PIVOT THRUST REVERSER SURROUNDING INNER SURFACE OF BYPASS DUCT

• US 20140239083A1
• Filed: 02/19/2014
• Published: 08/28/2014
• Est. Priority Date: 02/22/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Chandler, Jesse M., Bomzer, T. David
• Granted Patent: US 9,631,578 B2
• Time in Patent Office: Days
• US Class Current: 239/11
• CPC Class Codes: B23P 19/04 for assembling or disassembling parts
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C
• CPC Class Codes: B64D 33/04 of exhaust outlets or jet pipes exhaust outlets for combustion engines in general F01N; jet pipes or nozzles for jet-propulsion plants per se F02K; plants characterised by the form or arrangement of the jet pipe or nozzle F02K ; attitude, flight direction, or altitude control by jet reaction B64C
• CPC Class Codes: F02K 1/60 by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• CPC Class Codes: F02K 1/605 the aft end of the engine cowling being movable to uncover openings for the reversed flow
• CPC Class Codes: F02K 1/62 by blocking the rearward discharge by means of flaps
• CPC Class Codes: F02K 1/64 Reversing fan flow
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: F02K 1/763 with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• CPC Class Codes: F05D 2260/50 Kinematic linkage, i.e. transmission of position
• CPC Class Codes: Y10T 29/49229 Prime mover or fluid pump making

Abstract

One embodiment of the present invention includes a pivot thrust reverser including 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.

Claims

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; and

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, and

wherein in a 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, further comprising an actuator configured to pivot both the first pivot door and the second pivot door from the stowed position to the deployed position, 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 2, 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 axises that are each positionally fixed relative to the gas turbine engine assembly.

4. The pivot thrust reverser of claim 2, further comprising a first linkage on the first pivot door and a second linkage on the second pivot door where the first linkage on the first pivot door and the second linkage on the second pivot door both connect to the actuator.

5. The pivot thrust reverser of claim 4, 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.

6. The pivot thrust reverser of claim 1, 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.

7. The pivot thrust reverser of claim 6, wherein the second pivot door is spaced approximately 180°

from the first pivot door relative to the axis of the gas turbine engine assembly.

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

9. The pivot thrust reverser of claim 8, further comprising a second cutout on the second pivot door.

10. The pivot thrust reverser of claim 9, wherein both the first cutout and the second cutout are each arc-shaped.

11. The pivot thrust reverser of claim 10, 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.

12. The pivot thrust reverser of claim 11, 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.

13. 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, 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, wherein the actuator is located between the surface of the bypass duct and the outer surface of the nacelle;

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.

14. The method of claim 13, wherein both the first pivot door and the second pivot door are pivotally deployed by the actuator on respective pivot axises each positionally fixed relative to the gas turbine engine assembly.

15. A pivot thrust reverser comprising:

a first pivot door with an aft edge;

a second pivot door with an aft edge such that when the first pivot door and the second pivot door are in a deployed position the aft edge of the first pivot door and the aft edge of the second pivot door face each other;

a first cutout on the first pivot door; and

a linkage of the first pivot door and a linkage of the second pivot door each connected to an actuator which pivots the first pivot door and the second pivot door on pivot axises that are positionally fixed.

16. The pivot thrust reverser of claim 15, further comprising a second cutout on the second pivot door.

17. The pivot thrust reverser of claim 16, wherein both the first cutout and the second cutout are each arc-shaped.

18. The pivot thrust reverser of claim 17, wherein the aft edge of the first pivot door and the aft edge of the second pivot each contain an arc-shaped cutout.