Abstract: Aircraft electric machines are described. The aircraft electric machines include a laminated rotor operably connected to a shaft, the laminated rotor comprising a plurality of rotor teeth and air gaps defined between adjacent rotor teeth about a circumference of the laminated rotor, a modular stator assembly comprising at least one stator segment having a winding wrapped about a center body of the at least one stator segment, a cooling element arranged at least one of adjacent to or within the winding, and at least one power module system comprising an active rectifier and wherein the laminated rotor and modular stator are arranged as a switched reluctance rotor-stator assembly.

Abstract: An assembly for a propulsion system of an aircraft includes an electric motor, a first gearbox module, a second gearbox module, and a propeller. The electric motor includes a rotor. The rotor includes a first axial end and a second axial end. The first gearbox module includes a first gear assembly. The first gear assembly is coupled to the first axial end. The second gearbox module includes a second gear assembly. The second gear assembly is coupled to the second axial end. The propeller is coupled to the first gear assembly. The first gear assembly is configured to drive rotation of the propeller in response to rotation of the rotor.

Abstract: A system includes an electric motor. A drive shaft is connected to be driven by the electric motor. A propulsor is connected to be driven by the shaft. The propulsor is configured to pivot to a first orientation configured to produce lift when the motor rotates the shaft in a first direction, and to pivot to a second orientation configured to produce thrust when the motor rotates the shaft in a second direction that is opposite of the first direction.

Abstract: An aircraft hybrid electrical system includes an electric power generating system in signal communication with a thermal combustion engine, a secondary power system in signal communication with the electric power generating system, and a battery in signal communication with the electric power generating system and the secondary power system. The aircraft hybrid electrical system further comprises a system controller in signal communication with the electric power generating system, secondary power system, and the battery. The system controller is configured to monitor a charge capacity of the battery and selectively operate in a current charge mode and a voltage charge mode to charge the battery. The system controller invokes the current charge mode in response to detecting the charge capacity falls below a charge capacity threshold, and invokes the voltage charge mode in response to detecting the charge capacity reaches a target value.

Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.

Abstract: A hybrid electric aircraft powerplant arrangement can include a first wing pair of powerplants for a first wing of an aircraft, the first wing pair comprising a first electric powerplant configured to drive a first air mover and a first heat engine powerplant configured to drive a second air mover separate from the first air mover. The arrangement can include a second wing pair of powerplants for a second wing of the aircraft, the second wing pair comprising a second electric powerplant configured to drive a third air mover separate from the first and second air movers, and a second heat engine powerplant configured to drive a fourth air mover separate from the first, second, and third air movers.

Abstract: An aircraft hybrid electrical system includes an electric power generating system in signal communication with a thermal combustion engine, a secondary power system in signal communication with the electric power generating system, and a battery in signal communication with the electric power generating system and the secondary power system. The aircraft hybrid electrical system further comprises a system controller in signal communication with the electric power generating system, secondary power system, and the battery. The system controller is configured to monitor a charge capacity of the battery and selectively operate in a current charge mode and a voltage charge mode to charge the battery. The system controller invokes the current charge mode in response to detecting the charge capacity falls below a charge capacity threshold, and invokes the voltage charge mode in response to detecting the charge capacity reaches a target value.

Abstract: A hybrid propulsion system for driving an air mover about a rotation axis, has: a heat engine driving a heat engine shaft; an electric motor driving a motor shaft, the heat engine and the electric motor being axially offset from one another relative to the rotation axis; a gearbox having at least one input in driving engagement with the heat engine shaft and the motor shaft, and an output drivingly engageable to the air mover; and a disconnect mechanism disposed between one of the heat engine and the electric motor and the gearbox, the disconnect mechanism having an engaged configuration in which the one of the heat engine and the electric motor is drivingly engaged to the gearbox through the disconnect mechanism and a disengaged configuration in which the disconnect mechanism disengages the one of the heat engine and the electric motor from the gearbox.

Abstract: In accordance with at least one aspect of this disclosure, a system includes a turbine configured to fluidly connect to a heat engine to be driven by exhaust from the heat engine, the turbine including a turbine shaft, and a generator operatively coupled to the turbine shaft to be driven by the turbine configured to receive rotational input power from turbine shaft and to convert the rotational input power to output power to generate electrical energy.

Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.

Abstract: An aircraft propulsion system includes at least one hybrid-electric power plant for delivering power to an air mover for propelling an aircraft. The at least one hybrid-electric power plant includes a first thermal engine and an electrical motor arranged in a parallel drive configuration or in an in-line drive configuration. The aircraft propulsion system includes a second thermal engine operatively connected to the electrical motor to power the electrical motor. A method for providing propulsion to an aircraft includes delivering power to an air mover for propelling the aircraft with at least one hybrid-electric power plant. The at least one hybrid-electric power plant includes a first thermal engine and an electrical motor arranged in a parallel drive configuration or in an in-line drive configuration. The method includes powering the electrical motor with a second thermal engine.

Abstract: A cooling system includes a thermal engine having a fluid output, and a motor drive having a fluid inlet in fluid communication with the fluid output of the thermal engine. The fluid inlet of the motor drive is downstream from the fluid output of the thermal engine. The system includes a fluid storage downstream from the motor drive and a fluid output of the motor drive. A method of cooling a motor drive includes outputting a cooling fluid from a fluid output of a thermal engine, receiving the cooling fluid from the fluid output of the thermal engine in a fluid inlet of a motor drive, passing the cooling fluid through the motor drive to a fluid output of the motor drive, receiving the cooling fluid in a fluid storage.

Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.

Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.

Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; and one or more acoustic panel assemblies located around the electric generator, the one or more acoustic panel assemblies including: an acoustic backing sheet, an outer porous liner, and an acoustic liner interposed between the outer porous liner and the acoustic backing sheet.

Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a mounting system located within the tail cone between the structural support housing and the tail cone, wherein the mounting system attaches the tail cone to the structural support housing.

Abstract: Provided are embodiments of a system including a series hybrid architecture using compounded doubly fed induction machines. Embodiments include a controller configured to control the operation of the system, and a power source configured to convert a first form of energy to a second form of energy. Embodiments also include a first machine configured to generate power, wherein the first machine is mechanically coupled to the power source, and a second machine configured to control equipment, wherein the first machine is electrically coupled to the second machine. Embodiments further include methods for operating the series hybrid architecture using the compounding doubly fed induction machines.

Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool, wherein the electric generator includes a coolant cavity in thermal communication with one or more components of the electric generator; a structural support housing at least partially enclosing the electric generator, the structural support housing including a forward wall located on a forward end of the structural support housing, wherein the forward wall includes a first opening; a first coolant conveying tube extending through the first opening to fluidly connect to the coolant cavity; and a first electrical connector tube extending through the first opening within the first coolant conveying tube to electrically connect to the electric generator.

Abstract: A system includes an electric motor. A drive shaft is connected to be driven by the electric motor. A propulsor is connected to be driven by the shaft. The propulsor is configured to pivot to a first orientation configured to produce lift when the motor rotates the shaft in a first direction, and to pivot to a second orientation configured to produce thrust when the motor rotates the shaft in a second direction that is opposite of the first direction.

Abstract: A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a temperature control device located within the tail cone between the structural support housing and the tail cone, wherein the temperature control device is in thermal communication with at least one of the structural support housing and the tail cone.