Fan variable area nozzle for a gas turbine engine fan nacelle with drive ring actuation system
A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. The flap assembly generally includes a multiple of flaps, flap linkages and an actuator system. The actuator system radially and axially translates a drive ring relative an engine centerline axis. A slot within the drive ring receives the flap linkages to asymmetrically and symmetrically vary the fan nozzle exit area in response to movement of the drive ring.
1. A gas turbine engine comprising:
a core structure defined about an axis;
a fan structure circumscribing said core structure, said fan structure having a fan variable area nozzle with at least one flap which at least partially defines a fan nozzle exit area between said fan structure and said core structure;
a drive ring segment having a slot;
a flap linkage pivotally mounted to said fan structure, said flap linkage mounted to said at least one flap and engaged within said slot at an interface; and
an actuator system capable of translating said drive ring in at least one of an axial direction and a radial direction relative to said axis to respectively symmetrically vary and asymmetrically vary said fan nozzle exit area.
2. The engine as recited in claim 1 , wherein said at least one flap includes a multiple of flaps defined about the fan nozzle exit area.
3. The engine as recited in claim 2 , wherein said multiple of flaps define a trailing edge of said fan variable area nozzle.
4. The engine as recited in claim 1 , wherein said actuator system includes a multiple of actuators, each of said multiple of actuators pivotally mounted to said fan structure and said drive ring.
5. The engine as recited in claim 1 , wherein said slot is a circumferentially continuous slot, each of said flap linkages mounted at least partially within said circumferentially continuous slot.
6. The engine as recited in claim 5 , wherein said circumferentially continuous slot includes a curved component.
7. The engine as recited in claim 5 , wherein said circumferentially continuous slot includes a linear component.
8. The engine as recited in claim 5 , wherein said circumferentially continuous slot extends through an inner diameter of said drive ring.
9. The engine as recited in claim 5 , wherein said circumferentially continuous slot includes a slot ceiling and a slot floor.
10. The engine as recited in claim 9 , wherein said slot ceiling and said slot floor each define a constant radius at any given axial location with varying circumferential location.
11. The engine as recited in claim 9 , wherein said slot ceiling includes a non-constant radius at any given axial location with varying circumferential location.
12. The engine as recited in claim 9 , wherein said slot floor includes a non-constant radius at any given axial location with varying circumferential location.
13. The engine as recited in claim 1 , wherein said slot has a circumferential clearance relative said interface of said flap linkage.
14. The engine as recited in claim 13 , wherein said slot defines a slot ceiling and a slot floor engaged with said interface.
15. The engine as recited in claim 1 , wherein said drive ring segment includes a circumferentially continuous slot, a multiple of said flap linkages each engaged within said slot at an interface between a slot ceiling and a slot floor.
16. The engine as recited in claim 1 , wherein said interface includes a ball link.
17. A gas turbine engine comprising:
a core engine defined about an axis;
a fan driven by said core engine about said axis;
a core structure defined at least partially about said core engine; and
a fan structure mounted around said fan and at least partially around said core structure, said fan structure having a fan variable area nozzle with a multiple of flaps which defines a fan nozzle exit area downstream of said fan between said fan structure and said core structure;
a drive ring mounted within said fan structure, said drive ring including a slot which extends through an inner diameter of said drive ring;
a multiple of flap linkages extending from the multiple of flaps, each of said multiple of flap linkages pivotally mounted to said fan structure and engaged within said slot at an interface; and
an actuator system which axially translates and radially translates said drive ring relative to said axis to respectively symmetrically vary and asymmetrically vary said fan nozzle exit area.
18. The engine as recited in claim 17 , wherein said interface defines a point contact at a slot ceiling and a slot floor.
19. The engine as recited in claim 17 , wherein said interface defines a line contact at a slot ceiling and a slot floor.
20. The engine as recited in claim 17 , wherein said interface defines a sliding interface at a slot ceiling and a slot floor, said slot defining a circumferential clearance adjacent said interface.