An assembly is provided for an aircraft propulsion system. This assembly includes a geartrain, a propulsor rotor, a compressor rotor, a rotating structure and an electric machine. The geartrain includes a first component, a second component and a third component. The propulsor rotor is coupled to the geartrain through the first component. The compressor rotor is coupled to the geartrain through the second component. The rotating structure is coupled to the geartrain through the third component. The rotating structure includes a turbine rotor. The electric machine is positioned remote from the geartrain. The electric machine includes an electric machine rotor, and the electric machine rotor is coupled to the geartrain through the third component.

An assembly is provided for an aircraft propulsion system. This assembly includes a geartrain, a propulsor rotor, a compressor rotor, a rotating structure and an electric machine. The geartrain includes a first component, a second component and a third component. The propulsor rotor is coupled to the geartrain through the first component. The compressor rotor is coupled to the geartrain through the second component. The rotating structure is coupled to the geartrain through the third component. The rotating structure includes a turbine rotor. The electric machine is positioned remote from the geartrain. The electric machine includes an electric machine rotor, and the electric machine rotor is coupled to the geartrain through the third component.

A hybrid multi-spool gas turbine engine, has: a LP spool and a HP spool rotatable about a central axis, the LP spool having an LP compressor and an LP turbine engaged to the LP compressor via an LP shaft, the LP shaft engaged to a rotatable load at a first end thereof, the HP spool having an HP turbine and an HP compressor engaged to the HP turbine via a HP shaft; an accessory gearbox (AGB) engaged to both of the LP shaft and the HP shaft and located proximate a second end thereof, the AGB having at least one accessory output drivingly engageable to at least one accessory and at least one input; and at least one electric motor drivingly engaged to the at least one input of the AGB, the at least one electric motor drivingly engaged to the rotatable load via the AGB and the LP shaft.

A hybrid multi-spool gas turbine engine, has: a LP spool and a HP spool rotatable about a central axis, the LP spool having an LP compressor and an LP turbine engaged to the LP compressor via an LP shaft, the LP shaft engaged to a rotatable load at a first end thereof, the HP spool having an HP turbine and an HP compressor engaged to the HP turbine via a HP shaft; an accessory gearbox (AGB) engaged to both of the LP shaft and the HP shaft and located proximate a second end thereof, the AGB having at least one accessory output drivingly engageable to at least one accessory and at least one input; and at least one electric motor drivingly engaged to the at least one input of the AGB, the at least one electric motor drivingly engaged to the rotatable load via the AGB and the LP shaft.

An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.

A hybrid-electric VTOL aircraft includes an airframe including at least a pair of fixed wings, one or more VTOL powertrains supported by the airframe each including one or more rotor blades and an electric motor for rotating the one or more rotor blades about a rotational axis, one or more forward flight powertrains separate from the one or more VTOL powertrains and supported by the airframe each including a prime, and a computer system in signal communication with the one or more VTOL powertrains and the one or more forward flight powertrains.

A hybrid-electric VTOL aircraft includes an airframe including at least a pair of fixed wings, one or more VTOL powertrains supported by the airframe each including one or more rotor blades and an electric motor for rotating the one or more rotor blades about a rotational axis, one or more forward flight powertrains separate from the one or more VTOL powertrains and supported by the airframe each including a prime, and a computer system in signal communication with the one or more VTOL powertrains and the one or more forward flight powertrains.

A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.

A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.

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.