Translating nozzle for mixed flow turbofan engine

• US 10,641,208 B2
• Filed: 11/27/2017
• Issued: 05/05/2020
• Est. Priority Date: 11/27/2017
• Status: Active Grant

• Current Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Lacko, Anthony
• Primary Examiner(s): Nguyen, Andrew H
• Application Number:
  US15/822,505
• Publication Number:
  US 20190162136A1
• Time in Patent Office: Days
• 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 1/70 using thrust reverser flaps or doors mounted on the fan housing
• CPC Class Codes: F02K 1/763 with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines

Abstract

A thrust reverser for a gas turbine engine includes a reverser door pivotally mounted to a frame, an exhaust duct translationally mounted to the frame and an actuator having an actuator rod connected to the reverser door and to the exhaust duct.

Claims

1. A thrust reverser, comprising:

a reverser door pivotally mounted to a frame;

an exhaust duct translationally mounted to the frame;

a first actuator having a first actuator rod connected to the reverser door and to the exhaust duct;

a first door link connecting the reverser door to the first actuator rod;

a first translating member connecting the exhaust duct to the first actuator rod;

a first support member mounted to the frame, the first translating member configured to translate linearly with respect to the first support member;

a first beam link connecting the first translating member to the first actuator rod; and

a second actuator having a second actuator rod connected to the reverser door and to the exhaust duct,

wherein the frame comprises a first side beam and wherein the reverser door is pivotally mounted to the first side beam and the exhaust duct is translationally mounted to the first side beam and

wherein the frame comprises a second side beam and wherein the reverser door is pivotally mounted to both the first side beam and the second side beam.

2. The thrust reverser of claim 1, further comprising a second support member mounted to the frame and wherein the first translating member is configured to translate linearly with respect to the second support member.

3. The thrust reverser of claim 1 wherein the first translating member comprises a first beam configured to translate linearly with respect to the first support member.

4. The thrust reverser of claim 3, wherein the first translating member comprises a second beam spaced apart from the first beam and wherein the first beam and the second beam are connected by one or more rung members.

5. The thrust reverser of claim 3, further comprising a bearing system positioned between the first beam and the first support member.

6. The thrust reverser of claim 1, wherein the first actuator further comprises a base connected to the frame and wherein the first actuator rod is configured to translate linearly with respect to the base.

7. The thrust reverser of claim 1, further comprising a second door link connecting the reverser door to the second actuator rod, a second translating member connecting the exhaust duct to the second actuator rod and a second beam link connecting the second translating member to the second actuator rod.

8. A thrust reverser for a turbofan engine, comprising:

an upper reverser door pivotally mounted to a frame and a lower reverser door pivotally mounted to the frame;

an exhaust duct translationally mounted to the frame;

a first actuator having a first actuator rod connected to the upper reverser door, the lower reverser door and the exhaust duct;

a second actuator having a second actuator rod connected to the upper reverser door, the lower reverser door and the exhaust duct;

a first upper door link connecting the upper reverser door to the first actuator rod;

a first lower door link connecting the lower reverser door to the first actuator rod;

a first translating member connecting the exhaust duct to the first actuator rod;

a first beam link connecting the first translating member to the first actuator rod; and

a first support member mounted to the frame, the first translating member configured to translate linearly with respect to the first support member;

wherein the frame comprises a first side beam and wherein the upper reverser door is pivotally mounted to the first side beam and the exhaust duct is translationally mounted to the first side beam and

wherein the frame comprises a second side beam and wherein the upper reverser door is pivotally mounted to both the first side beam and the second side beam.

9. The thrust reverser of claim 8, further comprising a second upper door link connecting the upper reverser door to the second actuator rod.

10. The thrust reverser of claim 9, further comprising a second lower door link connecting the lower reverser door to the second actuator rod.

11. The thrust reverser of claim 10, further comprising a second translating member connecting the exhaust duct to the second actuator rod and a second support member mounted to the frame, the second translating member configured to translate linearly with respect to the second support member.

12. The thrust reverser of claim 11, further comprising a second beam link connecting the second translating member to the second actuator rod.

13. A gas turbine engine, comprising a core engine;

a nacelle surrounding the core engine;

a fan operably connected to the core engine and configured to drive air along a flow path in a bypass duct between the nacelle and an outer casing of the core engine;

a mixing section where exhaust from the core engine is mixed with air in the flow path as the air exits the flow path and

a thrust reverser downstream of the mixing section, wherein the thrust reverser comprises an upper reverser door pivotally mounted to a frame and a lower reverser door pivotally mounted to the frame,

an exhaust duct translationally mounted to the frame,

a first actuator having a first actuator rod connected to the upper reverser door, the lower reverser door and the exhaust duct,

a second actuator having a second actuator rod connected to the upper reverser door, the lower reverser door and the exhaust duct,

a first translating member connecting the exhaust duct to the first actuator rod,

a first support member mounted to the frame, the first translating member configured to translate linearly with respect to the first support member,

a first beam link connecting the first translating member to the first actuator rod,

a first upper door link connecting the upper reverser door to the first actuator rod,

a first lower door link connecting the lower reverser door to the first actuator rod,

wherein the frame comprises a first side beam and wherein the upper reverser door is pivotally mounted to the first side beam and the exhaust duct is translationally mounted to the first side beam and

wherein the frame comprises a second side beam and wherein the upper reverser door is pivotally mounted to both the first side beam and the second side beam.

14. The gas turbine engine of claim 13, wherein the thrust reverser further comprises

a second upper door link connecting the upper reverser door to the second actuator rod,

a second lower door link connecting the lower reverser door to the second actuator rod,

a second translating member connecting the exhaust duct to the second actuator rod,

a second support member mounted to the frame, the second translating member configured to translate linearly with respect to the second support member and a second beam link connecting the second translating member to the second actuator rod.