Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

A power system including at least one electrical machine, plurality of doubly fed induction machines (DFIMs), a plurality of first power converters, and a speed regulation unit is presented. The electrical machine includes a mechanical input end and at least one of a first stator winding terminal and a first rotor winding terminal. Each DFIM includes a second stator winding terminal, a second rotor winding terminal, and a mechanical output end. At least one of the first stator winding terminal and the first rotor winding terminal is coupled to one of first power converters and the second rotor winding terminal of each DFIM is coupled to one of the first power converters. The speed regulation unit is coupled to at least one of the mechanical input end and the mechanical output end.

A power system including at least one electrical machine, plurality of doubly fed induction machines (DFIMs), a plurality of first power converters, and a speed regulation unit is presented. The electrical machine includes a mechanical input end and at least one of a first stator winding terminal and a first rotor winding terminal. Each DFIM includes a second stator winding terminal, a second rotor winding terminal, and a mechanical output end. At least one of the first stator winding terminal and the first rotor winding terminal is coupled to one of first power converters and the second rotor winding terminal of each DFIM is coupled to one of the first power converters. The speed regulation unit is coupled to at least one of the mechanical input end and the mechanical output end.

A power generation system is provided including a power boost regulator operative to provide load matched voltage operation of an AC power source.

A power generation system is provided including a power boost regulator operative to provide load matched voltage operation of an AC power source.

An aircraft propulsion system (10) comprises at least first and second electrical generators (15a, 15b), each being configured to provide electrical power to a respective first and second AC electrical network (16a, 16b). The system (10) further comprises at least first and second AC electrical motors (19a, 19b) directly electrically coupled to a respective AC network (16a, 16b) and coupled to a respective propulsor (4), and a DC electrical network electrically coupled to the first and second AC networks (16a, 16b) via respective first and second AC to DC converters (17a, 17b), and to a further electrical motor 19c), the further electrical motor (19c) being coupled to a propulsor (4).

An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.

An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.

A propulsion system for an unmanned underwater vehicle includes a turbine engine, a generator mechanically coupled to an output shaft of the turbine engine, an electrical motor mechanically decoupled from the turbine engine and electrically coupled to the generator via a power bus architecture, and a propulsor mechanically coupled to a rotational output of the electrical motor. The power bus architecture includes a pair of AC buses and a DC bus.