Aircraft having an aft engine

Patent metadata

Field	Value
Publication number	US-11097849-B2
Application number	US-201816126269-A
Country	US
Kind code	B2
Filing date	Sep 10, 2018
Priority date	Sep 10, 2018
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

First claim

What is claimed is:

1. A method for operating an electric fan of an aircraft propulsion system, the method comprising:
driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft;
receiving data indicative of a failure condition of one or more components of the propulsion system; and
driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power in response to receiving data indicative of the failure condition subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.

2. The method of claim 1 , wherein the electric fan is an electric fan of an aft engine of the aircraft propulsion system, and wherein driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power comprises modifying a variable geometry component of the aft engine.

3. The method of claim 2 , wherein modifying the variable geometry component of the aft engine comprises changing at least one of an effective pitch angle of a plurality of variable inlet guide vanes of the aft engine, an effective pitch angle of a plurality of variable outlet guide vanes of the aft engine, or an effective nozzle area for the aft engine.

4. The method of claim 2 , wherein modifying the variable geometry component of the aft engine comprises changing an effective pitch angle of a plurality of variable guide vanes of the aft engine.

5. The method of claim 2 , wherein modifying the variable geometry component of the aft engine comprises an effective nozzle area for the aft engine.

6. The method of claim 2 ,
wherein modifying the variable geometry component of the aft engine comprises modifying the variable geometry component of the aft engine in response to receiving data indicative of the failure condition.

7. The method of claim 2 , wherein modifying the variable geometry component of the aft engine includes modifying the variable geometry component of the aft engine to modify an amount of electrical power generated with the electric machine.

8. The method of claim 1 , wherein driving the plurality of fan blades of the electric fan with the electric machine comprises driving the plurality of fan blades of the electric fan with the electric machine while the plurality of fan blades of the electric fan are in a first angular position, and wherein driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power comprises driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power while the plurality of fan blades of the electric fan are in a second angular position.

9. The method of claim 8 , wherein the first angular position is a positive angular position, and wherein the second angular position is a negative angular position.

10. The method of claim 9 , wherein the positive angular position and the negative angular position define an angular difference of at least 20 degrees and up to 100 degrees.

11. The method of claim 8 , further comprising:
moving the plurality of fan blades of the electric fan from the first angular position to the second angular position.

12. The method of claim 11 , wherein the aircraft propulsion system further comprises a first propulsor, wherein the method further comprises:
receiving data indicative of a failure condition of the first propulsor, and wherein moving the plurality of fan blades of the electric fan comprises moving the plurality of fan blades of the electric fan in response to receiving the data indicative of the failure condition of the first propulsor.

13. The method of claim 11 , further comprising:
determining an air speed of the aircraft, a rotational speed of the electric fan, or both, and wherein moving the plurality of fan blades of the electric fan from the first angular position to the second angular position comprises moving the plurality of fan blades of the electric fan from the first angular position to the second angular position based at least in part on the determined air speed of the aircraft, the determined rotational speed of the electric fan, or both.

14. The method of claim 11 , further comprising:
driving the electric machine with the plurality of fan blades of the electric fan while the plurality of fan blades of the electric fan are in the first angular position to generate an initial amount of electrical power, and wherein moving the plurality of fan blades of the electric fan from the first angular position to the second angular position comprises moving the plurality of fan blades of the electric fan from the first angular position to the second angular position using at least in part the initial amount of electrical power.

15. The method of claim 1 , wherein driving the plurality of fan blades of the electric fan with the electric machine comprises rotating the plurality of fan blades of the electric fan in a first rotational direction, and wherein driving the electric machine with the plurality of fan blades of the electric fan comprises rotating the plurality of fan blades of the electric fan in a second rotational direction, opposite the first rotational direction.

16. The method of claim 1 , wherein the aircraft propulsion system further comprises a first propulsor, wherein the first propulsor is a gas powered propulsor, and wherein the method further comprises:
operating the first propulsor to generate electrical power, and wherein driving the plurality of fan blades of the electric fan with the electric machine comprises providing the electric machine with at least a portion of the electrical power generated through the operation of the first propulsor.

17. The method of claim 1 , the aircraft comprises an aft end, and wherein the electric fan is a boundary layer ingestion electric fan mounted at the aft end of the aircraft.

18. The method of claim 1 , wherein the electric machine of the electric fan is mechanically coupled to the plurality of fan blades of the electric fan through a gearbox.

19. An aircraft comprising:
a fuselage extending between a forward end and an aft end;
a wing extending from the fuselage; and
a propulsion system, the propulsion system comprising:
an electric generator;
a gas turbine engine mounted to the wing of the aircraft, the gas turbine engine configured to drive the electric generator to generate electric power;
an aft engine mounted to the fuselage at the aft end of the fuselage, the aft engine comprising a fan and an electric machine in electrical communication with the electric generator, the aft engine further comprising one or more variable geometry components; and
wherein the electric machine of the aft engine is configured to drive the fan using at least in part the electric power generated by the electric generator in a first operating mode, and wherein the electric machine of the aft engine is configured to be driven by the fan to generate electrical power in a second operating mode in response to receiving data indicative of a failure condition of one or more components of the propulsion system.

20. The aircraft of claim 19 , wherein the aft engine defines an axial direction, wherein the fan includes a plurality of fan blades, wherein each fan blade of the plurality of fan blades defines a positive angle with the axial direction when the plurality of fan blades are in a first angular position, and wherein each fan blade of the plura

Assignees

• Gen Electric

Inventors

• Pastouchenko Nikolai N
• Vondrell Randy M
• Murrow Kurt David
• Yao Jixian
• Miller Brandon Wayne
• Marrinan Patrick Michael
• Niergarth Daniel Alan
• Joshi Narendra Digamber

Classifications

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D35/024

  of series type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02K5/00

  Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan · CPC title