An aircraft propulsion system assembly includes an aircraft propulsion system and a control assembly. The aircraft propulsion system includes a propulsor, an engine, and an electrical assembly. The engine is coupled to the propulsor. The electrical assembly includes an electric motor and a battery management system. The electric motor is coupled to the propulsor. The control assembly includes a plurality of channel A control units and at least one channel B control unit. The plurality of channel A control units includes an engine control unit for the engine and an electric motor control unit for the electric motor. The at least one channel B control unit is configured to identify valid and invalid output control signals of the engine control unit. The battery management system is configured to identify valid and invalid output control signals of the electric motor control unit.

A starter system for a gas turbine engine in, for example, a hybrid electric engine is provided. The hybrid electric engine may include the gas turbine engine, an electric machine, and an electrical energy storage. The starter system may include the electric machine, and a low-pressure shaft of the gas turbine engine may be mechanically coupled to a rotor of the electric machine. The electrical energy storage may electrically power the electrical machine and receive electrical power from the electrical machine. In addition, a clutch may selectively couple the low-pressure shaft to a high-pressure shaft of the gas turbine engine. The clutch may, when engaged, transfer mechanical power from the low-pressure shaft, which is mechanically coupled to the electric machine, to the high-pressure shaft. Further, the clutch may disengage if a rotational speed of the high-pressure shaft exceeds a rotational speed of the low-pressure shaft.

A starter system for a gas turbine engine in, for example, a hybrid electric engine is provided. The hybrid electric engine may include the gas turbine engine, an electric machine, and an electrical energy storage. The starter system may include the electric machine, and a low-pressure shaft of the gas turbine engine may be mechanically coupled to a rotor of the electric machine. The electrical energy storage may electrically power the electrical machine and receive electrical power from the electrical machine. In addition, a clutch may selectively couple the low-pressure shaft to a high-pressure shaft of the gas turbine engine. The clutch may, when engaged, transfer mechanical power from the low-pressure shaft, which is mechanically coupled to the electric machine, to the high-pressure shaft. Further, the clutch may disengage if a rotational speed of the high-pressure shaft exceeds a rotational speed of the low-pressure shaft.

A propulsion assembly includes a hybrid-electric propulsion system, an electrical distribution system, and a controller. The hybrid-electric propulsion system includes an engine, a first electric motor, and a first propulsor. The engine and the first electric motor are couplable with the first propulsor to drive rotation of the first propulsor. The electric propulsion system includes a second electric motor and a second propulsor. The second electric motor is coupled with the second propulsor to drive rotation of the second propulsor. The controller is configured to: in a first flight mode, control the engine to drive rotation of the first propulsor, and in a second flight mode, control the at least one first electric motor to drive rotation of the first propulsor with the engine in a shutdown condition, and control the second electric motor to drive rotation of the second propulsor.

A propulsion assembly includes a hybrid-electric propulsion system, an electrical distribution system, and a controller. The hybrid-electric propulsion system includes an engine, a first electric motor, and a first propulsor. The engine and the first electric motor are couplable with the first propulsor to drive rotation of the first propulsor. The electric propulsion system includes a second electric motor and a second propulsor. The second electric motor is coupled with the second propulsor to drive rotation of the second propulsor. The controller is configured to: in a first flight mode, control the engine to drive rotation of the first propulsor, and in a second flight mode, control the at least one first electric motor to drive rotation of the first propulsor with the engine in a shutdown condition, and control the second electric motor to drive rotation of the second propulsor.

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.

A propulsion system is provided for an aircraft. This propulsion system includes a geartrain, a propulsor rotor, a turbine engine core, an electric machine and an accessory gearbox system. The propulsor rotor is disposed to a first side of the geartrain. The turbine engine core is disposed to a second side of the geartrain. The turbine engine core is operatively coupled to the propulsor rotor through the geartrain. The electric machine is disposed to the second side of the geartrain. The electric machine is operatively coupled to the propulsor rotor and/or the turbine engine core through the geartrain. The accessory gearbox system is operatively coupled to the turbine engine core. The accessory gearbox system is circumferentially offset from the electric machine about a centerline axis of the turbine engine core. The accessory gearbox system axially overlaps the electric machine along the centerline axis of the turbine engine core.

A propulsion system is provided for an aircraft. This propulsion system includes a geartrain, a propulsor rotor, a turbine engine core, an electric machine and an accessory gearbox system. The propulsor rotor is disposed to a first side of the geartrain. The turbine engine core is disposed to a second side of the geartrain. The turbine engine core is operatively coupled to the propulsor rotor through the geartrain. The electric machine is disposed to the second side of the geartrain. The electric machine is operatively coupled to the propulsor rotor and/or the turbine engine core through the geartrain. The accessory gearbox system is operatively coupled to the turbine engine core. The accessory gearbox system is circumferentially offset from the electric machine about a centerline axis of the turbine engine core. The accessory gearbox system axially overlaps the electric machine along the centerline axis of the turbine engine core.

This method for controlling the operation of a coupling device for an aircraft turbomachine comprises the steps of: a first comparison of the determined rotational speed of an electric machine with a time evolution profile, the first comparison being carried out to determine an operating deviation; a second comparison of the operating deviation with a detection threshold; and according to the result of the second comparison step, identifying the existence or absence of a failure of the coupling device; the second comparison step comprising determining the value of the detection threshold from at least one control parameter, the operating deviation and the rotational speed of the electric machine.