Thrust reverser system with translating-rotating blocker doors and method of operation

• US 10,006,405 B2
• Filed: 11/30/2012
• Issued: 06/26/2018
• Est. Priority Date: 11/30/2012
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Stuart, Alan Roy, Cosgrove, James Michael
• Primary Examiner(s): Kim, Ted
• Application Number:
  US13/689,981
• Publication Number:
  US 20140353399A1
• Time in Patent Office: 2,034 Days
• Field of Search: 602262, 60230, 23926519, 23929531, 244110 B
• 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: F05D 2260/50 Kinematic linkage, i.e. transmission of position
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thrust reverser system and operation suitable for turbofan engines. Blocker doors of the thrust reverser system have stowed positions in which each door is disposed between a fixed structure and a translating cowl of the engine. The translating cowl is translated in an aft direction of the engine to define at least one opening with the fixed structure, after which the translating cowl is further translated aft to deploy linkage mechanisms that are received in slots recessed into the blocker doors and pivotably connect the doors to the fixed structure. Deployment of the linkage mechanisms from the slots causes the blocker doors to rotate to a deployed position in which each door extends across a bypass duct of the engine and diverts bypass air within the duct through the opening.

Claims

1. A thrust reverser system for a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising:

a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween;

a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction;

blocker doors mounted to the nacelle and having stowed positions and deployed positions, each of the blocker doors having a first end, an oppositely-disposed second end, a radially inner surface between the first and second ends, and at least one slot recessed into the radially inner surface; and

linkage mechanisms connecting the blocker doors to the fixed structure, each of the linkage mechanisms comprising a first link pivotably coupled to the fixed structure and a second link pivotably coupled to one of the blocker doors, the first and second links being received in the slots recessed into the radially inner surfaces of the blocker doors when the blocker doors are in the stowed position, the linkage mechanisms being pivotably connected to the blocker doors so that translation of the translating cowl in the aft direction causes the first and second links to be displaced from the slots as each of the blocker doors moves to the deployed position thereof whereat each of the blocker doors extends across the bypass duct and diverts bypass air within the bypass duct through the circumferential opening;

wherein the linkage mechanisms consist of the first and second links, first pivotal connections that pivotably couple the first and second links to each other, second pivotal connections that pivotably couple the first links to the fixed structure, and third pivotal connections that pivotably couple the second links to the blocker doors.

2. The thrust reverser system according to claim 1, wherein the linkage mechanisms and the translating cowl cooperate so that the blocker doors initially translate aft with the translating cowl so as not to project into the bypass duct and thereafter rotate to extend across the bypass duct.

3. The thrust reverser system according to claim 2, wherein at least one of the second links associated with each of the blocker doors comprises a feature that engages the blocker door to which the second link is pivotably coupled to cause the blocker door to rotate.

4. The thrust reverser system according to claim 3, wherein the linkage mechanisms and the blocker doors are configured so that air flow through the bypass duct inhibits rotation of the blocker doors until the features of the second links engage the blocker doors.

5. The thrust reverser system according to claim 1, further comprising means associated with the linkage mechanisms for biasing the blocker doors toward the stowed positions thereof.

6. The thrust reverser system according to claim 1, wherein the first ends of the blocker doors are pivotably coupled to the translating cowl.

7. The thrust reverser system according to claim 1, wherein the blocker doors are not pivotably coupled to the core cowl.

8. The thrust reverser system according to claim 1, wherein the first and second links are completely received in the slots when the blocker doors are in the stowed positions thereof.

9. The thrust reverser system according to claim 1, wherein the first and second links do not to protrude into the bypass duct when the blocker doors are in the stowed positions thereof.

10. The thrust reverser system according to claim 1, wherein the circumferential opening comprises a cascade.

11. A thrust reverser system installed in a high-bypass turbofan engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising:

a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the high-bypass turbofan engine away from the fan cowl to define a circumferential opening therebetween, the translating cowl having a radially inner wall that defines a first portion of a radially outer flow surface of the bypass duct;

a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction, the fixed structure comprising a radially inner wall that defines a second portion of the radially outer flow surface of the bypass duct, the fixed structure comprising at least one cascade that is exposed to the bypass duct when the translating cowl is translated in the aft direction and through which bypass air within the bypass duct is diverted when the translating cowl is translated in the aft direction;

blocker doors mounted to the nacelle and having stowed positions and deployed positions, each of the blocker doors having a first end pivotably coupled to the translating cowl, an oppositely-disposed second end, a radially inner surface between the first and second ends, and at least one slot recessed into the radially inner surface, the blocker doors being disposed between the fixed structure and the translating cowl so that when in the stowed position the first ends thereof are adjacent the inner wall of the fixed structure, the second ends thereof are adjacent the inner wall of the translating cowl, and the radially inner surfaces thereof define a third portion of the radially outer flow surface of the bypass duct that is continuous with the first and second portions of the radially outer flow surface defined by the translating cowl and the fixed structure; and

linkage mechanisms connecting the blocker doors to the fixed structure but not to the translating cowl or the core cowl, each of the linkage mechanisms consist of first and second links, first pivotal connections that pivotably couple the first and second links to each other, second pivotal connections that pivotably couple the first links to the fixed structure, and third pivotal connections that pivotably couple the second links to the blocker doors, the first and second links being completely received in the slots recessed into the radially inner surfaces of the blocker doors so as not to protrude into the bypass duct when the blocker doors are in their stowed positions, the linkage mechanisms being pivotably connected to the blocker doors so that translation of the translating cowl in the aft direction causes the first and second links to be displaced from the slots as each of the blocker doors moves to the deployed position thereof whereat each of the blocker doors extends across the bypass duct and diverts bypass air within the bypass duct through the cascade of the fixed structure.

12. The thrust reverser system according to claim 11, wherein the linkage mechanisms and the translating cowl cooperate so that the blocker doors initially translate aft with the translating cowl so as not to project into the bypass duct and thereafter rotate to extend across the bypass duct.

13. The thrust reverser system according to claim 12, wherein each of the second links comprises a feature, each of the blocker doors comprises a stop, and the features of the second links engage the stops of the blocker doors to cause the blocker doors to rotate.

14. The thrust reverser system according to claim 13, wherein the linkage mechanisms and the blocker doors are configured so that air flow through the bypass duct inhibits rotation of the blocker doors until the features of the second links engage the stops of the blocker doors.