distance from one another in the inner opening so as to form an air gap. An inner side of the magnet core, which inner side faces the inner opening, and regions of outer sides of the busbars, which regions face the inner side of the magnet core, have shapes which correspond to one another.

Abstract: A control method and a switching device are provided for a separately excited synchronous machine as a drive in a hybrid or electric vehicle. The switching device converts and/or distributes electrical energy within the vehicle, in particular the hybrid or electric vehicle, wherein an asymmetric full bridge is provided, in the bridge branch of which a rotor of an SSM is arranged. Switches are provided in the asymmetric full bridge in order to provide a pulse width modulation corresponding to a desired motor rotational speed and power of the SSM. The device is characterized in that it has a short-circuit branch extending in parallel with the bridge branch of the asymmetric full bridge, by which short-circuit branch the rotor of the SSM is able to be short-circuited.

Abstract: A rotor for an electric motor includes an even number n of pole pairs arranged on a rotor body with rotor windings connected in series between two electrical connections to supply or conduct away current through the rotor windings. The series circuit has a first section including n/2 rotor windings arranged first in the series circuit, and a second section including n/2 rotor windings and arranged upstream of the second electrical connection. During application of a direct-current voltage between the two connections in each of the rotor windings of the first section, the radial component of the direct-current flow in the series circuit extends through the entire respective rotor winding, from an outer side to an inner side of the rotor winding, and in each of the rotor windings of the second section, in reverse, from an outer side to an inner side of the rotor winding.

Abstract: A control method and a switching device are provided for a separately excited synchronous machine as a drive in a hybrid or electric vehicle. The switching device converts and/or distributes electrical energy within the vehicle, in particular the hybrid or electric vehicle, wherein an asymmetric full bridge is provided, in the bridge branch of which a rotor of an SSM is arranged. Switches are provided in the asymmetric full bridge in order to provide a pulse width modulation corresponding to a desired motor rotational speed and power of the SSM. The device is characterized in that it has a short-circuit branch extending in parallel with the bridge branch of the asymmetric full bridge, by which short-circuit branch the rotor of the SSM is able to be short-circuited.

Abstract: A drive arrangement for an electrically driven vehicle includes an electric motor that is configured to accelerate the vehicle, the electric motor has a rotor, which is arranged inside a stator having stator windings and is arranged on a rotor shaft. The drive arrangement also includes a drive shaft coupled to a drive wheel of the vehicle, and a shaft coupling that transmits torque output by the rotor shaft such that said torque is conducted to the drive shaft, wherein the shaft coupling has a torque receiving element that receives the torque output by the electric motor, and a torque output element that is mechanically coupled to the torque receiving element and outputs the torque in a direction of the drive shaft. An electrically insulating grease is arranged between the torque receiving element and the torque output element.

Abstract: A drive arrangement for an electrically driven vehicle includes an electric motor that is configured to accelerate the vehicle, the electric motor has a rotor, which is arranged inside a stator having stator windings and is arranged on a rotor shaft. The drive arrangement also includes a drive shaft coupled to a drive wheel of the vehicle, and a shaft coupling that transmits torque output by the rotor shaft such that said torque is conducted to the drive shaft, wherein the shaft coupling has a torque receiving element that receives the torque output by the electric motor, and a torque output element that is mechanically coupled to the torque receiving element and outputs the torque in a direction of the drive shaft. An electrically insulating grease is arranged between the torque receiving element and the torque output element.

Abstract: The present invention relates to a capacitor arrangement having a capacitor and a first terminal plate and a second terminal plate. The capacitor has a first contact face and a second contact face arranged opposite one another. The terminal plates are each connected to one of the contact faces and have protrusions on one end suitable for engaging in recesses in a power rail.

Abstract: The present technology generally relates to jet engines, in particular for an aircraft, having at least one turbine shaft on which at least one compressor and a turbine are arranged, and a housing extends over the lateral surfaces of the jet engine, wherein furthermore at least one electrical generator unit for generating electricity is arranged on at least one turbine shaft, wherein the electrical generator unit has a locating plate and a generator, wherein the generator unit is detachably mounted on the engine-side locating plate. Therefore, a jet engine having a generator unit is provided which permits simple installation, removal and servicing of the generator unit in or out of the jet engine.

