Compact actuation system for flow nozzle

Patent metadata

Field	Value
Publication number	US-9464594-B2
Application number	US-201414209749-A
Country	US
Kind code	B2
Filing date	Mar 13, 2014
Priority date	Mar 13, 2013
Publication date	Oct 11, 2016
Grant date	Oct 11, 2016

Abstract

Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions. Each of the plurality of divergent flaps may extend from a respective one of the plurality of convergent flaps. The system may further include a first sync ring rotatably carried by an engine body and configured to synchronously move the divergent flaps between the first and second divergent positions and a second sync ring rotatably carried by the engine body and configured to synchronously move the convergent flaps between the first and second convergent positions. A method may translate rotation of the sync ring to movement of a vehicle surface between radially outward and inward positions.

First claim

What is claimed is:

1. An actuation system for an exhaust nozzle of a gas turbine engine, comprising:
a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions, each of the plurality of divergent flaps extending from a respective one of the plurality of convergent flaps;
a first sync ring rotatably carried by an engine body and configured to synchronously move the plurality of divergent flaps between the first and second divergent positions;
a second sync ring rotatably carried by the engine body and configured to synchronously move the plurality of convergent flaps between the first and second convergent positions; and
a first actuator configured to rotate the first sync ring about an engine axis of the engine body.

2. The actuation system of claim 1 , further comprising a first connecting link operatively connecting the first sync ring to each of the plurality of divergent flaps.

3. The actuation system of claim 2 , further comprising a second connecting link operatively connecting the second sync ring to each of the plurality of convergent flaps.

4. The actuation system of claim 1 , further comprising a second actuator configured to rotate the second sync ring about the engine axis.

5. The actuation system of claim 1 , wherein the first and second sync rings are configured to be concentrically positioned with respect to each other.

6. The actuation system of claim 1 , further comprising:
a first plurality of bell cranks coupled to the first sync ring and a respective one of the plurality of divergent flaps; and
a second plurality of bell cranks coupled to the second sync ring and a respective one of the plurality of convergent flaps.

7. An actuation system for an exhaust nozzle of a gas turbine engine, comprising:
a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions, each of the plurality of divergent flaps extending from a respective one of the plurality of convergent flaps;
a first plurality of bell cranks coupled to a respective one of the plurality of divergent flaps; and
a second plurality of bell cranks coupled to a respective one of the plurality of convergent flaps; and
a first actuator configured to rotate a first sync ring about an engine axis of an engine body.

8. The actuation system of claim 7 , further comprising a first connecting link operatively connecting the first sync ring to each of the plurality of divergent flaps.

9. The actuation system of claim 8 , further comprising a second connecting link operatively connecting a second sync ring to each of the plurality of convergent flaps.

10. The actuation system of claim 7 , further comprising a second actuator configured to rotate a second sync ring about the engine axis.

11. The actuation system of claim 7 , wherein the first sync ring and a second sync ring are configured to be concentrically positioned with respect to each other.

12. The actuation system of claim 7 , further comprising:
the first sync ring rotatably carried by the engine body and coupled to the first plurality of bell cranks for synchronously moving the plurality of divergent flaps between the first and second divergent positions; and
a second sync ring rotatably carried by the engine body and coupled to the second plurality of bell cranks for synchronously moving the plurality of convergent flaps between the first and second convergent positions.

13. A method of operating an actuation system, comprising:
rotating a sync ring about a central axis of the sync ring with an actuator, the sync ring being operatively connected to an input arm of a bell crank, the bell crank being rotatable about a radial axis perpendicular to the central axis, wherein a telescoping input is operatively disposed between the actuator and the input arm of the bell crank;
translating the rotation of the sync ring to a connecting link with an output arm of the bell crank;
urging the connecting link in an axial direction with the output arm of the bell crank; and
moving a vehicle surface to a radially outward or inward position with the connecting link.

14. The method of claim 13 , wherein the vehicle surface includes a flap of a nozzle.

15. The method of claim 14 , further comprising opening a variable area passage by moving the vehicle surface to the radially inward position.

16. The method of claim 14 , further comprising closing a variable area passage by moving the vehicle surface to the radially outward position.

17. The method of claim 13 , further comprising rotating a second sync ring to urge a second connecting link to move a second vehicle surface to a radially outward or inward position.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls-Royce North America Tech Inc

Inventors

• Pesyna Kenneth M

Classifications

• F05D2260/56

  using cams or eccentrics · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title

• F02K1/1238

  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 a substantially axially movable structure · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F02K3/075

  controlling flow ratio between flows · CPC title