Turbomachine thrust reverser

Patent metadata

Field	Value
Publication number	US-10145335-B2
Application number	US-201213712240-A
Country	US
Kind code	B2
Filing date	Dec 12, 2012
Priority date	Sep 28, 2012
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

First claim

We claim:

1. A thrust reverser of a gas turbine engine configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located substantially at or adjacent to a top circumferential apex of the engine, comprising:
a first cowl moveable along an axis between a stowed position and a deployed position relative to a second cowl, the first cowl in the deployed position configured to permit thrust to be redirected from the engine,
the first cowl forming a portion of a substantially annular encasement of the engine,
the first cowl directly interfacing with the second cowl of the encasement at a cowl interface that is axially extending and is more than 18 degrees circumferentially offset in a first circumferential direction from the top circumferential apex when the first cowl is in the stowed position,
the second cowl extending in the first circumferential direction from the top circumferential apex to the cowl interface, and the first cowl extending in the first circumferential direction from the cowl interface to a bottom circumferential apex, which circumferentially opposes the top circumferential apex; and
a third cowl and a fourth cowl of the encasement, the fourth cowl movable between a stowed position and a deployed position relative to the third cowl, the third cowl directly interfacing with the fourth cowl at another position that is more than 18° circumferentially offset from the top circumferential apex.

2. The thrust reverser of claim 1 , wherein the second cowl extends substantially from the top circumferential apex.

3. The thrust reverser of claim 2 , wherein the thrust reverser mounts receive a pylon at the top circumferential apex of the encasement.

4. The thrust reverser of claim 1 , wherein the first cowl and the second cowl are positioned on an inboard side of the engine, and the third cowl and the fourth cowl are positioned on an outboard side of the engine.

5. The thrust reverser of claim 1 , wherein the second cowl and the fourth cowl extend from circumferentially opposite sides of the top circumferential apex.

6. The thrust reverser of claim 1 , wherein the cowl interface is circumferentially offset from the top circumferential apex from 20 to 25 degrees.

7. The thrust reverser of claim 1 , wherein the cowl interface is circumferentially offset 32 degrees from the top circumferential apex.

8. The thrust reverser of claim 1 , wherein the first cowl moves between the deployed position and the stowed position along a path that causes the first cowl to avoid contact with a slat of the aircraft wing.

9. The thrust reverser of claim 1 , wherein the axis is aligned with a rotational axis of the gas turbine engine, wherein the first cowl extends axially from a leading edge to terminate at a trailing edge such that no portion of the first cowl extends axially past the trailing edge, wherein the interface is an axially extending interface that extends linearly from the leading edge to the trailing edge.

10. The thrust reverser of claim 1 , wherein the fourth cowl is movable between a stowed position and a deployed position relative to the third cowl, the third cowl directly interfacing with the fourth cowl at another position that is circumferentially offset from the top circumferential apex an amount that is less than the circumferential offset between the cowl interface between the first cowl and the second cowl.

11. The thrust reverser of claim 1 , wherein the fourth cowl is movable between a stowed position and a deployed position relative to the third cowl, the fourth cowl interfacing with the first cowl at a bottom circumferential apex, the first cowl separate and distinct from the fourth cowl.

12. An engine configured to connect to an aircraft wing via a pylon located substantially at or adjacent to a top circumferential apex for the engine, comprising:
a first cowl;
a second cowl extending from a thrust reverser mount located substantially at the top circumferential apex in a first circumferential direction to a cowl interface, the first cowl extending in the first circumferential direction from the cowl interface to a bottom circumferential apex, the first cowl being translatable along an axis relative to the second cowl to selectively redirect thrust from the engine, wherein the second cowl interfaces with the first cowl at the cowl interface at a circumferential location that is more than 18° circumferentially offset from the top circumferential apex in the first circumferential direction, the cowl interface an axially extending cowl interface; and
a third cowl extending from the thrust reverser mount located substantially at the top circumferential apex; and
a fourth cowl translatable relative to the third cowl to selectively redirect thrust from the engine, wherein the fourth cowl is separate and distinct from the third cowl.

13. The engine of claim 12 , wherein a twelve o'clock position is the top circumferential apex of the engine.

14. The engine of claim 12 , wherein the thrust reverser mount is configured to receive the pylon such that the pylon extends from adjacent to the top circumferential apex.

15. The engine of claim 12 , wherein the first cowl extends axially from a leading edge and terminates at a trailing edge, wherein the cowl interface is an axially extending interface that extends linearly from the leading edge to the trailing edge.

16. The engine of claim 12 , wherein the axis is parallel to a rotational axis of the engine.

17. An engine configured to connect to an aircraft wing via a pylon located substantially at or adjacent to a top circumferential apex for the engine, comprising:
a first cowl;
a second cowl extending from a thrust reverser mount located substantially at the top circumferential apex in a first circumferential direction to a cowl interface, the first cowl extending in the first circumferential direction from the cowl interface to a bottom circumferential apex, the first cowl being translatable along an axis relative to the second cowl to selectively redirect thrust from the engine, wherein the second cowl interfaces with the first cowl at the cowl interface at a circumferential location that is more than 18° circumferentially offset from the top circumferential apex in the first circumferential direction, the cowl interface an axially extending cowl interface; and
a third cowl and a fourth cowl of the encasement, the fourth cowl movable between a stowed position and a deployed position relative to the third cowl, the third cowl directly interfacing with the fourth cowl at another position that is circumferentially offset from the top circumferential apex an amount that is different than the circumferential offset between the cowl interface between the first cowl and the second cowl.

Assignees

• United Technologies Corp

Inventors

• Gukeisen Robert L
• Mercier Claude
• Malecki Robert E

Classifications

• F05D2250/34

  translated · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F02K1/72

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

• F02K1/64 Primary

  Reversing fan flow · CPC title

• F02K1/58 Primary

  Reversers mounted on the inner cone or the nozzle housing {or the fuselage} · CPC title