Electrical assist for aircraft

Patent metadata

Field	Value
Publication number	US-10604266-B2
Application number	US-201715432230-A
Country	US
Kind code	B2
Filing date	Feb 14, 2017
Priority date	May 16, 2016
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

First claim

What is claimed is:

1. An aircraft engine system comprising:
a first internal combustion engine mechanically coupled to a first bladed rotor for rotation of the first bladed rotor;
a second internal combustion engine mechanically coupled to a second bladed rotor for rotation of the second bladed rotor;
a first motor generator having a first shaft, the first shaft configured to receive mechanical energy from the first internal combustion engine;
a second motor generator having a second shaft, the second shaft configured to receive mechanical energy from the second internal combustion engine; and
a control unit configured to cause the first motor generator to generate electricity, the electricity generated by the first motor generator by a rotation of the first shaft caused by the first internal combustion engine, wherein the control unit is further configured to alternatively cause the first motor generator to generate mechanical power that is transferred to the first bladed rotor, the mechanical power generated by the first motor generator is due to a rotation of the first shaft caused by an application of electricity to the first motor generator, wherein the electricity applied to the first motor generator is generated by the second motor generator, the electricity generated by the second motor generator is due to a rotation of the second shaft by the second internal combustion engine mechanically coupled to the second bladed rotor.

2. The system of claim 1 , wherein the first internal combustion engine and the first motor generator are in a first nacelle, and the second internal combustion engine and the second motor generator are in a second nacelle.

3. The system of claim 1 further comprising an electrical link configured to transfer the electricity that is applied to the first motor generator and generated by the second motor generator, wherein the electrical link extends from a first wing of an aircraft to a second wing of the aircraft.

4. The system of claim 1 further comprising an electrical link configured to transfer the electricity that is applied to the first motor generator and generated by the second motor generator, wherein the electrical link extends between opposite sides of an aircraft.

5. The system of claim 1 , wherein the control unit is further configured to cause the first motor generator to generate the mechanical power in response to a predetermined event.

6. An aircraft propulsion system comprising:
a first internal combustion engine mechanically coupled to a first bladed rotor for rotation of the first bladed rotor;
a first motor generator having a first shaft, the first shaft configured to receive mechanical energy from the first internal combustion engine; and
a control unit configured to direct the first motor generator to generate electricity, the electricity generated by the first motor generator due to a rotation of the first shaft caused by the first internal combustion engine, wherein the control unit is further configured to alternatively cause the first motor generator, in response to a predetermined event, to generate mechanical power that is transferred to the first bladed rotor, the mechanical power generated by the first motor generator is due to a rotation of the first shaft caused by an application of electricity to the first motor generator, wherein the electricity applied to the first motor generator is received from a second motor generator that is generated by a rotation of a second shaft of the second motor generator, the rotation of the second shaft of the second motor generator caused by a second internal combustion engine configured to mechanically power a second bladed rotor.

7. The aircraft propulsion system of claim 6 , wherein the predetermined event is detected.

8. The aircraft propulsion system of claim 6 , wherein the predetermined event is a failure of the first internal combustion engine.

9. The aircraft engine of claim 6 , wherein the predetermined event is a failure of the first internal combustion engine and a failure of a cross-shafting.

10. The aircraft propulsion system of claim 6 , wherein predetermined event is a failure of a cross-shafting.

11. The aircraft propulsion system of claim 6 , wherein predetermined event is a manual request.

12. The aircraft propulsion system of claim 6 , wherein the first internal combustion engine and the second internal combustion engine are gas turbine engines.

13. The aircraft propulsion system of claim 6 , wherein the first bladed rotor and the second bladed rotor are aircraft propellers.

14. The aircraft propulsion system of claim 6 , wherein the first bladed rotor and the second bladed rotor are tiltrotor propellers and/or helicopter propellers.

15. The aircraft propulsion system of claim 6 , wherein the control unit is configured to direct a clutch to disengage if the first motor generator is directed to generate the mechanical power, wherein disengagement of the clutch enables the first bladed rotor to rotate freely of the first internal combustion engine.

16. A method to electrically assist an internal combustion engine, the method comprising:
rotating a first bladed rotor by a first internal combustion engine of an aircraft via a mechanical coupling between the first internal combustion engine and the first bladed rotor;
generating electricity from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine; and
generating, in response to a predetermined event, mechanical power from the first motor generator instead of electricity, wherein the mechanical power is transferred to the first bladed rotor, wherein generating the mechanical power comprises rotating the first shaft of the first motor generator by applying electricity to the first motor generator received from a second motor generator, and wherein the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine of the aircraft that mechanically powers a second bladed rotor.

17. The method of claim 16 , wherein the first bladed rotor and the second bladed rotor are aircraft propellers.

18. The method of claim 16 , wherein the first bladed rotor and the second bladed rotor are tiltrotor propellers and/or helicopter propellers.

19. The method of claim 16 further comprising disengaging a clutch when generating the mechanical power, wherein disengaging the clutch enables the first bladed rotor to rotate freely of the first internal combustion engine.

20. The method of claim 16 further comprising applying additional electricity to the first motor generator from a battery when applying electricity to the first motor generator received from a second motor generator.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Roever Douglas M
• Zeller Robert

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D31/10

  for preventing asymmetric thrust · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D27/16

  of jet type · CPC title

• B64D27/24 Primary

  using steam or spring force (jet aircraft B64D27/16) · CPC title