An aircraft hybrid motive power source system includes: a gas turbine engine mounted on an aircraft and including a low-pressure shaft and a high-pressure shaft as rotary shafts; a first motor generator drivingly connected to the high-pressure shaft; a second motor generator drivingly connected to the low-pressure shaft; a fuel cell to which a fuel gas and an oxidant gas are supplied; a fuel gas generator configured to generate the fuel gas from a raw material by heating using an exhaust gas from the gas turbine engine; and a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

An aircraft hybrid motive power source system includes: a gas turbine engine mounted on an aircraft and including a low-pressure shaft and a high-pressure shaft as rotary shafts; a first motor generator drivingly connected to the high-pressure shaft; a second motor generator drivingly connected to the low-pressure shaft; a fuel cell to which a fuel gas and an oxidant gas are supplied; a fuel gas generator configured to generate the fuel gas from a raw material by heating using an exhaust gas from the gas turbine engine; and a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

An aircraft propulsion system includes a gas turbine engine, a water-exhaust heat exchanger, and a fuel cell segment. The gas turbine engine has a compressor, a combustor, and a turbine. The engine is in drive communication with a rotational load component. The water-exhaust heat exchanger is disposed to receive exhaust gas exiting the turbine section. The fuel cell segment includes a liquid hydrogen evaporator, a fuel cell, and a water pump. The liquid hydrogen evaporator is configured to change a flow of liquid hydrogen to a flow of gaseous hydrogen. The fuel cell is configured to receive a flow of air and the flow of gaseous hydrogen and react them to produce electrical power and a flow of water. The flow of water from the fuel cell goes to the water-exhaust heat exchanger which converts the flow of water to a flow of steam.

An aircraft propulsion system includes a gas turbine engine, a water-exhaust heat exchanger, and a fuel cell segment. The gas turbine engine has a compressor, a combustor, and a turbine. The engine is in drive communication with a rotational load component. The water-exhaust heat exchanger is disposed to receive exhaust gas exiting the turbine section. The fuel cell segment includes a liquid hydrogen evaporator, a fuel cell, and a water pump. The liquid hydrogen evaporator is configured to change a flow of liquid hydrogen to a flow of gaseous hydrogen. The fuel cell is configured to receive a flow of air and the flow of gaseous hydrogen and react them to produce electrical power and a flow of water. The flow of water from the fuel cell goes to the water-exhaust heat exchanger which converts the flow of water to a flow of steam.

Provided is an aircraft with a multi-power source electric propulsion system. The aircraft includes a fuselage, a power turbine accommodated in the fuselage and having a power shaft, a generator accommodated in the fuselage and connected to one end of the power shaft, a forward propeller for a forward flight and connected to another end of the power shaft, and a lift propeller for vertical take-off and landing (VTOL) and configured to receive power from the generator.

Provided is an aircraft with a multi-power source electric propulsion system. The aircraft includes a fuselage, a power turbine accommodated in the fuselage and having a power shaft, a generator accommodated in the fuselage and connected to one end of the power shaft, a forward propeller for a forward flight and connected to another end of the power shaft, and a lift propeller for vertical take-off and landing (VTOL) and configured to receive power from the generator.

An integrated hydrogen-electric engine includes a hydrogen fuel-cell; a hydrogen fuel source; an electric motor assembly disposed in electrical communication with the fuel-cell; an air compressor system configured to be driven by the motor assembly, and a cooling system having a heat exchanger radiator in a duct of the cooling system, and configured to direct an air stream including an air stream from the air compressor through the radiator, wherein an exhaust stream from a cathode side of the fuel-cell is fed via a flow control nozzle into the air stream in the cooling duct downstream of the radiator.

An integrated hydrogen-electric engine includes a hydrogen fuel-cell; a hydrogen fuel source; an electric motor assembly disposed in electrical communication with the fuel-cell; an air compressor system configured to be driven by the motor assembly, and a cooling system having a heat exchanger radiator in a duct of the cooling system, and configured to direct an air stream including an air stream from the air compressor through the radiator, wherein an exhaust stream from a cathode side of the fuel-cell is fed via a flow control nozzle into the air stream in the cooling duct downstream of the radiator.