Hybrid-electric drive system

Patent metadata

Field	Value
Publication number	US-10837304-B2
Application number	US-201615377080-A
Country	US
Kind code	B2
Filing date	Dec 13, 2016
Priority date	Dec 13, 2016
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

A propulsion system includes a propulsor having a driveshaft, an electric machine coupled to the driveshaft of the propulsor, and a combustion engine having an output shaft. The propulsion system additionally includes a one-way clutch operable with at least one of the driveshaft of the propulsor and the output shaft of the combustion engine. The one-way clutch allows for a differential angular velocity of the driveshaft relative to the output shaft in a first circumferential direction and prevents a differential angular velocity of the driveshaft relative to the output shaft in a second circumferential direction.

First claim

What is claimed is:

1. An aircraft propulsion system comprising:
a driveshaft to rotate a propeller;
an electric machine coupled to the driveshaft;
a turbine engine comprising an output shaft;
a brake operably coupled with the output shaft; and
a one-way clutch positioned between the brake and the electric machine and operable with at least one of the driveshaft and the output shaft of the turbine engine, the one-way clutch allowing for a differential angular velocity of the driveshaft relative to the output shaft in a first circumferential direction and preventing a differential angular velocity of the driveshaft relative to the output shaft in a second circumferential direction, wherein the propeller is positioned on an opposing side of the electric machine from the one-way clutch, and wherein the propeller, the electric machine, the one-way clutch, and the output shaft are coaxial.

2. The propulsion system of claim 1 , wherein the one-way clutch is configured to decouple the driveshaft from the output shaft passively based on an angular velocity of the output shaft generated by the turbine engine relative to an angular velocity of the driveshaft generated by the electric machine.

3. The propulsion system of claim 2 , wherein the one-way clutch is configured to decouple the driveshaft from the output shaft when the power applied to the driveshaft by the electric machine exceeds the power applied to the output shaft by the turbine engine by a predetermined threshold.

4. The propulsion system of claim 2 , wherein the one-way clutch is configured to couple the driveshaft to the output shaft when the power applied to the driveshaft by the electric machine is less than or equal to the power applied to the output shaft by the turbine engine.

5. The propulsion system of claim 4 , wherein the propulsor further comprises a gearbox, and wherein the driveshaft is configured for rotating the propeller across the gearbox.

6. The propulsion system of claim 1 , wherein the one-way clutch is configured as a mechanical one-way clutch passively controlled by the output shaft and the driveshaft.

7. The propulsion system of claim 1 , wherein the one-way clutch is configured as at least one of a sprag clutch or a cam clutch.

8. The propulsion system of claim 1 , wherein the driveshaft is configured as a first driveshaft of a first propulsor, wherein the electric machine is a first electric machine, and wherein the propulsion system further comprises:
a second propulsor comprising a second driveshaft; and
a second electric machine coupled to the second driveshaft of the second propulsor for driving the second propulsor, wherein the second electric machine is electrically coupled to the first electric machine and powered by the first electric machine.

9. A method of operating an aircraft propulsion system comprising
a propulsor including
a driveshaft to rotate a propeller,
an electric machine coupled to the driveshaft,
a turbine engine comprising an output shaft,
a brake operably coupled with the output shaft, and
a one-way clutch positioned on an opposing side of the electric machine from the propeller, between the brake and the electric machine, and operable with at least one of the driveshaft and the output shaft, wherein the propeller, the electric machine, the one-way clutch, and the output shaft are coaxial, the method comprising:
operating the propulsion system to power the propulsor at least in part with the turbine engine such that the one-way clutch couples the output shaft of the turbine engine to a first portion of the driveshaft of the propulsor; and
operating the propulsion system to power the propulsor at least in part with the electric machine such that the one-way clutch decouples the output shaft of the turbine engine from the driveshaft of the propulsor, wherein torque is supplied to a second portion of the driveshaft by the electric machine, the second portion of the driveshaft separated from the first portion of the driveshaft and wherein the propulsor is on an opposing side of the electric machine from the one-way clutch and the turbine engine.

10. The method of claim 9 , wherein operating the propulsion system to power the propulsor at least in part with the turbine engine further comprises operating the electric machine as an electric generator.

11. The method of claim 10 , wherein operating the electric machine as an electric generator comprises powering a second propulsor of the propulsion system.

12. The method of claim 9 , wherein operating the propulsion system to power the propulsor at least in part with the turbine engine further comprises operating the propulsion system to power the propulsor with both the turbine engine and the electric machine.

13. The method of claim 12 , wherein operating the propulsion system to power the propulsor with both the turbine engine and the electric machine comprises operating the turbine engine in a high power mode.

14. The method of claim 13 , wherein the high power mode is a takeoff operating mode.

15. The method of claim 9 , wherein the one-way clutch transitions from coupling the output shaft to the driveshaft to decoupling the output shaft from the driveshaft automatically based on a torque applied to the output shaft by the turbine engine relative to a torque applied to the driveshaft by the electric machine.

16. The method of claim 9 , wherein the first portion is an end section of the driveshaft and the second portion is a midsection of the driveshaft.

17. An aircraft propulsion system comprising:
a driveshaft;
an electric machine coupled to the driveshaft;
a turbine engine comprising an output shaft;
a one-way clutch coupled to the driveshaft and the output shaft of the turbine engine, wherein the one-way clutch is positioned between the turbine engine and the electric machine;
a propeller coupled to the driveshaft and position on an opposing side of electric machine from one-way clutch, wherein the propeller, the electric machine, the one-way clutch, and the output shaft are coaxial; and
a brake operably coupled with the output shaft, wherein the brake engages the output shaft to slow down the output shaft and disengage the one-way clutch, wherein the brake and the electric machine are separated by the one-way clutch.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Crabtree Glenn

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D35/024

  of series type · CPC title

• B64D35/025 Primary

  of parallel type · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title