Granted Patent B2

US 6,983,588 · App. 10/338,499 · Granted Jan 10, 2006

Abstract

Claims (39)

1. A turbofan exhaust nozzle comprising:

a fan nacelle surrounding a core engine cowling to define a fan duct radially therebetween for discharging fan air;

said fan duct including an arcuate outlet disposed radially between said cowling and a trailing edge of said nacelle;

said fan duct further including a movable flap disposed solely in a minor portion thereof, with a remaining major portion of said fan duct having a constant flow area; and

means for selectively moving said flap from a stowed position to a deployed position inside said fan duct to locally decrease flow area inside said fan duct for discharging said fan air through said fan duct outlet.

2. An exhaust nozzle according to claim 1 wherein said flap is disposed adjacent said nacelle trailing edge for selectively decreasing flow area adjacent said fan duct outlet.

3. An exhaust nozzle according to claim 2 wherein said flap moving means are configured to deploy said flap in said fan duct during takeoff operation of a turbofan engine configured to discharge said fan air through said fan duct.

4. An exhaust nozzle according to claim 3 wherein said flap moving means are configured to stow said flap during cruise operation of said turbofan engine at a predetermined altitude.

5. An exhaust nozzle according to claim 3 wherein said flap moving means are configured to deploy said flap for reducing rotor speed of a fan in said turbofan engine without substantially reducing thrust generated by said fan air.

6. An exhaust nozzle according to claim 2 wherein:

said fan duct is configured as a C-duct having arcuate portions of said nacelle and cowling joined together at circumferentially opposite first and second endwalls; and

said flap is pivotally mounted in said first endwall for deployment circumferentially into a corresponding end of said C-duct.

7. An exhaust nozzle according to claim 6 wherein said flap is disposed flush in said first endwall when stowed, and is pivoted outwardly therefrom when deployed.

8. An exhaust nozzle according to claim 6 wherein:

said flap includes a hinge pin at an upstream proximal end thereof for pivoting an opposite downstream distal end of said flap outwardly from said first endwall; and

said flap moving means are configured for pivoting said flap on said hinge pin between said stowed and deployed positions.

9. An exhaust nozzle according to claim 8 wherein:

said hinge pin is fixedly joined to said flap and includes opposite ends pivotally joined to said nacelle and cowling; and

said flap moving means comprise a link arm affixed to one end of said pin, and an actuator operatively joined to said arm for selectively rotating said arm and hinge pin to pivot said flap between said stowed and deployed positions.

10. An exhaust nozzle according to claim 9 wherein said flap comprises a composite material having a metal band affixed thereto at said proximal end, with said band having said hinge pin affixed thereto.

11. An turbofan exhaust nozzle comprising:

a fan nacelle surrounding a core engine cowling with arcuate portions joined together at circumferentially opposite endwalls to define a pair of C-shaped fan ducts for discharging fan air therefrom;

each of said fan ducts including an arcuate outlet disposed radially between said cowling and a trailing edge of said nacelle; and

each of said fan ducts further including a flap pivotally mounted in a respective one of said endwalls for locally varying flow area in a minor portion of said fan ducts, with remaining major portions of said fan ducts having a constant flow area.

12. An exhaust nozzle according to claim 11 further comprising:

a respective hinge pin affixed to each of said flaps and including opposite ends pivotally joined to said nacelle and cowling;

a respective link arm affixed to each of said hinge pins; and

respective actuators operatively joined to each of said link arms for selectively pivoting said flaps from stowed positions adjacent said endwalls to deployed positions inside said fan ducts to locally decrease discharge flow area of said fan air.

13. An exhaust nozzle according to claim 12 wherein said flaps are disposed adjacent said nacelle trailing edge for selectively decreasing flow area adjacent said fan duct outlets.

14. An exhaust nozzle according to claim 13 wherein said flaps are disposed flush in said endwalls when stowed, and are pivoted outwardly therefrom when deployed.

15. An exhaust nozzle according to claim 14 wherein said flap hinge pins are disposed at upstream proximal ends of said flaps for pivoting opposite, downstream distal ends of said flaps outwardly from said endwalls.

16. An exhaust nozzle according to claim 15 further comprising a controller operatively joined to said actuators and configured to deploy said flaps in said fan ducts during takeoff operation of a turbofan engine configured to discharge said fan air through said fan ducts.

17. An exhaust nozzle according to claim 16 wherein said controller is further configured to stow said flaps during cruise operation of said turbofan engine at a predetermined altitude.

18. An exhaust nozzle according to claim 17 wherein said controller is configured to deploy said flaps for reducing speed of a fan in said turbofan engine without substantially reducing thrust generated by said fan air.

19. An exhaust nozzle according to claim 18 wherein each of said flaps comprises a composite material having a metal band affixed thereto at said proximal end, with said band having said hinge pin affixed thereto.

20. A method of reducing noise in a turbofan engine having a turbofan exhaust nozzle according to claim 1 comprising:

discharging fan air through said fan duct;

deploying said flap for temporarily decreasing flow area in said fan duct during takeoff operation of said engine for correspondingly reducing speed of said fan; and

terminating said area decrease at cruise operation of said engine at altitude.

Assignments (13)