Gas turbine engine thrust reverser system

Patent metadata

Field	Value
Publication number	US-10006404-B2
Application number	US-201213406924-A
Country	US
Kind code	B2
Filing date	Feb 28, 2012
Priority date	Feb 28, 2012
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

An example thrust reverser blocker door includes a blocker door that is movable from a stowed position to a deployed position. Flow moves through an area of a bypass flowpath when the blocker door is in the stowed position. The blocker door blocks no less than about 70% and no more than about 85% of flow through this area when the blocker door is in the deployed position, wherein the area does not extend circumferentially past the blocker door.

First claim

I claim:

1. A thrust reverser blocker door, comprising:
a blocker door moveable from a stowed position to a deployed position, wherein flow moves through an area of a bypass flowpath when the blocker door is in the stowed position, and the blocker door blocks between no less than 70% and no more than 85% of flow through this area when the blocker door is in the deployed position, wherein the area does not extend circumferentially past the blocker door.

2. The thrust reverser blocker door of claim 1 , where substantially all flow that is blocked by the blocker door moves through cascades.

3. The thrust reverser blocker door of claim 2 , wherein the cascades are within an outer nacelle that provides the bypass flowpath with a core engine of a gas turbine engine.

4. The thrust reverser blocker door of claim 2 , wherein the cascades have a forward turning angle that is between 35 degrees and 45 degrees relative to a plane normal to an engine center longitudinal axis.

5. The thrust reverser blocker door of claim 1 , wherein the blocker door extends circumferentially relative to a rotational axis of a gas turbine engine a first distance, and the area extends circumferentially a second distance that is about the same as the first distance.

6. The thrust reverser blocker door of claim 1 , wherein flow that is not blocked by the blocker door exits through an aftmost region of the bypass flowpath.

7. The thrust reverser blocker door of claim 1 , wherein the blocker door is part of a thrust reverser system, and an effective area of the thrust reverser system when the blocker door is deployed is no less than the effective area of the thrust reversing system when the blocker door is stowed, wherein the effective area is a mean exit area of a flowpath exhaust.

8. The thrust reverser blocker door of claim 1 , wherein all the flow that is not blocked by the blocker door moves through a gap between the blocker door and a core of a gas turbine engine.

9. A gas turbine engine thrust reverser system, comprising:
a nacelle that establishes a radially outer boundary of a flowpath;
a core engine that establishes a radially inner boundary of the flowpath; and
an array of blocker doors moveable from a deployed position to a stowed position, the array of blocker doors in the deployed position blocking more flow through the flowpath than the blocker doors in the stowed position, wherein the blocker doors in the deployed position permit from no less than 15% to no more than 30% of flow through the flowpath that the blocker doors in the stowed position permit.

10. The gas turbine engine thrust reverser system of claim 9 , where flow that is blocked by the blocker doors moves through cascades within the nacelle.

11. The gas turbine engine thrust reverser system of claim 10 , wherein the cascades have a forward turning angle that is between 35 degrees and 45 degrees relative to a plane normal to the engine center longitudinal axis.

12. The gas turbine engine thrust reverser system of claim 9 , wherein flow through the flowpath that is permitted by the blocker doors exits the flowpath through a flowpath exhaust at least partially provided by a trailing edge of the nacelle.

13. The gas turbine engine thrust reverser system of claim 9 , wherein an effective area of the thrust reversing system when the blocker doors is deployed is no less than the effective area of the thrust reverser system when the blocker doors is stowed, wherein the effective area is a mean exit area of a flowpath exhaust.

14. A gas turbine engine thrust reversing method, comprising:
(a) redirecting no less than 70% to no more than 85% of flow from a bypass flowpath through a cascade arrangement; and
(b) moving the remaining flow through a bypass flowpath exhaust.

15. The gas turbine engine thrust reversing method of claim 14 , wherein the cascade arrangement has a forward turning angle that is between 35 degrees and 45 degrees relative to a plane normal to an engine center longitudinal axis.

16. The gas turbine engine thrust reversing method of claim 14 , wherein blocker doors in a deployed position redirect flow from the bypass flowpath.

17. The gas turbine engine thrust reversing method of claim 14 , wherein all the remaining flow moves through a gap between the blocker door and a core of an engine.

18. The thrust reverser blocker door of claim 1 , wherein the blocker door is unapertured such that no flow blocked by the blocker door is moved through any aperture provided by the blocker door.

19. The gas turbine engine thrust reverser system of claim 9 , wherein the blocker doors are each unapertured such that no flow through the flowpath moves through any aperture provided by the blocker doors.

20. The gas turbine engine thrust reversing method of claim 16 , wherein the blocker doors are unapertured such that no flow moves through any aperture provided by the blocker doors.

Assignees

• Malecki Robert E
• United Technologies Corp

Inventors

• Malecki Robert E

Classifications

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title