Hybrid electric aircraft system with distributed propulsion
A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.
1. A propulsion system for an aircraft, the propulsion system comprising:
at least one gas turbine engine;
an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources;
at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor; and
a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced, wherein the takeoff thrust settings of the electric auxiliary fan driving motor are established based on a takeoff thrust demand, at least one condition of the one or more electric power sources, and a health status of the at least one gas turbine engine.
2. The propulsion system of claim 1 , wherein the one or more electric power sources comprise a generator driven by an auxiliary power unit.
3. The propulsion system of claim 2 , wherein the one or more electric power sources comprise an energy storage system charged by the generator driven by the auxiliary power unit.
4. The propulsion system of claim 3 , wherein the energy storage system is charged by an engine-driven generator driven by the at least one gas turbine engine.
5. The propulsion system of claim 3 , wherein the controller is configured to determine a plurality of flight conditions comprising one or more flight inputs, a condition of the energy storage system, and a condition of the auxiliary power unit.
6. The propulsion system of claim 5 , wherein the controller is configured to determine a go-no-go threshold including a supplemental thrust provided by the electric auxiliary fan driving motor.
7. The propulsion system of claim 6 , wherein the controller is configured to determine a balanced field length based on the flight conditions and the go-no-go threshold to establish the plurality of takeoff thrust settings.
8. The propulsion system of claim 1 , further comprising:
an auxiliary fan transmission mechanically coupled to the at least one gas turbine engine and the electric auxiliary fan driving motor, the auxiliary fan transmission configured to selectively receive the motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor, wherein the at least one auxiliary propulsion fan is operably coupled to the auxiliary fan transmission.
9. The propulsion system of claim 8 , wherein the at least one gas turbine engine comprises a first gas turbine engine and a second gas turbine engine operably coupled through a shared drive shaft to the auxiliary fan transmission.
10. A method comprising:
providing an electric power input from one or more electric power sources to an electric auxiliary fan driving motor to produce an electric motor motive force;
providing a gas turbine engine motive force from at least one gas turbine engine;
establishing a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor; and
combining the electric motor motive force and the gas turbine engine motive force to drive rotation of an auxiliary propulsion fan of an aircraft such that a minimum total aircraft thrust required for takeoff of the aircraft is produced as a function of at least a runway length.
11. The method of claim 10 , wherein the one or more electric power sources comprise a generator driven by an auxiliary power unit.
12. The method of claim 11 , wherein the one or more electric power sources comprise an energy storage system charged by one or more of the generator driven by the auxiliary power unit and an engine-driven generator driven by the at least one gas turbine engine.
13. The method of claim 12 , further comprising: determining a plurality of flight conditions comprising one or more flight inputs, a condition of the energy storage system, and a condition of the auxiliary power unit.
14. The method of claim 13 , further comprising:
determining a go-no-go threshold including a supplemental thrust provided by the electric auxiliary fan driving motor.
15. The method of claim 14 , further comprising:
determining a balanced field length based on the flight conditions and the go-no-go threshold to establish the plurality of takeoff thrust settings; and
iterating on a dual engine takeoff thrust setting, wherein the go-no-go threshold is based on a takeoff thrust of a single engine of the at least one gas turbine engine.
16. The method of claim 15 , wherein the flight inputs comprise one or more of: the runway length, a single engine takeoff runway length, an ambient temperature, and an aircraft gross weight.
17. A propulsion system for an aircraft, the propulsion system comprising:
a first gas turbine engine;
a second gas turbine engine; a mechanical power mixing means operably coupled to the first gas turbine engine and the second gas turbine engine;
an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources;
an auxiliary propulsion fan configured to selectively receive a motive force from either or both of the mechanical power mixing means and the electric auxiliary fan driving motor; and
a controller configured to establish a plurality of takeoff thrust settings of the first gas turbine engine, the second gas turbine engine, and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced based on determining a balanced field length corresponding to a plurality of flight conditions to establish the plurality of takeoff thrust settings of the first and second gas turbine engines, the one or more electric power sources, and the electric auxiliary fan driving motor.
18. The propulsion system of claim 17 , wherein the mechanical power mixing means comprises a first engine drive shaft coupled through a first clutch to a gearbox, a second engine drive shaft coupled through a second clutch to the gearbox, and a shared drive shaft operably coupled between the gearbox and an auxiliary fan transmission operably coupled to the auxiliary propulsion fan.
19. The propulsion system of claim 17 , wherein the one or more electric power sources comprise one or more of a generator driven by an auxiliary power unit and an energy storage system, wherein controller is configured to determine the plurality of flight conditions comprising one or more flight inputs, a condition of the energy storage system, a condition of the auxiliary power unit, a go-no-go threshold including a supplemental thrust provided by the electric auxiliary fan driving motor.