THRUST REVERSERS AND METHODS TO PROVIDE REVERSE THRUST

• US 20170152811A1
• Filed: 11/14/2016
• Published: 06/01/2017
• Est. Priority Date: 10/31/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Acheson, Kurt Erik, Chuck, Chen
• Granted Patent: US 10,590,885 B2
• Time in Patent Office: Days
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: F02K 1/766 with blocking systems or locking devices; Arrangement of locking devices for thrust reversers
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Thrust reversers and methods to provide reverse thrust are disclosed. An example thrust reverser includes a cascade to direct air from an interior volume of an engine nacelle to generate reverse thrust with respect to a direction of travel, and an air extractor to extract a portion of air approaching the cascade from within the interior volume.

Claims

1. A thrust reverser for an engine comprising:

an air extractor to extract a portion of air from an interior portion of the engine, the air in the interior portion of the engine to generate reverse thrust with respect to a direction of travel of the engine; and

an air ejector to eject the portion of the air from a location on an exterior surface of the engine.

2. The thrust reverser of claim 1, further including a cascade to generate the reverse thrust.

3. The thrust reverser of claim 2, wherein the location is forward of the cascade.

4. The thrust reverser of claim 1, further including a tube coupled to the air ejector, the air ejector to receive air flowing through the tube, a pressure of the air flowing through the tube increased relative to a pressure of the portion of the air extracted by the air extractor.

5. The thrust reverser of claim 4, wherein the air ejector is to entrain the portion of air extracted by the air extractor via the air received from the tube.

6. The thrust reverser of claim 1, wherein the interior portion of the engine includes a first door to direct the air to form the reverse thrust and wherein at least a portion of the exterior surface of the engine includes a second door to direct the reverse thrust in a forward direction relative to the direction of travel.

7. The thrust reverser of claim 6, wherein the location is forward of the second door relative to the direction of travel.

8. The thrust reverser of claim 1, wherein the air extractor includes a first pump and the air ejector includes a second pump.

9. An engine comprising:

a thrust reverser to generate reverse thrust by directing air from an interior volume of the engine to an exterior of the engine;

means for extracting a portion of the air from the interior volume; and

means for ejecting the portion of the air from the interior volume to a location on an exterior surface of the engine

10. The engine of the claim 9, wherein the means for extracting includes a pump.

11. The engine of claim 9, wherein the means for ejecting includes a pump.

12. The engine of claim 9, further including a diverter fairing, the means for extracting to extract to the portion of the air via an opening formed in the diverter fairing.

13. The engine of claim 9, further including a tube coupled to the means for ejecting, the tube to provide a flow of air from a portion of the engine to the means for ejecting.

14. The engine of claim 9, wherein the thrust reverser further includes means for directing the reverse thrust relative to a direction of travel of the engine.

15. The engine of claim 14, wherein the means for directing includes a door.

16. The engine of claim 14, wherein the means for directing includes vanes.

17. The engine of claim 9, wherein the means for ejecting is to increase a pressure of the portion of the air extracted by the means for extracting, the means for ejecting to eject the portion of the air at an ejection speed to overcome external air pressure.

18. A method comprising:

coupling a cascade of a thrust reverser to an engine of an aircraft, the cascade to direct air from a nacelle of the engine to generate reverse thrust relative to a direction of travel of the aircraft;

coupling an air ejector to the engine; and

forming an air ejection location on an exterior surface of the engine, the air ejection location to be formed forward of the cascade relative to the direction of travel of the aircraft, the air ejector to eject air via the air ejection location.

19. The method of claim 18, further including coupling an air extractor to the engine, the air extractor to be communicatively coupled to the air ejector.

20. The method of claim 19, wherein the nacelle of the engine includes a diverter fairing, and further including forming an opening in the diverter fairing, the air extractor to be in communication with the opening.