Variable area nozzle and method for operating same

Patent metadata

Field	Value
Publication number	US-11994087-B2
Application number	US-202117542926-A
Country	US
Kind code	B2
Filing date	Dec 6, 2021
Priority date	Dec 6, 2021
Publication date	May 28, 2024
Grant date	May 28, 2024

Abstract

A variable area nozzle assembly for a gas turbine engine includes a nozzle disposed about a nozzle centerline and a fixed ring radially surrounding the nozzle. The nozzle includes a radially outer surface and a radially inner surface. The radially inner surface defines an outlet cross-sectional area of the nozzle. The nozzle is movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area. With the nozzle in the first position, the radially outer surface contacts the fixed ring. With the nozzle in the second position, the radially outer surface is spaced from the fixed ring.

First claim

What is claimed is:

1. A variable area nozzle assembly for a gas turbine engine, the variable area nozzle assembly comprising:
a nozzle disposed about a nozzle centerline, the nozzle comprising a radially outer surface, a radially inner surface, an axially forward end, and an axially aft end, the radially outer surface extending from the axially forward end to the axially aft end, the radially inner surface defining an outlet cross-sectional area of the nozzle, the nozzle pivotable at the axially forward end relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area; and
a fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring, and with the nozzle in the second position the radially outer surface is radially spaced from the fixed ring, wherein the fixed ring is positioned axially between and axially spaced from the axially forward end and the axially aft end with the nozzle in the first position and the second position.

2. The variable area nozzle assembly of claim 1 , further comprising a first thrust reverser door and a second thrust reverser door, each of the first thrust reverser door and the second thrust reverser door movable between a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring and a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle.

3. The variable area nozzle assembly of claim 2 , wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position.

4. The variable area nozzle assembly of claim 3 , wherein the radially outer surface of the nozzle defines a door recess in which the fixed ring is positioned with the nozzle in the first position.

5. The variable area nozzle assembly of claim 4 , wherein with the nozzle in the first position and the first thrust reverser door and the second thrust reverser door in the respective stowed positions, the radially outer surface, the radially outer ring side, the first thrust reverser door, and the second thrust reverser door define a substantially flush exterior surface.

6. The variable area nozzle assembly of claim 1 , further comprising a plurality of actuators, each actuator of the plurality of actuators including a first actuator end pivotably mounted to the fixed ring and a second actuator end pivotably mounted to the nozzle.

7. A gas turbine engine comprising:
a fixed structure;
a nozzle comprising an axially forward end, an axially aft end, a radially outer surface, and a radially inner surface, the nozzle hingedly mounted to the fixed structure at the axially forward end, the nozzle disposed about a nozzle centerline, the radially inner surface defining an outlet cross-sectional area of the nozzle, the nozzle movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area; and
a fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring, and with the nozzle in the second position the radially outer surface is radially spaced from the fixed ring, wherein the fixed ring is positioned axially between and axially spaced from the axially forward end and the axially aft end with the nozzle in the first position and the second position.

8. The gas turbine engine of claim 7 , wherein the fixed ring is axially spaced from the fixed structure and the fixed ring is mounted to the fixed structure by at least one side beam.

9. The gas turbine engine of claim 7 , further comprising a first thrust reverser door and a second thrust reverser door, each of the first thrust reverser door and the second thrust reverser door movable between a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring and a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle.

10. The gas turbine engine of claim 9 , wherein the fixed ring comprising a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position.

11. The gas turbine engine of claim 10 , further comprising at least one actuation system mounted to the fixed ring circumferentially between the first recess and the second recess with respect to the nozzle centerline.

12. The gas turbine engine of claim 11 , wherein the at least one actuation system comprises a linear actuator and a carrier mounted to the linear actuator, the linear actuator configured to translate the carrier in a substantially axial direction, the carrier connected to each of the first thrust reverser door and the second thrust reverser door by at least one linkage.

13. The gas turbine engine of claim 7 , further comprising a plurality of actuators, each actuator of the plurality of actuators including a first actuator end pivotably mounted to the fixed ring and a second actuator end pivotably mounted to the nozzle.

14. A method of operating a variable area nozzle for a gas turbine engine, the method comprising:
pivoting an axially forward end of a nozzle relative to a nozzle centerline of the nozzle from a first position toward a second position, the nozzle comprising a radially outer surface and a radially inner surface, the radially inner surface defining an outlet cross-sectional area of the nozzle,
the radially inner surface with the nozzle in the first position defining a maximum area of the outlet cross-sectional area and the radially inner surface with the nozzle in the second position defining a minimum area of the outlet cross-sectional area, and
the radially outer surface with the nozzle in the first position contacting a fixed ring radially surrounding the nozzle, and the radially outer surface with the nozzle in the second position being radially spaced from the fixed ring, wherein the fixed ring is positioned axially between and axially spaced from the axially forward end and an axially aft of the nozzle with the nozzle in the first position and the second position.

15. The method of claim 14 , further comprising deploying a first thrust reverser door and a second thrust reverser door by moving each of the first thrust reverser door and the second thrust reverser door from a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring to a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle.

16. The method of claim 15 , wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess i

Assignees

• Rohr Inc

Inventors

• Gormley Timothy

Classifications

• F02K1/1207 Primary

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02K1/1269 Primary

  of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the internal downstream series having its flaps hinged at their downstream ends on the downstream ends of the flaps of the external downstream series hinged on a fixed structure at their upstream ends · CPC title

• F02K1/1223

  of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series · CPC title

• F02K1/1292

  of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream ends on a substantially axially movable structure · CPC title