Abstract: The present invention relates to a capacitor arrangement having a capacitor and a first terminal plate and a second terminal plate. The capacitor has a first contact face and a second contact face arranged opposite one another. The terminal plates are each connected to one of the contact faces and have protrusions on one end suitable for engaging in recesses in a power rail.

Abstract: An electric centrifugal pump for conveying a fluid, in particular for conveying fuel to an aircraft engine, is disclosed. The pump includes a housing in which a rotor shaft is rotationally mounted and an impeller for conveying the fuel which is arranged on the rotor shaft. A motor arrangement is provided for driving the rotor shaft in a rotary manner around a rotor axis. The impeller includes at least one rotor, and at least one stator is arranged in the housing in a plane-parallel manner adjacent to the rotor such that the rotor and the stator form the motor arrangement.

Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.

Abstract: An electric drive, particularly for a fuel metering unit for delivering and metering fuel from a fuel tank into a combustion chamber of an airplane engine, is disclosed. The electric drive drives at least one work module and is composed of at least two engine modules that are supplied separately with electricity and disposed on a common rotor shaft to form a redundant engine arrangement.

Abstract: In a transverse flux machine, the rotor has multiple permanent magnet rings that are arranged axially in proximity to one another. The stator surrounds the rotor concentrically in at least some sections, forming an air gap. The stator has multiple stator coils oriented coaxially with the permanent magnet rings and the stator coil has two terminals. An active reactive power source to be controlled has two terminals for each stator coil, the respective stator coil being connected to each. In the event of a fault incident in one of the stator coils, a monitoring arrangement supplies triggering signals for the active reactive power source so that the two terminals of the respective stator coil are interconnected with a low resistance.

Abstract: The present technology generally relates to jet engines, in particular for an aircraft, having at least one turbine shaft on which at least one compressor and a turbine are arranged, and a housing extends over the lateral surfaces of the jet engine, wherein furthermore at least one electrical generator unit for generating electricity is arranged on at least one turbine shaft, wherein the electrical generator unit has a locating plate and a generator, wherein the generator unit is detachably mounted on the engine-side locating plate. Therefore, a jet engine having a generator unit is provided which permits simple installation, removal and servicing of the generator unit in or out of the jet engine.

Abstract: A gas turbine, particularly an aircraft engine includes at least one compressor. The gas turbine comprises at least one stator, at least one rotor and at least one generator (19) for generating electrical energy. An engine rotor has a rotor shaft (11) and rotor disks (12, 13, 14), which are driven by the rotor shaft (11) and which have rotating rotor blades (15). A stator has a housing (17) and fixed guide vanes (18). A generator (19) has at least one stator (21) and at least one rotor (20). The electrical energy generated by the generator (19) preferably serves to operate at least one attachment or one auxiliary unit of the gas turbine. According to the invention, the generator (19) is integrated in the interior of the gas turbine in such a manner that each rotor (20) of the generator is allocated to the compressor rotor and the stator (21) of the generator is allocated to the compressor stator, whereby kinetic energy of the rotor is convertible into electrical energy by the generator (19).

Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.

Abstract: In a transverse flux machine, the rotor has multiple permanent magnet rings that are arranged axially in proximity to one another. The stator surrounds the rotor concentrically in at least some sections, forming an air gap. The stator has multiple stator coils oriented coaxially with the permanent magnet rings and the stator coil has two terminals. An active reactive power source to be controlled has two terminals for each stator coil, the respective stator coil being connected to each. In the event of a fault incident in one of the stator coils, a monitoring arrangement supplies triggering signals for the active reactive power source so that the two terminals of the respective stator coil are interconnected with a low resistance.

Abstract: The invention relates to a gas turbine, particularly an aircraft engine. The gas turbine comprises at least one stator, at least one rotor and at least one generator (19) for generating electrical energy. A rotor has a rotor shaft (11) and rotor disks (12, 13, 14), which are driven by the rotor shaft (11) and which have rotating rotor blades (15). A stator has a housing (17) and fixed guide vanes (18). A generator (19) has at least one stator (21) and at least one rotor (20). The electrical energy generated by the generator (19) preferably serves to operate at least one attachment device or one auxiliary unit of the gas turbine. According to the invention, the generator (19) is integrated in the interior of the gas turbine in such a manner that the or each rotor (20) of the generator is allocated to the rotor and the or each stator (21) of the generator is allocated to the stator, whereby kinetic energy of the rotor is convertible into electrical energy by the generator (19).