An electric drive (20) comprising an electric machine (10) is specified. The electric machine (10) comprises a stator (21) and a rotor (22) mounted so as to be movable with respect to the stator (21), wherein the stator (21) comprises at least two first conductor sections (23) and at least two second conductor sections (24), the stator (21) comprises at least one first short-circuiting means (25) and at least one second short-circuiting means (26), the first conductor sections (23) are electrically connected to the first short-circuiting means (25), the second conductor sections (24) are electrically connected to the second short-circuiting means (26), and the first conductor sections (23) and the second conductor sections (24) are each designed to be supplied with a separate electric phase. Moreover, a supply system (46) for the electric drive (20) and a method of operating the electric drive (20) are specified.

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

Technologies described herein are directed to a generator concurrently providing different voltages to multiple components, some of which are unable to receive the full supply voltage output by the generator, without the addition of an electronic power converter or a transformer to the apparatus or system.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

An example system includes a dynamo-electric machine. The dynamo-electric machine includes a rotor that is cylindrical and that is configured for rotation and a stator that is arranged relative to the rotor. The stator has a stepped configuration that defines a first diameter for the stator and a second diameter for the stator. The first diameter is greater than the second diameter. Zones of the stator at the first diameter hold direct-axis (D-axis) windings and zones of the stator at the second diameter hold quadrature axis (Q-axis) windings. An airgap between the rotor and the Q-axis windings is greater than an airgap between the rotor and the D-axis windings.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

Provided is an arrangement for producing electric energy, including: a generator having plural winding sets; plural converters each connected to one of the winding sets; at least two transformers, each connected at a low voltage side to output terminal of at least one converter; and a control portion connected to control the converters.