Exhaust nozzle control for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9964069-B2
Application number	US-201514753637-A
Country	US
Kind code	B2
Filing date	Jun 29, 2015
Priority date	Jun 29, 2015
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. An exhaust nozzle for a gas turbine engine, comprising:
a duct having a first surface and a second opposing surface extending along a duct axis to define an exhaust flow path; and
wherein the duct defines a recess extending from the first surface;
at least one effector positioned across the first surface,
the at least one effector includes a body extending along an effector axis between a first effector-sidewall and an opposing second effector-sidewall and extending between an effector leading edge and an effector trailing edge with respect to the duct axis,
the at least one effector pivotable about the effector axis to vary a throat area of the exhaust flow path,
the effector leading edge and the effector trailing edge of the at least one effector tapering along the effector axis; and
wherein at least one of the effector leading edge and the effector trailing edge is pivotable away from the recess and into the exhaust flow path.

2. The exhaust nozzle as recited in claim 1 , wherein the at least one effector includes a first effector and a second effector pivotable about a common axis extending between the first effector and the second effector.

3. The exhaust nozzle as recited in claim 1 , wherein the first surface is stationary relative to the duct axis.

4. The exhaust nozzle as recited in claim 3 , wherein the second surface is movable relative to the duct axis.

5. The exhaust nozzle as recited in claim 1 , wherein:
each of the effector leading edge and effector trailing edge slopes inwardly from the first effector-sidewall to the second effector-sidewall with respect to the effector axis;
the effector leading edge is received in the recess and the effector trailing edge extends towards the second surface when the at least one effector is positioned in a first position; and
the effector trailing edge is received in the recess and the effector leading edge extends towards the second surface when the at least one effector is positioned in a second position.

6. The exhaust nozzle as recited in claim 5 , wherein the throat area is defined at a first axial location relative to the duct axis when the at least one effector is located in the first position, and the throat area is defined at a second, different axial location relative to the duct axis when the at least one effector is located in the second position.

7. The exhaust nozzle as recited in claim 6 , wherein the effector leading edge and the effector trailing edge are substantially flush with the first surface when the at least one effector is located in a third position.

8. The exhaust nozzle as recited in claim 5 , wherein the effector leading edge and the effector trailing edge are substantially flush with the first surface when the at least one effector is located in a third position.

9. The exhaust nozzle as recited in claim 8 , wherein surfaces of the body extending between the effector leading edge and the effector trailing edge are substantially planar, the surfaces of the body bounding the exhaust flow path.

10. The exhaust nozzle as recited in claim 8 , wherein the throat area is defined by the effector trailing edge at the first axial location, and the throat area is defined by the effector leading edge at the second axial location.

11. The exhaust nozzle as recited in claim 10 , wherein the body includes a first face and a second face joined at a ridge to bound the exhaust flow path, the ridge extending radially outward with respect to the effector axis and into the exhaust flow path, with the first face sloping from the ridge toward the effector leading edge and the second face sloping from the ridge toward the effector trailing edge, and each of the effector leading edge and effector trailing edge and said ridge progressively tapers from the first effector-sidewall toward the second effector-sidewall with respect to the effector axis.

12. The exhaust nozzle as recited in claim 1 , wherein the body defines a ridge extending radially from the effector axis and sloping towards the duct axis.

13. The exhaust nozzle as recited in claim 12 , wherein the ridge is configured such that a distance between the ridge and the second surface differs in response to pivoting the at least one effector about the effector axis.

14. The exhaust nozzle as recited in claim 1 , wherein the effector axis is spaced apart from the first surface.

15. A gas turbine engine, comprising:
a fan section coupled to a core engine; and
a nacelle assembly mounted at least partially about the core engine, the nacelle assembly including an exhaust nozzle coupled to the nacelle assembly, the exhaust nozzle comprising:
a duct having a first surface and a second opposing surface extending along a duct axis to define an exhaust flow path;
at least one effector having a body positioned in a recess across the first surface,
the body extending along an effector axis between a first effector-sidewall and an opposing second effector-sidewall and extending between an effector leading edge and an effector trailing edge,
the effector leading edge and the effector trailing edge pivotable about the effector axis to vary a throat area of the exhaust flow path,
the effector leading edge and the effector trailing edge of the at least one effector tapering along the effector axis; and

wherein at least one of the effector leading edge and the effector trailing edge is pivotable away from the recess and into the exhaust flow path.

16. The gas turbine engine as recited in claim 15 , wherein the core engine defines a core flow path, the fan section defines a bypass flow path, and the at least one effector is in fluid communication with at least one of the core flow path and the bypass flow path.

17. The gas turbine engine as recited in claim 15 , wherein the effector axis extends longitudinally through the at least one effector.

18. The gas turbine engine as recited in claim 17 , wherein the at least one effector includes a first effector and a second effector pivotable about a common axis, and the first effector and the second effector both taper in a direction towards the duct axis.

19. A method of exhaust control for a gas turbine engine, comprising:
positioning a first effector in a first recess extending across an exhaust duct to define a first thrust vector angle with respect to exhaust flow exiting the exhaust duct,
the first effector comprising a first edge that is an effector leading edge and a second edge that is an effector trailing edge;
the effector leading edge and the effector trailing edge of the first effector tapering along an effector axis; and
rotating the first effector in a first direction about the effector axis to cause the effector leading edge to be located in the first recess, the effector trailing edge to extend into the exhaust duct, and the first thrust vector angle to increase such that the exhaust flow is vectored in a third direction.

20. The method as recited in claim 19 , wherein:
the first edge and the second edge extend between opposed effector-sidewalls of the first effector.

21. The method as recited in claim 19 , comprising:
positioning a second effector in a second recess extending across the exhaust duct to define a second thrust vector angle with respect to exhaust flow exiting the exhaust duct; and
rotating the first effector in a second direction about the effector axis, simultaneously with rotating the second effector, to cause the effector trailing edge to be located in the first recess, the

Assignees

• United Technologies Corp

Inventors

• Roberge Gary D

Classifications

• F02K1/763

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

• F02K1/002

  with means to modify the direction of thrust vector (F02K1/54 takes precedence; thrust vectoring of rockets F02K9/80) · CPC title

• F02K1/58

  Reversers mounted on the inner cone or the nozzle housing {or the fuselage} · CPC title

• F02K1/15

  Control or regulation · CPC title

• F02K3/02

  in which part of the working fluid by-passes the turbine and combustion chamber · CPC title