Dual turn thrust reverser cascade systems and methods

Patent metadata

Field	Value
Publication number	US-10724475-B2
Application number	US-201615277900-A
Country	US
Kind code	B2
Filing date	Sep 27, 2016
Priority date	Sep 27, 2016
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

Systems and methods are provided for a thrust reverser system with a straight vane thrust reverser cascade. The thrust reverser system may also include a blocker door and a turning door. The blocker door may divert air flowing within a bypass flow path of the aircraft propulsor to flow through the thrust reverser cascade. The turning door may then deflect air flowing from the thrust reverser cascade to provide reverse thrust. The straight vane thrust reverser cascade may allow for increased reverse thrust and/or a smaller, more efficient, aircraft propulsor.

First claim

What is claimed is:

1. An aircraft propulsor comprising:
a nacelle comprising a thrust reverser aperture;
a core engine circumscribed by the nacelle and comprising a plurality of fan blades configured to rotate around a first axis, wherein the nacelle and the core engine define, at least in part, a bypass flow path configured to direct airflow from the plurality of fan blades of the core engine;
a thrust reverser cascade configured to be at least partially disposed within the thrust reverser aperture, comprising a plurality of straight cascade vanes coupled to the nacelle, arranged substantially orthogonal to the first axis, and configured to permit airflow from the bypass flow path through the cascade vanes;
a blocker door disposed between the nacelle and the core engine and configured to move between at least a first blocker door position and a second blocker door position, wherein the blocker door in the first blocker door position blocks at least a portion of the bypass flow path; and
a first turning door and a second turning door disposed within the thrust reverser aperture and configured to move between at least a first turning door position and a second turning door position, wherein the first turning door and the second turning door in the first turning door position are configured to deflect airflow from the cascade vanes to a direction with a component opposite that of airflow within the bypass flow path, and
wherein the second turning door is disposed between the thrust reverser cascade and the first turning door, such that the second turning door in the second turning door position is enclosed within the thrust reverser aperture by the first turning door.

2. The aircraft propulsor of claim 1 , wherein the blocker door and the first and second turning doors are coupled together.

3. The aircraft propulsor of claim 2 , wherein the blocker door and the first and second turning doors are coupled together via one or more drag links.

4. The aircraft propulsor of claim 2 , wherein the blocker door is configured to move from the first blocker door position to the second blocker door position substantially simultaneously with the first and second turning doors moving from the first turning door position to the second turning door position.

5. The aircraft propulsor of claim 1 , wherein the blocker door is configured to move independently of the first and second turning doors.

6. The aircraft propulsor of claim 1 , wherein the thrust reverser cascade is coupled to at least one of the blocker door and/or the first and second turning doors.

7. The aircraft propulsor of claim 1 , wherein the thrust reverser cascade is configured to move between a first cascade position and a second cascade position, and wherein at least the first cascade position is configured to permit airflow from the bypass flow path through the cascade vanes.

8. The aircraft propulsor of claim 7 , wherein the thrust reverser cascade is coupled to at least one of the blocker door and/or the first turning door, is configured to move to the first cascade position responsive to the blocker door moving to the first blocker door position and/or the first turning door moving to the first turning door position, and is configured to move to the second cascade position responsive to the blocker door moving to the second blocker door position and/or the first turning door moving to the second turning door position.

9. The aircraft propulsor of claim 1 , wherein the thrust reverser cascade is fixed in a position where at least a portion of the thrust reverser cascade is disposed within the thrust reverser aperture.

10. The aircraft propulsor of claim 1 , wherein the second turning door is configured to move responsive to movement of the first turning door.

11. The aircraft propulsor of claim 1 , wherein the direction with the component opposite that of airflow within the bypass flow path is a direction 135 degrees or more relative to the airflow energized by the core engine within the bypass flow path.

12. The aircraft propulsor of claim 1 , wherein the thrust reverser cascade is disposed circumferentially around the core engine, and wherein each straight cascade vane is arranged substantially orthogonal to the first axis.

13. The aircraft propulsor of claim 1 , wherein the thrust reverser cascade further comprises angled and/or curved vanes, wherein at least a portion of the angled and/or curved vanes are parallel to the first axis.

14. An aircraft comprising the aircraft propulsor of claim 1 , the aircraft comprising:
a fuselage; and
a wing, wherein the aircraft propulsor is coupled to at least one of the fuselage and/or the wing.

15. The aircraft of claim 14 , further comprising:
a controller, communicatively coupled to the blocker door and/or the first and second turning doors and configured to provide instructions to move the blocker door between the first blocker door position and the second blocker door position and/or move the first and second turning doors between the first turning door position and the second turning door position, wherein the blocker door and the first and second turning doors are coupled together and the controller is communicatively coupled to the blocker door or the first and second turning doors.

16. The aircraft of claim 15 , wherein the blocker door is configured to move independently of the first and second turning doors and the controller is communicatively coupled to the blocker door and the first and second turning doors.

17. A method of operating the aircraft propulsor of claim 1 , comprising:
operating the core engine by rotating the plurality of fan blades around the first axis to direct airflow through at least the bypass flow path of the aircraft propulsor;
moving the blocker door to the first blocker door position to flow air from the bypass flow path through the thrust reverser cascade; and
moving the first turning door and the second turning door to the first turning door position to deflect airflow from the cascade vanes to the direction with the component opposite that of airflow within the bypass flow path.

18. The method of claim 17 , wherein the blocker door and the first and second turning doors are moved substantially simultaneously.

Assignees

• Boeing Co

Inventors

• Chuck Chen
• Vandemark Zachariah B

Classifications

• Y02T50/60

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

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F05D2250/711

  convex · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title