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US 2010/0058769 A1Published application
Fan variable area nozzle for a gas turbine engine fan nacelle with drive ring actuation system
AssigneeUnited Technologies Corporation
InventorKenneth C. Baran
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. 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.
Claims20
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.
3 more elements
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.
6 more elements
Dependencies are inferred from the claim text.