Electric drive system line replaceable unit with integrated thermal cooling

Patent metadata

Field	Value
Publication number	US-11554859-B2
Application number	US-202016808818-A
Country	US
Kind code	B2
Filing date	Mar 4, 2020
Priority date	Mar 4, 2020
Publication date	Jan 17, 2023
Grant date	Jan 17, 2023

Abstract

One embodiment is an electric drive system for an aircraft including a motor, a gear box associated with the motor, and a cooling fan for drawing air into the unit across an electronic component to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein. The electric drive system further includes an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, the distributed oil being used to cool the motor and the gearbox, a reservoir for collecting the distributed oil after it has been used to cool the motor and the gearbox, and at least one structural element for retaining the motor, gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit.

First claim

What is claimed is:

1. An electric drive system for a tiltrotor aircraft including a rotatable nacelle, the electric drive system comprising:
at least one motor;
at least one gear box associated with the at least one motor;
a cooling fan for drawing air into the electric drive system across an electronic component of the electric drive system to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein;
an oil distribution system for distributing oil cooled by the oil cooler to the at least one motor and the at least one gearbox, wherein the distributed oil is used to cool the at least one motor and the at least one gearbox;
a reservoir for collecting the distributed oil after it has been used to cool the at least one motor and the at least one gearbox; and
at least one structural element for retaining the at least one motor, the at least one gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit;
wherein the electric drive system is housed in the rotatable nacelle of the tiltrotor aircraft, and
wherein the at least one electric motor comprises a plurality of redundant electric motors arranged in a stack, wherein a rotor shaft is disposed through the plurality of redundant motors.

2. The electric drive system of claim 1 further comprising a pump associated with the reservoir for returning the oil collected in the reservoir to the oil cooler.

3. The electric drive system of claim 1 wherein the least one structural element comprises a housing.

4. The electric m of claim 1 , wherein the at least one structural element comprises a first rail along a first side of the stack of redundant electric motors and a second rail along an opposite side of the stack of redundant motors, wherein each of the redundant electric motors is connected to the side rails.

5. The electric drive system of claim 1 , wherein power generated by the at least one motor drives the rotor shaft disposed through a center of the electric drive system.

6. The electric drive system of claim 5 , wherein the cooling fan is mechanically powered by the rotor shaft.

7. The electric drive system of claim 1 , wherein the cooling fan is electrically powered.

8. The electric drive system of claim 1 , wherein the electronic components comprise inverters.

9. The electric drive system of claim 1 , wherein the electric drive system is a line replaceable unit.

10. The electric drive system of claim 1 further comprising a collective actuator for controlling a collective pitch of rotor blades connected to the rotor shaft.

11. The electric drive system of claim 1 further comprising a cyclic actuation system for controlling a cyclic pitch of rotor blades connected to the rotor shaft.

12. A tiltrotor aircraft comprising a rotor system, the rotor system comprising:
a ducted rotor for providing lift for the tiltrotor aircraft when the tiltrotor aircraft is in helicopter mode and for providing thrust for the tiltrotor aircraft when the tiltrotor aircraft is in airplane mode;
a rotatable nacelle for supporting the ducted rotor; and
an electric drive system implemented as a line replaceable unit housed in the rotatable nacelle, the electric drive system comprising:
at least one motor;
at least one gear box associated with the at least one motor;
a cooling fan for drawing air into the electric drive system across an electronic component of the electric drive system to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein;
an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, wherein the distributed oil is used to cool the at least one motor and the at least one gearbox;
a reservoir for collecting the distributed oil after it has been used to cool the at least one motor and the at least one gearbox; and
at least one structural element for retaining the at least one motor, the at least one gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit,

wherein the electric drive system is disposed in the rotatable nacelle wherein the electric drive system is disposed in the rotatable nacelle, and
wherein the at least one electric motor comprises a plurality of redundant electric motors arranged in a stack, wherein a rotor shaft is disposed through the plurality of redundant motors.

13. The rotorcraft of claim 12 further comprising a pump associated with the reservoir for returning the oil collected in the reservoir to the oil cooler.

14. The rotorcraft of claim 12 , wherein the at least one structural element comprises at least one of a housing and first and second rails disposed on opposite sides of the unit.

15. The rotorcraft of claim 12 , wherein the at least one motor comprises redundant electric motors and power generated by the redundant electric motors drives a rotor shaft disposed through a center of the electric drive system.

16. A tiltrotor aircraft comprising a rotor system, the rotor system comprising:
a rotor;
a rotatable nacelle for supporting the rotor; and
an electric drive system implemented as a line replaceable unit housed in the rotatable nacelle, the electric drive system comprising:
at least one motor;
at least one gear box associated with the at least one motor;
a cooling fan for drawing air into the electric drive system across an electronic component of the electric drive system to cool the electronic component and for expelling air into an oil cooler for cooling oil contained therein, wherein the electrical component comprises an inverter;
an oil distribution system for distributing oil cooled by the oil cooler to at least one motor and at least one gearbox, wherein the distributed oil is used to cool the at least one motor and the at least one gearbox;
a reservoir for collecting the distributed oil after it has been used to cool the at least one motor and the at least one gearbox; and
at least one structural element for retaining the at least one motor, the at least one gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit,

wherein the electric drive system is disposed in the rotatable nacelle, and
wherein the at least one electric motor comprises a plurality of redundant electric motors arranged in a stack, wherein a rotor shaft is disposed through the plurality of redundant motors.

17. The rotorcraft of claim 16 further comprising a pump associated with the reservoir for returning the oil collected in the reservoir to the oil cooler.

18. The rotorcraft of claim 16 , wherein the at least one structural element comprises at least one of a housing and first and second rails disposed on opposite sides of the unit.

19. The rotorcraft of claim 16 , wherein the at least one motor comprises redundant electric motors and power generated by the redundant electric motors drives a rotor shaft disposed through a center of the electric drive system.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Heironimus William Kyle
• Chung Stephen Yibum

Classifications

• B64D33/08

  of power plant cooling systems · CPC title

• H02K2213/12

  Machines characterised by the modularity of some components · CPC title

• B64C27/58

  Transmitting means, e.g. interrelated with initiating means or means acting on blades (means acting on blades B64C27/72) · CPC title

• B64D13/006

  the air being used to cool structural parts of the aircraft · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title