The hybrid aircraft power plant can have a load, a thermal engine coupled to drive the load via a clutch, and coupled to drive a first lubricant pump, an electric motor coupled to drive the load and a second lubricant pump. In a first mode, the clutch is in an engaged configuration, and the thermal engine drives the load via the clutch and drives the first lubricant pump. In a second mode, in which the clutch is in the disengaged configuration and in which the thermal engine may be inoperative, the electric motor is operated to drive the load and the second lubricant pump.

The hybrid aircraft power plant can have a load, a thermal engine coupled to drive the load via a clutch, and coupled to drive a first lubricant pump, an electric motor coupled to drive the load and a second lubricant pump. In a first mode, the clutch is in an engaged configuration, and the thermal engine drives the load via the clutch and drives the first lubricant pump. In a second mode, in which the clutch is in the disengaged configuration and in which the thermal engine may be inoperative, the electric motor is operated to drive the load and the second lubricant pump.

A hybrid propulsion system including a turbine engine including a high-pressure spool and a low-pressure spool, the low-pressure spool including reduction gear, the reduction gear forming part of a transmission gearbox which is positioned axially at a front end of the propulsion system; first and second electric machines mechanically and respectively connected to the high-pressure and low-pressure spools, the electric machines being configured to operate in modes referred to as motor and generator, the first and second electric machines being fixed to the transmission gearbox; a control system which is configured to allow the transfer of power between the high-pressure and low-pressure spools via the first and second electric machines.

A hybrid propulsion system including a turbine engine including a high-pressure spool and a low-pressure spool, the low-pressure spool including reduction gear, the reduction gear forming part of a transmission gearbox which is positioned axially at a front end of the propulsion system; first and second electric machines mechanically and respectively connected to the high-pressure and low-pressure spools, the electric machines being configured to operate in modes referred to as motor and generator, the first and second electric machines being fixed to the transmission gearbox; a control system which is configured to allow the transfer of power between the high-pressure and low-pressure spools via the first and second electric machines.

An aircraft power plant, comprising: a fan for providing power to an aircraft; a gas turbine engine located on a first axial side of the fan, the gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft; an electric motor powered by a power source, the electric motor driving a motor shaft; and a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan, the fan in continuous driving engagement with both of the gas turbine engine and the electric motor along the first load path and the second load path.

An aircraft power plant, comprising: a fan for providing power to an aircraft; a gas turbine engine located on a first axial side of the fan, the gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft; an electric motor powered by a power source, the electric motor driving a motor shaft; and a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan, the fan in continuous driving engagement with both of the gas turbine engine and the electric motor along the first load path and the second load path.

An assembly is provided for an aircraft propulsion system. This assembly includes an electric machine, an exhaust duct and a mounting structure. The electric machine extends axially along an axis. The exhaust duct includes an annular first section and a non-annular second section fluidly coupled with and downstream of the annular first section. The annular first section extends circumferentially around the axis. The non-annular second section axially overlaps the electric machine and extends partially circumferentially about the electric machine. The mounting structure connects the electric machine to the exhaust duct. The mounting structure includes a duct mount, a machine mount and a framework. The duct mount is connected to the annular first section. The machine mount is connected to the electric machine. The framework extends axially between and is connected to the duct mount and the machine mount. The framework includes a plurality of struts arranged in a truss.

An assembly is provided for an aircraft propulsion system. This assembly includes an electric machine, an exhaust duct and a mounting structure. The electric machine extends axially along an axis. The exhaust duct includes an annular first section and a non-annular second section fluidly coupled with and downstream of the annular first section. The annular first section extends circumferentially around the axis. The non-annular second section axially overlaps the electric machine and extends partially circumferentially about the electric machine. The mounting structure connects the electric machine to the exhaust duct. The mounting structure includes a duct mount, a machine mount and a framework. The duct mount is connected to the annular first section. The machine mount is connected to the electric machine. The framework extends axially between and is connected to the duct mount and the machine mount. The framework includes a plurality of struts arranged in a truss.

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.