Fan variable area nozzle for a gas turbine engine fan nacelle with sliding actuation system
AssigneeUnited Technologies Corporation
InventorRobert L. Gukeisen
Life of this patent
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Abstract
A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area.
Claims16
A nacelle assembly for a gas turbine engine comprising:
- a core nacelle defined about an axis;
- a fan nacelle mounted at least partially around said core nacelle, said fan nacelle having a fan variable area nozzle defined about said core nacelle;
- a drive ring mounted within said fan nacelle;
- a flap linkage mounted to each of a multiple of flaps and said drive ring;
- and,
- an actuator system which drives said drive ring along said axis to vary a fan nozzle exit area defined by said fan variable area nozzle.
A gas turbine engine comprising:
- a core engine defined about an axis;
- a gear system driven by said core engine;
- a fan driven by said gear system about said axis;
- a core nacelle defined at least partially about said core engine;
- and
- a fan nacelle mounted around said fan and at least partially around said core nacelle, said fan nacelle 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 nacelle and said core nacelle;
- a drive ring mounted within said fan nacelle;
- a flap linkage mounted to each of said multiple of flaps and said drive ring;
- and,
- an actuator system which drives said drive ring along said axis to vary a fan nozzle exit area defined by said fan variable area nozzle.
A method of varying a fan nozzle exit area of a gas turbine engine comprising the steps of:
- (A) locating a fan variable area nozzle which defines a fan nozzle exit area between a fan nacelle and a core nacelle;
- (B) axially moving a drive ring disposed within said fan nacelle;
- and
- (C) pitching a flap assembly of the fan variable area nozzle between a first position and a second position to vary at least a sector of the fan nozzle exit area in response to said step (B).
Dependencies are inferred from the claim text.