Split sleeve hidden door thrust reverser

Patent metadata

Field	Value
Publication number	US-2016160799-A1
Application number	US-201414534988-A
Country	US
Kind code	A1
Filing date	Nov 6, 2014
Priority date	Nov 6, 2014
Publication date	Jun 9, 2016
Grant date	—

Abstract

A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve.

First claim

I claim:

1 . A thrust reverser of an aircraft comprising:
a primary sleeve; and a secondary sleeve coupled to a blocker door, wherein a stroke associated with the primary sleeve is different from a stroke associated with the secondary sleeve.

2 . The thrust reverser of claim 1 , wherein the secondary sleeve is coupled to a first link, and wherein the first link is coupled to a crank, and wherein the crank is coupled to a second link, and wherein the second link is coupled to the blocker door.

3 . The thrust reverser of claim 2 , wherein the first link is configured to be oriented in a substantially axial direction relative to an axis of the thrust reverser when the thrust reverser is fully deployed.

4 . The thrust reverser of claim 2 , wherein the blocker door is configured to provide load from the blocker door through the second link and the crank to a fixed structure of the aircraft.

5 . The thrust reverser of claim 1 , further comprising:
a ring configured to couple to the blocker door.

6 . The thrust reverser of claim 1 , wherein the blocker door is configured to be stowed above a skin associated with at least one of the primary sleeve and a duct when the thrust reverser is stowed.

7 . The thrust reverser of claim 1 , wherein the primary sleeve and the secondary sleeve are configured to be driven via independent actuation mechanisms.

8 . A thrust reverser of an aircraft comprising:
a movable primary sleeve with an exterior surface exposed to the exterior free air stream around the thrust reverser during flight, the primary sleeve movable between a stowed position and a deployed position corresponding to reverse thrust operation; a movable secondary sleeve that includes a cascade for redirecting air from a fan duct during reverse thrust operation, the secondary sleeve movable between a stowed position and a deployed position corresponding to reverse thrust operation; and wherein the primary sleeve covers the cascade when the primary sleeve is in its stowed position, and the cascade is exposed to the exterior free air stream when the primary sleeve is in its deployed position.

9 . A thrust reverser according to claim 8 and further comprising:
a blocker door coupled to the secondary sleeve, the blocker door movable between a stowed position and a deployed position corresponding to reverse thrust operation; and
wherein the blocker door is driven from its stowed position to its deployed position when the secondary sleeve moves from its stowed position to its deployed position.

10 . A thrust reverser according to claim 9 :
wherein the primary sleeve further comprises an interior skin and an exterior skin, the blocker door being fully positioned between the interior skin and the exterior skin when the blocker door is in its stowed position.

11 . A thrust reverser according to claim 8 , further comprising:
a first sliding mechanism coupled with the primary sleeve such that the primary sleeve is movable by sliding relating to a fixed structure of the thrust reverser along a sliding axis defined by the first sliding mechanism; and a second sliding mechanism coupled with the secondary sleeve such that the secondary sleeve is movable by sliding relating to a fixed structure of the thrust reverser along a sliding axis defined by the second sliding mechanism.

12 . A thrust reverser of an aircraft comprising:
a movable primary sleeve with an exterior surface exposed to the exterior free air stream around the thrust reverser during flight, the primary sleeve movable between a stowed position and a deployed position corresponding to reverse thrust operation; a movable secondary sleeve, the secondary sleeve movable between a stowed position and a deployed position corresponding to reverse thrust operation; a blocker door coupled to the secondary sleeve and movable between a stowed position and a deployed position corresponding to reverse thrust operation wherein the blocker door redirects air through a cascade; wherein when the secondary sleeve moved from its stowed position to its deployed position it drives the blocker door from its stowed position to its deployed position.

13 . A thrust reverser according to claim 12 wherein the cascade is mounted on and moves with the secondary sleeve.

14 . A thrust reverser according to claim 13 wherein in the stowed position of the secondary sleeve at least a portion of the cascade radially overlaps a fan case of a turbofan engine.

15 . A thrust reverser according to claim 14 wherein the blocker door is hidden from exposure to the air stream in a fan duct when the blocker door is in its stowed position.

Assignees

• Rohr Inc

Inventors

• Gormley Timothy

Classifications

• F02K1/766

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · 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

• F05D2260/50

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

• F02K1/763 Primary

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

• F05D2260/57

  using servos, independent actuators, etc. · CPC title