Variable fan duct nozzle translatable core/inner cowl including two overlapping portions made of different materials
AssigneeSpirit AeroSystems, Inc.
InventorRandall Ray West
Life of this patent
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Abstract
An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.
Claims20
A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising:
- a forward portion having a first front edge and a first aft edge;
- an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the inner cowl and a center axis of the inner cowl occurs at or forward of a location in which the forward portion and the aft portion meet or overlap;
- an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction to decrease an exit area between the inner and outer cowl;
- and
- a first inner cowl half and a second inner cowl half, each comprising:
- a top edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to pivotally attach to opposing sides of a pylon, and
- a bottom edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to mechanically fasten and unfasten with each other.
An aircraft nacelle comprising:
- an outer cowl having a forward end, an aft end, an outer wall, and an inner wall;
- an inner cowl located inward of the outer cowl, forming an air flow path therebetween, wherein the inner cowl comprises:
- a forward portion made of a first type of material and having a first front edge, a first aft edge;
- an aft portion made of a second type of material and having a second front edge and a second aft edge, wherein at least part of the forward portion proximate the first aft edge or at least part of the aft portion proximate the second front edge substantially overlaps one of the forward portion and the aft portion;
- and
- an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction.
A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising:
- a forward portion having a first front edge and a first aft edge;
- an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the inner cowl and a center axis of the inner cowl occurs at or forward of a location in which the forward portion and the aft portion meet or overlap;
- an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction to decrease an exit area between the inner and outer cowl;
- and
- a heat-resistant panel located inward of the forward and aft portions and configured for shielding the forward and aft portions from engine heat.
Dependencies are inferred from the claim text.