Variable area nozzle and associated propulsion system and method

Patent metadata

Field	Value
Publication number	US-9957917-B2
Application number	US-201414455063-A
Country	US
Kind code	B2
Filing date	Aug 8, 2014
Priority date	Aug 8, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.

First claim

What is claimed is:

1. A nozzle comprising:
a frame comprising a plurality of deflecting elements arranged in an array, said array extending about a longitudinal axis, wherein at least a first of said plurality of deflecting elements is fixedly connected at a first node to an adjacent second of said plurality of deflecting elements and is fixedly connected at a second node to an adjacent third of said plurality of deflecting elements;
a skin positioned over said frame; and
actuation assembly operatively connected to said frame to supply a deflection force to said frame.

2. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements is fixedly connected at a node to adjacent deflecting elements of said plurality of deflecting elements.

3. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements produces a lateral displacement in response to a deflection force applied in a direction substantially parallel to said longitudinal axis.

4. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements comprises a rectilinear frame structure.

5. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements comprises a square frame structure.

6. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements comprises a curvilinear frame structure.

7. The nozzle of claim 1 wherein each deflecting element of said plurality of deflecting elements comprises a continuous frame structure.

8. The nozzle of claim 1 wherein at least one deflecting element of said plurality of deflecting elements comprises a hinge.

9. The nozzle of claim 1 wherein at least one deflecting element of said plurality of deflecting elements comprises a biasing element.

10. The nozzle of claim 1 wherein said skin comprises a stretchable material.

11. The nozzle of claim 1 wherein said skin comprises a plurality of plates, strips or tiles.

12. The nozzle of claim 1 wherein said actuation assembly supplies said deflection force in a direction substantially parallel with said longitudinal axis.

13. The nozzle of claim 1 wherein said actuation assembly comprises a displaceable ring and a plurality of connectors, wherein each connector of said plurality of connectors extends from said displaceable ring to an associated deflecting element of plurality of deflecting elements.

14. The nozzle of claim 13 wherein said actuation assembly further comprises a stationary ring, wherein said displaceable ring is displaceable relative to said stationary ring.

15. A propulsion system comprising:
a propulsion unit having an inlet end opposed from an outlet end along a longitudinal axis; and
a nozzle connected to said propulsion unit, wherein said nozzle defines a throat having a cross-sectional area, said nozzle comprising:
a frame comprising a plurality of deflecting elements arranged in a tubular array, wherein at least a first of said plurality of deflecting elements is fixedly connected at a first node to an adjacent second of said plurality of deflecting elements and is fixedly connected at a second node to an adjacent third of said plurality of deflecting elements;
a skin positioned over said frame; and
an actuation assembly operatively connected to said frame.

16. The propulsion system of claim 15 wherein said cross-sectional area changes in response to deflection force applied to said frame in a direction substantially parallel with said longitudinal axis.

17. The propulsion system of claim 15 wherein said nozzle is connected to said outlet end of said propulsion unit.

18. A nozzle method comprising:
providing a nozzle having a frame comprising a plurality of deflecting elements arranged in an array, said array extending about a longitudinal axis, wherein at least a first of said plurality of deflecting elements is fixedly connected at a first node to an adjacent second of said plurality of deflecting elements and is fixedly connected at a second node to an adjacent third of said plurality of deflecting elements; and
applying a deflection force to said frame, wherein said deflection force is applied in a direction substantially parallel with said longitudinal axis.

19. The nozzle of claim 1 wherein said nozzle defines a throat having a cross-sectional area, and wherein said actuation assembly effects an expansion of the frame to increase the cross-sectional area of the throat and effects a contraction of the frame to decrease the cross-sectional area of the throat.

20. The propulsion system of claim 1 wherein said actuation assembly effects an expansion of the frame to increase the cross-sectional area of the throat and effects a contraction of the frame to decrease the cross-sectional area of the throat.

Assignees

• Boeing Co

Inventors

• Cawthorne Matthew H
• Filter Evan J

Classifications

• F02K1/10 Primary

  by distorting the jet pipe or nozzle · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2250/90

  Variable geometry · CPC title

• F05D2260/52

  involving springs · CPC title

• F01D17/16

  by means of nozzle vanes · CPC title