Hybrid gas-electric turbine engine

Patent metadata

Field	Value
Publication number	US-10717539-B2
Application number	US-201615147284-A
Country	US
Kind code	B2
Filing date	May 5, 2016
Priority date	May 5, 2016
Publication date	Jul 21, 2020
Grant date	Jul 21, 2020

Abstract

A hybrid gas-electric turbine engine for turboprop or turboshaft applications is disclosed together with associated methods. In various embodiments disclosed herein, the turbine engine comprises a turbine configured to be driven by a flow of combustion gas; a turbine shaft configured to be driven by the turbine and transfer power to a load coupled to the turbine engine and an electric motor configured to transfer power to the load coupled to the turbine engine. The rotor may have a rotor axis of rotation that is radially offset from a shaft axis of rotation of the turbine shaft. In some embodiments, the electric motor may be a multi-rotor electric motor.

First claim

What is claimed is:

1. A hybrid gas-electric turbine engine for turboprop or turboshaft applications, the turbine engine comprising:
a turbine configured to be driven by a flow of combustion gas;
a turbine shaft configured to be driven by the turbine and transfer power to a load coupled to the turbine engine, the turbine shaft having a shaft axis of rotation;
an electric motor configured to transfer power to the load coupled to the turbine engine, the electric motor comprising one or more stators and a plurality of rotors angularly distributed about the shaft axis of rotation, the rotors each having a rotor axis of rotation that is radially offset from the shaft axis of rotation;
a respective drive gear drivingly engaged to each rotor for cooperatively transferring power from each rotor of the electric motor to the load; and
a common gear that is substantially coaxial with the shaft axis of rotation and drivingly engaged to the load via a gearbox input shaft that is separate from the turbine shaft, the common gear having:
a radially outer interface in driving engagement with the drive gears;
a first radially inner interface drivingly engageable with the turbine shaft via a coupling device; and
a second radially inner interface in driving engagement with the gearbox input shaft, the second radially inner interface axially spaced apart from the first radially inner interface,

the coupling device configured to:
drivingly engage the turbine shaft to the common gear to transfer power from the turbine shaft to the load during a first mode of operation; and
drivingly disengage the turbine shaft from the common gear during a second mode of operation to permit the common gear to rotate separately from the turbine shaft when power is transferred from the electric motor to the load via the common gear.

2. The hybrid turbine engine as defined in claim 1 , wherein the rotor axis of rotation of each rotor is substantially parallel to the shaft axis of rotation.

3. The hybrid turbine engine as defined in claim 1 , comprising an exhaust duct configured to channel the flow of combustion gas downstream of the turbine axially and radially outwardly relative to the shaft axis of rotation, an exterior of the exhaust duct defining a radially-inner space that is radially converging in a first direction along the shaft axis of rotation; wherein:
the electric motor is at least partially disposed in the radially inner space defined by the exterior of the exhaust duct; and
the drive gears are disposed farther in the first direction along the shaft axis of rotation than the rotors.

4. The hybrid turbine engine as defined in claim 3 , wherein:
the turbine engine has a reverse-flow configuration where the exhaust duct is disposed forward of an air inlet of the turbine engine; and
the first direction along the shaft axis of rotation corresponds to an aft direction of the turbine engine.

5. The hybrid turbine engine as defined in claim 4 , wherein the second radially inner interface is disposed axially forward of the radially outer interface.

6. The hybrid turbine engine as defined in claim 1 , comprising a gearbox configured to transfer power from the turbine shaft to the load and to transfer power from the electric motor to the load, the electric motor being disposed axially between the gearbox and the turbine relative to the shaft axis of rotation.

7. The hybrid turbine engine as defined in claim 6 , wherein the coupling device is configured to drivingly disengage the turbine shaft from the gearbox.

8. The hybrid turbine engine as defined in claim 7 , wherein the electric motor is permanently drivingly engaged to the gearbox.

9. The hybrid turbine engine as defined in claim 1 , wherein the electric motor is drivingly engaged to the load via:
the drive gears respectively drivingly engaged to the rotors;
the common gear drivingly engaged to the drive gears; and
a gearbox input shaft drivingly engaged to the common gear via the second radially inner interface.

10. The hybrid turbine engine as defined in claim 9 , wherein the turbine shaft is drivingly engaged to the load via:
the common gear; and
the gearbox input shaft drivingly engaged to the common gear via the second radially inner interface.

11. The hybrid turbine engine as defined in claim 9 , wherein the common gear is coupled for common rotation with the gearbox input shaft.

12. The hybrid turbine engine as defined in claim 1 , wherein the electric motor is configured to be drivingly engaged to the common gear during the first mode of operation and during the second mode of operation.

13. The hybrid turbine engine as defined in claim 1 , wherein the coupling device comprises a one-way clutch.

14. The hybrid turbine engine as defined in claim 1 , wherein the gearbox input shaft and the turbine shaft are substantially coaxial.

15. The hybrid turbine engine as defined in claim 1 , wherein the coupling device is axially disposed inside a central opening of the common gear.

Assignees

• Pratt & Whitney Canada

Inventors

• Menheere David H

Classifications

• B64D27/10 Primary

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02C3/10 Primary

  with another turbine driving an output shaft but not driving the compressor · CPC title

• Y02T50/60

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

• H02K7/1823

  structurally associated with turbines or similar engines · CPC title