Tiltrotor propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-10384774-B2
Application number	US-201615259654-A
Country	US
Kind code	B2
Filing date	Sep 8, 2016
Priority date	Sep 8, 2016
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.

First claim

What is claimed is:

1. A method of operating a propulsion system of an aircraft having a plurality of forward propulsors and a plurality of aft propulsors, each powered by an electric power source and rotatable between a forward thrust position and a vertical thrust position, the method comprising:
moving the plurality of forward propulsors and the plurality of aft propulsors to the vertical thrust positions;
providing a first forward to aft ratio of electric power to the plurality of forward propulsors and the plurality of aft propulsors from the electric power source, such that the plurality of forward propulsors and plurality of aft propulsors each generate vertical thrust;
moving the plurality of forward propulsors and the plurality of aft propulsors to the forward thrust positions; and
providing a second forward to aft ratio of electric power to the plurality of forward propulsors and the plurality of aft propulsors from the electric power source, wherein the first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power.

2. The method of claim 1 , wherein the first forward to aft ratio of electric power is greater than the second forward to aft ratio of electric power.

3. The method of claim 2 , wherein the second forward to aft ratio of electric power is less than ten percent (10%) of the first forward to aft ratio of electric power.

4. The method of claim 1 , wherein the second forward to aft ratio of electric power is greater than the first forward to aft ratio of electric power.

5. The method of claim 4 , wherein the first forward to aft ratio of electric power is less than ten percent (10%) of the second forward to aft ratio of electric power.

6. The method of claim 1 , wherein the propulsion system further comprises a supplemental propulsor, and wherein the method further includes:
providing a first amount of power from the electric power source to the supplemental propulsor when the plurality of forward propulsors and plurality of aft propulsors are in the vertical thrust positions; and
providing a second amount of power from the electric power source to the supplemental propulsor when the plurality of forward propulsors and the plurality of aft propulsors are in the forward thrust positions, wherein the second amount of power is greater than the first amount of power.

7. The method of claim 6 , wherein the supplemental propulsor is a fan mounted to the fuselage of the aircraft.

8. The method of claim 6 , wherein the first amount of power is less than about half of the second amount of power.

9. The method of claim 1 , wherein the electric power source comprises a combustion engine and an electric generator, wherein the combustion engine drives the electric generator.

10. The method of claim 1 , wherein the electric power source is located remotely from the plurality of forward propulsors and the plurality of aft propulsors.

11. The method of claim 1 , wherein the plurality of forward propulsors are configured as a plurality of forward primary thrust propulsors, wherein the plurality of aft propulsors are configured as a plurality of aft primary thrust propulsors, wherein the propulsion system further comprises a plurality of forward secondary thrust propulsors and a plurality of aft secondary thrust propulsors, and wherein the method further includes:
providing a first amount of electrical power from the electric power source to the plurality of forward and aft secondary thrust propulsors when the plurality of forward and aft primary thrust propulsors are in the vertical thrust positions; and
providing a second amount of electrical power from the electric power source to the plurality of forward and aft secondary thrust propulsors when the plurality of forward and aft primary thrust propulsors are in the forward thrust positions, wherein the second amount of electrical power is greater than the first amount of electrical power.

12. The method of claim 11 , wherein the first amount of electrical power is less than about half of the second amount of electrical power.

13. A method of operating a propulsion system of an aircraft having a plurality of primary thrust propulsors and a plurality of secondary thrust propulsors, each powered by an electric power source and rotatable between a forward thrust position and a vertical thrust position, the method comprising:
moving the plurality of primary thrust propulsors to the vertical thrust positions;
providing power to the plurality of primary thrust propulsors to generate a vertical thrust for vertically oriented flight and simultaneously providing a first amount of electrical power to the plurality of secondary thrust propulsors;
moving the plurality of primary thrust propulsors to the forward thrust positions; and
providing a second amount of electrical power to the plurality of secondary thrust propulsors to generate a forward thrust for horizontally oriented flight, wherein the second amount of electrical power is greater than the first amount of electrical power.

14. The method of claim 13 , wherein the second amount of electrical power is at least about two times greater than the first amount of electrical power.

15. The method of claim 13 , wherein the second amount of electrical power is at least about four times greater than the first amount of electrical power.

16. The method of claim 13 , wherein the first amount of electrical power is less than ten percent of the second amount of electrical power.

17. The method of claim 13 , wherein the aircraft defines a minimum necessary takeoff thrust, and wherein providing power to the plurality of primary thrust propulsors to generate a vertical thrust comprises providing power to the plurality of primary thrust propulsors to generate a vertical thrust within ten percent of the minimum necessary takeoff thrust.

18. The method of claim 13 , wherein the plurality of primary thrust propulsors comprises a plurality of forward primary thrust propulsors and a plurality of aft primary thrust propulsors, wherein providing power to the plurality of primary thrust propulsors comprises providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors, and wherein the method further comprises:
providing a second forward to aft ratio of electric power to the plurality of forward propulsors and the plurality of aft propulsors from the electric power source, wherein the first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power.

19. The method of claim 13 , wherein moving the plurality of primary thrust propulsors to the vertical thrust positions comprises moving the plurality of primary thrust propulsors and the plurality of secondary thrust propulsors to the vertical thrust positions, and wherein moving the plurality of primary thrust propulsors to the forward thrust positions comprises moving the plurality of primary thrust propulsors and the plurality of secondary thrust propulsors to the forward thrust positions.

20. The method of claim 13 , wherein the electric power source comprises a combustion engine configured to generate at least about 1,500 horsepower and an electric generator driven by the combustion engine and configured to generate at least about 1.12 megawatts.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Polakowski Matthew Ryan
• Murrow Kurt David
• Crabtree Glenn
• Zatorski Darek Tomasz

Classifications

• A61L9/122

  comprising a fan · CPC title

• A61L2209/133

  Replaceable cartridges, refills · CPC title

• H02J7/70

  characterised by the mechanical construction · CPC title

• B64C29/00 Primary

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• B64C3/385

  Variable incidence wings · CPC title