Patent application number | Description | Published |
20100254821 | INTERMEDIATE-MANUFACTURED COMPOSITE AIRFOIL AND METHODS FOR MANUFACTURING - An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix. | 10-07-2010 |
20110033302 | FAN BLADE DOVETAIL WITH COMPLIANT LAYER - A fan blade includes an airfoil and a dovetail at a radially inner end of the airfoil. The dovetail extends between first and second axial ends, and has outer circumferential faces. The dovetail is formed of relatively rigid composite material. Compliant material is placed on each outer circumferential face of the dovetail. The compliant material is less rigid than the composite material for forming the dovetail. In a second embodiment, the compliant layer may be positioned within the disk slots in a disk, such that the compliant layer will come in contact with circumferentially outer faces of the dovetail. | 02-10-2011 |
20110038732 | GAS TURBINE ENGINE COMPOSITE BLADE - The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness. | 02-17-2011 |
20110129348 | CORE DRIVEN PLY SHAPE COMPOSITE FAN BLADE AND METHOD OF MAKING - A method of forming a composite airfoil having a suction side and pressure side includes the steps of designing a mold, designing a woven core, designing a plurality of plies and assembling the designed mold, core and plies to create the composite airfoil. The hollow mold has an inner surface which defines the surface profile of the composite airfoil. The plurality of plies is designed to fit between the inner surface of the mold and an outer surface of the woven core. The plurality of plies is designed after the step of designing the woven core. | 06-02-2011 |
20110182740 | FAN AIRFOIL SHEATH - A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil. | 07-28-2011 |
20120134839 | COMPOSITE AIRFOIL AND TURBINE ENGINE - A composite airfoil includes a core that has a three-dimensional network of fibers. The core defines an airfoil section and a root section. A composite skin covers a portion of the core excluding the root section. | 05-31-2012 |
20130064676 | COMPOSITE FILLED METAL AIRFOIL - A method of forming an airfoil includes forming a metal portion of the airfoil including a tip, a leading edge, a trailing edge, a pressure side and a suction side; forming a plurality of grooves into one side of the airfoil; and filling the plurality of grooves with composite material. | 03-14-2013 |
20140086737 | STRUCTURAL GUIDE VANE INTERNAL TOPOLOGY - A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction. | 03-27-2014 |