Jet Engine With Deflector
OwnerMichael J. Klineinventor
Life of this patent
Estimating the term…
Abstract
An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.
Claims20
An aircraft component comprising a wing, a tail section, an engine nacelle, an air inlet cowl, a windshield, an air inlet deflector, or a fuselage, the aircraft component comprising an outer skin, the outer skin comprising a fore end region and an aft end region relative to an intended direction of an airstream or airborne matter impacted by the outer skin, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction than the second angle of incidence, wherein the fore end region of the outer skin comprises a first thickness relative to the intended direction, and the aft end region of the outer skin comprises a second thickness relative to the intended direction, and the first thickness is greater than the second thickness.
An aircraft component comprising a wing, a tail section, an engine nacelle, an air inlet cowl, a windshield, an air inlet deflector, or a fuselage, the aircraft component comprising an outer skin, the outer skin comprising a fore end region and an aft end region relative to an intended direction of an airstream or airborne matter impacted by the outer skin, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction than the second angle of incidence, wherein the fore end region of the outer skin comprises a first impact strength, and the aft end region of the outer skin comprises a second impact strength, and the first impact strength is greater than the second impact strength.
A method of fabricating an aircraft component comprising molding an outer skin of a wing, a tail section, an engine nacelle, an air inlet cowl, a windshield, an air inlet deflector, or a fuselage, the outer skin comprising a molded, unitary piece, the outer skin further comprising a fore end region and an aft end region relative to an intended direction of an airstream or airborne matter impacted by the outer skin, the fore end region presenting a first angle of incidence, and the aft end region presenting a second angle of incidence, the first angle of incidence being more direct relative to the intended direction than the second angle of incidence, the method comprising molding the fore end region with a first impact strength, and molding the aft end region with a second impact strength, wherein the first impact strength is greater than the second impact strength.
Dependencies are inferred from the claim text.