A converter for an aircraft includes an intermediate circuit for providing a DC voltage between a positive line and a negative line, at least two rectifiers connected to the intermediate circuit to produce the DC voltage from input AC voltages and at least two inverters connected to the intermediate circuit to produce AC output voltages from the DC voltage. The DC voltage terminals of the rectifiers are connected to a first series circuit and the DC voltage terminals of the inverters are connected to a second series circuit. The positive line and the negative line of the intermediate circuit are connected on an input side via the first series circuit and on the output side via the second series circuit. At least one of the DC voltage terminals includes a short circuit for short-circuiting terminal contacts by which the DC voltage terminal is connected to the respective series circuit.

A converter for an aircraft includes an intermediate circuit for providing a DC voltage between a positive line and a negative line, at least two rectifiers connected to the intermediate circuit to produce the DC voltage from input AC voltages and at least two inverters connected to the intermediate circuit to produce AC output voltages from the DC voltage. The DC voltage terminals of the rectifiers are connected to a first series circuit and the DC voltage terminals of the inverters are connected to a second series circuit. The positive line and the negative line of the intermediate circuit are connected on an input side via the first series circuit and on the output side via the second series circuit. At least one of the DC voltage terminals includes a short circuit for short-circuiting terminal contacts by which the DC voltage terminal is connected to the respective series circuit.

An electrical machine is provided. The electrical machine includes a stator, a rotor, and a plurality of switches. The stator includes main windings and auxiliary windings. The rotor is couplable to a prime mover configured to turn the rotor relative to the stator to generate at least six phases of alternating current (AC) power at the main windings. The plurality of switches is respectively coupled between the auxiliary windings and groups of the main windings. The plurality of switches is configured to convert the at least six phases to three phases when the plurality of switches is closed.

An electrical machine is provided. The electrical machine includes a stator, a rotor, and a plurality of switches. The stator includes main windings and auxiliary windings. The rotor is couplable to a prime mover configured to turn the rotor relative to the stator to generate at least six phases of alternating current (AC) power at the main windings. The plurality of switches is respectively coupled between the auxiliary windings and groups of the main windings. The plurality of switches is configured to convert the at least six phases to three phases when the plurality of switches is closed.

A marine propulsion device, including an engine including a crankshaft, and a power generator including a rotor configured to be rotated by the crankshaft, and a stator arranged to face the rotor, the stator including a first coil group and a second coil group each configured to generate alternating current (AC), the second coil group being configured to generate more electric power than the first coil group. The marine propulsion device further includes a rectifier configured to rectify the AC generated by the first coil group to thereby obtain a first direct current (DC), and to output the first DC to a first battery, a converting device configured to convert the AC generated by the second coil group into a second DC, and a transformation device configured to transform a voltage of the second DC, and to output the voltage-transformed DC to a second battery.

A marine propulsion device, including an engine including a crankshaft, and a power generator including a rotor configured to be rotated by the crankshaft, and a stator arranged to face the rotor, the stator including a first coil group and a second coil group each configured to generate alternating current (AC), the second coil group being configured to generate more electric power than the first coil group. The marine propulsion device further includes a rectifier configured to rectify the AC generated by the first coil group to thereby obtain a first direct current (DC), and to output the first DC to a first battery, a converting device configured to convert the AC generated by the second coil group into a second DC, and a transformation device configured to transform a voltage of the second DC, and to output the voltage-transformed DC to a second battery.

A variable frequency generator (VFG) may include a housing, a shaft, a rotor, and a stator with slots. The VFG also includes a first set of stator windings including a first subset of windings and a second subset of windings and a second set of stator windings including a first subset of windings and a second subset of windings. The windings of the first subset of the first set of stator windings are co-located with the windings of the first subset of the second set of stator windings so as to share a common slot of the plurality of slots of the stator. Further, the windings of the second subset of the first set of stator windings are co-located with the windings of the second subset of the second set of stator windings so as to share a common alternative slot of the plurality of slots of the stator.

A variable frequency generator (VFG) may include a housing, a shaft, a rotor, and a stator with slots. The VFG also includes a first set of stator windings including a first subset of windings and a second subset of windings and a second set of stator windings including a first subset of windings and a second subset of windings. The windings of the first subset of the first set of stator windings are co-located with the windings of the first subset of the second set of stator windings so as to share a common slot of the plurality of slots of the stator. Further, the windings of the second subset of the first set of stator windings are co-located with the windings of the second subset of the second set of stator windings so as to share a common alternative slot of the plurality of slots of the stator.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.