Systems and methods for hybrid electric turbine engines
A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, a first electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft, and an electric compressor extending along a second axis that is radially offset from the central longitudinal axis, the electric compressor in fluid communication with the second turbine section.
1. An engine, comprising:
a fan section having a fan;
a first turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis;
a first electric motor drivably connected to the main shaft; and
an electric compressor extending along a first axis that is disposed in a non-parallel relationship to the central longitudinal axis, wherein a motor axis of the first electric motor is parallel or coincident with the central longitudinal axis.
2. The engine of claim 1 , wherein:
the electric compressor comprises a second electric motor including a second motor shaft extending along a second electric motor axis, and
the second electric motor axis is parallel with the first axis.
3. The engine of claim 2 , further comprising a third electric motor including a third motor shaft extending along a third electric motor axis, the third electric motor axis being parallel with a second axis.
4. The engine of claim 3 , wherein:
the third electric motor is configured to drive the electric compressor,
the third electric motor is configured to drive a core, and
the third electric motor is configured to be driven by the core.
5. The engine of claim 1 , wherein:
the first electric motor is configured to drive the fan, and
the first electric motor is configured to be driven by the fan.
6. The engine of claim 1 , wherein a core is sized and configured to provide between 30% and 80% of an airflow to a second turbine section.
7. The engine of claim 1 , further comprising a discharge duct disposed between a compressor outlet of the electric compressor and a diffuser inlet of a core.
8. The engine of claim 1 , further comprising:
a core extending along a second axis that is radially offset from the central longitudinal axis, the core including a second turbine section;
the first electric motor being radially offset from the core; and
the electric compressor in fluid communication with the second turbine section.
9. The engine of claim 8 , further comprising a support structure that extends between and operatively connects a static structure of the fan section and an exit housing of the second turbine section.
10. The engine of claim 8 , wherein the electric compressor comprises a second electric motor, and wherein the engine further comprises a third electric motor drivably coupled to a shaft defining a shaft axis that is co-axial with the first axis.
11. The engine of claim 10 , further comprising a battery electrically coupled to the first electric motor, the second electric motor, and the third electric motor.
12. The engine of claim 11 , wherein at least one of the first electric motor and the third electric motor are configured to charge the battery.
13. The engine of claim 10 , further comprising a controller operatively coupled to the first electric motor, the second electric motor, and the third electric motor, the controller configured to command at least one of the first electric motor and the third electric motor to power the second electric motor.
14. An engine, comprising:
a fan section having a fan;
a first turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis;
a core extending along a first axis that is radially offset from the central longitudinal axis, the core comprising a second turbine section;
a first electric motor drivably connected to the main shaft, the first electric motor having a central axis parallel with the central longitudinal axis; and
a controller operably coupled to the first electric motor, the controller configured to command a second electric motor to power the first electric motor.
15. The engine of claim 14 , wherein the first electric motor is configured to drive the fan, and the first electric motor is configured to be driven by the fan.
16. The engine of claim 14 , wherein the core is sized and configured to provide between 30% and 80% of an airflow to the second turbine section.
17. The engine of claim 14 , wherein:
the fan section further comprises a static structure and a guide vane extending from the static structure, and
a support structure extends between and operatively connects the static structure to an exit housing of the first turbine section.
18. The engine of claim 14 , further comprising the second electric motor, wherein the second electric motor is connected to a second shaft of the core.
19. An engine, comprising:
a fan section having a fan;
a first turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis;
a first electric motor drivably connected to the main shaft; and
an electric compressor extending along a first axis that is disposed in a non-parallel relationship to the central longitudinal axis, the electric compressor comprising a second electric motor.
20. The engine of claim 19 , further comprising a third electric motor drivably coupled to a shaft defining a shaft axis that is co-axial with the first axis.