Hybrid aircraft power plant
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.
1. 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 relative to a central axis of the gas turbine engine, the gas turbine engine having a compressor and a turbine, the turbine drivingly engaged by 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.
2. The aircraft power plant of claim 1 , wherein the first axial side corresponds to a downstream side of the fan relative to an airflow through the fan, the second axial side corresponding to an upstream side of the fan relative to the airflow.
3. The aircraft power plant of claim 1 , comprising a duct extending circumferentially around both of the fan and the gas turbine engine.
4. The aircraft power plant of claim 1 , wherein the gearbox is a planetary gearbox having a sun gear, planet gears meshed with the sun gear and rollingly supported by a planet carrier, and a ring gear meshed with the planet gears.
5. The aircraft power plant of claim 4 , wherein the engine shaft is drivingly engaged to the planet carrier, the motor shaft is drivingly engaged to the sun gear, and the fan is drivingly engaged by the ring gear.
6. The aircraft power plant of claim 1 , comprising:
a first configuration in which the electric motor is in a generator mode, the gas turbine engine driving both of the electric motor and the fan in the first configuration along the first load path and the second load path; and
a second configuration in which the electric motor is in a propelling mode, the gas turbine engine and the electric motor conjointly driving the fan in the second configuration and the first load path and the second load path.
7. The aircraft power plant of claim 1 , wherein the gas turbine engine is a single spool engine.
8. The aircraft power plant of claim 1 , wherein the electric motor is located on the second axial side of the fan.
9. The aircraft power plant of claim 8 , wherein the gearbox is located axially between the electric motor and the fan.
10. An aircraft comprising:
a fuselage having a skin enclosing an internal volume of the fuselage, the fuselage having a tail section, the skin defining an air intake within the tail section;
a power plant located within the tail section, the power plant having:
a fan for providing power to the aircraft, the fan in fluid flow communication with the air intake of the tail section;
a gearbox drivingly engaged with the fan;
a gas turbine engine drivingly engaged with the gearbox and in fluid flow communication with the air intake of the tail section;
an electric motor drivingly engaged with the gearbox, the gearbox and the electric motor located forward of the fan relative to a direction of travel of the aircraft; and
wherein the fan is in continuous driving engagement with both of the gas turbine engine and the electric motor via the gearbox, the fan is driven by one or more of the gas turbine engine and the electric motor through the gearbox.
11. The aircraft of claim 10 , wherein the tail section defines an intake conduit extending from the air intake to the fan, the intake conduit curving from the air intake to the fan.
12. The aircraft of claim 10 , wherein the tail section has an opening at a rear end thereof, the gas turbine engine and the fan in fluid flow communication with the opening.
13. The aircraft of claim 10 , wherein the tail section has a converging portion that extends towards a longitudinal axis of the fuselage, the air intake located within the converging portion.
14. The aircraft of claim 10 , wherein the gearbox is a planetary gearbox having a sun gear, planet gears meshed with the sun gear and rollingly supported by a planet carrier, and a ring gear meshed with the planet gears.
15. The aircraft of claim 14 , wherein the gas turbine engine is drivingly engaged to the sun gear, the electric motor is drivingly engaged to the planet carrier, and the fan is drivingly engaged by the ring gear.
16. The aircraft of claim 10 , wherein the gas turbine engine is a single spool engine.
17. The aircraft of claim 10 , comprising secondary propulsors mounted to the tail section of the fuselage.
18. The aircraft of claim 17 , wherein the secondary propulsors are ducted fans each drivingly engaged by a respective electric motor.
19. The aircraft of claim 10 , wherein the power plant has:
a first configuration in which the electric motor is in a generator mode, the gas turbine engine driving both of the electric motor and the fan in the first configuration; and
a second configuration in which the electric motor is in a propelling mode, the gas turbine engine and the electric motor conjointly driving the fan in the second configuration.