Pivot thrust reverser surrounding inner surface of bypass duct

Patent metadata

Field	Value
Publication number	US-9631578-B2
Application number	US-201414184313-A
Country	US
Kind code	B2
Filing date	Feb 19, 2014
Priority date	Feb 22, 2013
Publication date	Apr 25, 2017
Grant date	Apr 25, 2017

Abstract

A pivot thrust reverser includes a first pivot door forming a first portion of a nacelle when stowed and second pivot door forming a second portion of the nacelle when stowed. The first pivot door and second pivot door each form a portion of a surface of a bypass duct when in a stowed position. In the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.

First claim

The invention claimed is:

1. A pivot thrust reverser for use in a gas turbine engine assembly, the pivot thrust reverser comprising:
a first pivot door forming a first portion of an outer surface of a nacelle when stowed;
a second pivot door spaced from the first pivot door forming a second portion of the outer surface of the nacelle when stowed, wherein the first pivot door and the second pivot door are axially aligned and radially opposite along an axis of the gas turbine engine assembly and each form a portion of a surface of a bypass duct when stowed;
an actuator configured to pivot both the first pivot door and the second pivot door from a stowed position to a deployed position;
a first linkage on the first pivot door connected to the actuator; and
a second linkage on the second pivot door connected to the actuator,
wherein in the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.

2. The pivot thrust reverser of claim 1 , wherein the actuator is located between the surface of the bypass duct and the outer surface of the nacelle.

3. The pivot thrust reverser of claim 1 , wherein the actuator pivots both the first pivot door and the second pivot door from the stowed position to the deployed position on respective pivot axes that are each positionally fixed relative to the gas turbine engine assembly.

4. The pivot thrust reverser of claim 1 , wherein the first linkage on the first pivot door and the second linkage on the second pivot door are both between the surface of the bypass duct and the outer surface of the nacelle.

5. The pivot thrust reverser of claim 1 , wherein the second pivot door is spaced approximately 180° from the first pivot door relative to the axis of the gas turbine engine assembly.

6. The pivot thrust reverser of claim 1 , further comprising a first cutout on the first pivot door.

7. The pivot thrust reverser of claim 6 , further comprising a second cutout on the second pivot door.

8. The pivot thrust reverser of claim 7 , wherein both the first cutout and the second cutout are each arc-shaped.

9. The pivot thrust reverser of claim 8 , wherein both the first cutout and the second cutout are located at aft edges of the first pivot door and the second pivot door respectively.

10. The pivot thrust reverser of claim 9 , wherein when the first pivot door and the second pivot door are in the deployed position the aft edge of the first pivot door faces the aft edge of the second pivot door.

11. A method for use in a gas turbine engine assembly, the method comprising:
providing a first pivot door, wherein the first pivot door forms both a portion of a surface of a bypass duct and a portion of an outer surface of a nacelle when in a stowed position;
providing a second pivot door spaced from the first pivot door with the first pivot door and the second pivot door being axially aligned and radially opposite along an axis of gas turbine engine assembly, wherein the second pivot door forms both a portion of the surface of the bypass duct and a portion of the outer surface of the nacelle when in the stowed position;
pivotally deploying both the first pivot door and the second pivot door from the stowed position to a deployed position by an actuator, a first linkage connecting the first pivot door to the actuator, and a second linkage connecting the second pivot door to the actuator;
circumferentially surrounding a portion of an inner surface of a bypass duct with both the first pivot door and the second pivot door when the first pivot door and the second pivot door are in the deployed position; and
redirecting a fan bypass stream during engine operation when the first pivot door and the second pivot door are in the deployed position.

12. The method of claim 11 , wherein both the first pivot door and the second pivot door are pivotally deployed by the actuator on respective pivot axes each positionally fixed relative to the gas turbine engine assembly.

13. A pivot thrust reverser for use in a gas turbine engine assembly, the pivot thrust reverser comprising:
a first pivot door forming a first portion of an outer surface of a nacelle when stowed, the first pivot door including a first cutout;
a second pivot door spaced from the first pivot door forming a second portion of the outer surface of the nacelle when stowed, wherein the pivot doors each form a portion of a surface of a bypass duct when stowed;
an actuator configured to pivot both the first pivot door and the second pivot door from a stowed position to a deployed position;
a first linkage on the first pivot door connected to the actuator; and
a second linkage on the second pivot door connected to the actuator,
wherein in the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.

14. The pivot thrust reverser of claim 13 , further comprising a second cutout on the second pivot door.

15. The pivot thrust reverser of claim 14 , wherein both the first cutout and the second cutout are each arc-shaped.

16. The pivot thrust reverser of claim 15 , wherein both the first cutout and the second cutout are located at aft edges of the first pivot door and the second pivot door respectively.

17. The pivot thrust reverser of claim 16 , wherein when the first pivot door and the second pivot door are in the deployed position the aft edge of the first pivot door faces the aft edge of the second pivot door.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M
• Bomzer T David

Classifications

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B23P19/04

  for assembling or disassembling parts · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F02K1/763 Primary

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

• F02K1/64

  Reversing fan flow · CPC title