Reconfigurable exhaust nozzle for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11408368-B2
Application number	US-202016836080-A
Country	US
Kind code	B2
Filing date	Mar 31, 2020
Priority date	Mar 31, 2020
Publication date	Aug 9, 2022
Grant date	Aug 9, 2022

Abstract

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

First claim

What is claimed is:

1. A propulsion unit for an aircraft, the unit comprising
a gas turbine engine arranged along an axis including an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow, and
an exhaust system coupled to the gas turbine engine to receive mixed bypass and core flows from the gas turbine engine, the exhaust system including (i) a static outer structure arranged around the axis to provide an outer boundary surface of a primary exhaust system flow path, (ii) a noise management structure including a plug that defines an inner boundary surface of the primary exhaust system flow path that is mounted for movement along the axis, wherein the noise management structure is configured to axially translate relative to the static outer structure between a slid-forward take-off position, a slid-forward thrust-reverse position, and a slid-aft cruise position to provide a reconfigurable exhaust nozzle that adjusts a variable nozzle throat area of the exhaust system to vary noise produced by the gas turbine engine during operation of the gas turbine engine, and (iii) a thrust reverser unit including a plurality of pivot doors configured to pivot relative to the outer structure about a pivot axis between a stored arrangement in which the plurality of pivot doors engage the static outer structure to provide a portion of the outer boundary surface of the primary exhaust system flow path and a thrust-reversing arrangement in which each pivot door blocks at least some flow of the mixed bypass and core flows along the primary exhaust system flow path so as to direct the at least some flow of the mixed bypass and core flows out of the primary exhaust system flow path and create reverse thrust, wherein the plurality of pivot doors have an edge that has a corresponding shape to the inner boundary surface and engages the inner boundary surface when the plurality of pivot doors are in the thrust-reversing arrangement,
wherein the plug includes a plug body that extends axially between a nose and a tail end and a plurality of struts that extend radially outward from the plug body to the static outer structure,
wherein the noise management structure further includes a plurality of actuator units arranged to extend between and interconnect the plurality of struts and the static outer structure to change the plug between the slid-forward take-off position, the slid-forward thrust-reverse position, and the slid-aft cruise position.

2. The propulsion unit of claim 1 , wherein the plurality of actuator units each include an actuator with a first end coupled to a radially outer end of a corresponding strut included in the plurality of struts and a second end coupled to the static outer structure, a guide track coupled to the static outer structure, and at least one carriage coupled to the radially outer end of the corresponding strut and mounted on the guide track to translate axially along the guide track, and wherein the actuator is configured to translate the at least one carriage axially along the guide track to change the plug between the slid-forward take-off position, the slid-forward thrust-reverse position, and the slid-aft cruise position.

3. The propulsion unit of claim 1 , wherein the plurality of struts includes at least three struts spaced apart circumferentially about the axis and the plurality of pivot doors includes at least two pivot doors arranged circumferentially between adjacent struts of the plurality of struts.

4. The propulsion unit of claim 1 , wherein the plurality of struts includes at least four struts spaced apart circumferentially about the axis and the plurality of pivot doors includes at least two pivot doors.

5. The propulsion unit of claim 1 , wherein the slid-forward take-off position and the slid-forward thrust-reverse position are the same position along the axis.

6. The propulsion unit of claim 1 , wherein the slid-forward take-off position of the plug provides a maximum nozzle throat area between the outer boundary surface of the static outer structure and the inner boundary surface of the plug.

7. The propulsion unit of claim 6 , wherein the slid-aft cruise position of the plug provides a minimum nozzle throat area between the outer boundary surface of the static outer structure and the inner boundary surface of the plug that is less than the maximum nozzle throat area.

8. The propulsion unit of claim 7 , wherein the plug is configured to translate axially between a plurality of positions between the slid-forward take-off position and the slid-aft cruise position.

9. An exhaust system for use with a gas turbine engine, the exhaust system comprising
a static outer structure arranged around an axis to provide an outer boundary surface of a primary exhaust system flow path of the exhaust system,
a noise management structure including a plug that defines an inner boundary surface of the primary exhaust system flow path that is mounted for movement along the axis, wherein the noise management structure is configured to axially translate relative to the static outer structure between a slid-forward take-off position, a slid-forward thrust-reverse position, and a slid-aft cruise position to provide a reconfigurable exhaust nozzle that adjusts a variable nozzle throat area of the exhaust system, and
a thrust reverser unit including a plurality of pivot doors configured to pivot relative to the outer structure about a pivot axis between a stored arrangement in which the plurality of pivot doors provide a portion of the outer boundary surface of the primary exhaust system flow path and an thrust-reversing arrangement in which each pivot door blocks at least some flow along the primary exhaust system flow path so as to direct the at least some flow out of the primary exhaust system flow path and create reverse thrust,
wherein the plurality of pivot doors have a corresponding shape to the inner boundary surface of the plug in the slid-forward thrust-reverse position at a location radially inward of the plurality of pivot doors when the plurality of pivot doors are in the thrust-reversing arrangement,
wherein the plug includes a plug body that extends axially between a nose and a tail end and a plurality of struts that extend radially outward from the plug body to the static outer structure,
wherein the noise management structure further includes a plurality of actuators arranged to extend between and interconnect the plurality of struts and the static outer structure to change the plug between the slid-forward take-off position, the slid-forward thrust-reverse position, and the slid-aft cruise position.

10. The exhaust system of claim 9 , wherein the plurality of struts includes at least three struts spaced apart circumferentially about the axis and the plurality of pivot doors includes at least two pivot doors arranged circumferentially between adjacent struts of the plurality of struts.

11. The exhaust system of claim 9 , wherein the plurality of struts includes at least four struts spaced apart circumferentially about the axis and the plurality of pivot doors includes at least two pivot doors.

12. The exhaust system of claim 9 , wherein the slid-forward take-off position and the slid-forward thrust-reverse position are substantially the same position along the axis.

13. The exhaust system of claim 9 , wherein the slid-forward take-off position of the plug provides a maximum nozzle throat area between the outer boundary surface of the static outer structure and the inner boundary surface of the plug.

14. The exhaust system of claim 13 , wherein the slid-aft crui

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Sutterfield David L
• Taylor Todd S
• Petty Jack D
• Sanderson Andrew
• Lerg Bryan H

Classifications

• F02K1/763

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

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F02K1/04 Primary

  Mounting of an exhaust cone in the jet pipe · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title