Decoupled translating sleeve

Patent metadata

Field	Value
Publication number	US-2016201604-A1
Application number	US-201514595432-A
Country	US
Kind code	A1
Filing date	Jan 13, 2015
Priority date	Jan 13, 2015
Publication date	Jul 14, 2016
Grant date	—

Abstract

A thrust reverser for a nacelle may include a translating sleeve. A plurality of lint blocker doors may be coupled to the translating sleeve. The translating sleeve may translate along a line of action which is non-parallel to an engine centerline. The non-parallel translation of the translating sleeve may prevent interference between the translating sleeve and surrounding components.

First claim

I claim:

1 . A nacelle configured to house an engine, the nacelle comprising:
a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position; and a plurality of blocker doors coupled to the translating sleeve, wherein the translating sleeve comprises a line of action which is non-parallel to a centerline of the engine, and wherein in response to the translating sleeve translating along the line of action from the stowed position to the deployed position, the plurality of blocker doors are configured to deploy within a bypass air duct of the nacelle.

2 . The nacelle of claim 1 , wherein the plurality of blocker doors are linkless blocker doors.

3 . The nacelle of claim 1 , wherein a first blocker door in the plurality of blocker doors comprises a longer radial length than a second blocker door in the plurality of blocker doors.

4 . The nacelle of claim 1 , wherein, in the deployed position, the translating sleeve is not concentric with an inner fixed structure of the nacelle.

5 . The nacelle of claim 4 , wherein in the stowed position, the translating sleeve is concentric with the inner fixed structure.

6 . The nacelle of claim 1 , wherein the translating sleeve is configured to translate aft and downward relative to the centerline of the engine.

7 . The nacelle of claim 1 , wherein the translating sleeve is configured to translate radially outward from the centerline of the engine.

8 . The nacelle of claim 1 , wherein the line of action is defined by a track and slider mechanism.

9 . A nacelle for an aircraft engine comprising:
a thrust reverser comprising a first translating sleeve configured to translate along a first line of action, wherein the first line of action is non-parallel to a centerline of the aircraft engine, and a first linkless blocker door coupled to the first translating sleeve.

10 . The nacelle of claim 9 , further comprising a second linkless blocker door coupled to the first translating sleeve, wherein the second linkless blocker door comprises a larger radial length than a radial length of the first linkless blocker door.

11 . The nacelle of claim 9 , further comprising a second translating sleeve configured to translate along a second line of action, wherein the second line of action is non-parallel to the centerline of the aircraft engine.

12 . The nacelle of claim 11 , wherein the second line of action is non-parallel to the first line of action.

13 . The nacelle of claim 9 , wherein in a deployed position, the first, translating sleeve is not concentric with an inner fixed structure of the nacelle.

14 . The nacelle of claim 13 , wherein in a stowed position, the first translating sleeve is concentric with the inner fixed structure.

15 . The nacelle of claim 9 , wherein the first translating sleeve is configured to translate aft and downward relative to the centerline of the aircraft engine.

16 . A nacelle adapted for housing an engine, the nacelle comprising:
a thrust reverser component configured to translate along a line of action, wherein the line of action is $n-parallel to a centerline of the engine.

17 . The nacelle of claim 16 , wherein the thrust reverser component is a translating sleeve.

18 . The nacelle of claim 1 s, wherein the thrust reverser component is a translating VAFN.

19 . The nacelle of claim 16 , wherein the thrust reverser component is configured to provide access to the engine in response to the thrust reverser component translating in an aft direction along the line of action.

20 . The nacelle of claim 16 , wherein the thrust reverser component is configured to translate aft and downward relative the centerline of the engine.

Assignees

• Rohr Inc

Inventors

• Gormley Timothy

Classifications

• F05D2250/314

  the axes being inclined in relation to each other · 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

• F05D2250/41

  with one degree of freedom · CPC title

• F02K1/76 Primary

  Control or regulation of thrust reversers · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title