General Electric Company

Tod Winton Davis

Nicholas Joseph Kray

Gary Willard Bryant, Jr

Ming Xie

Elzbieta Kryj-Kos

Gerald Alexander Pauley

Mitchell Harold Boyer

Qiang Li

Jorge Orlando Lamboy

David William Crall

Wei Wu

Michael John Franks

Li Zheng

Dong-Jin Shim

Kevin Lee Kirkeng

Max Robert Farson

Benjamin Thomas Van Oflen

Daniel Allen Wilkin, Ii

Daryl John Burford

Theodore R Ingling

Pawel Pres

Stephanie Glynn Cotten

Michael W Peretti

Christopher Lee McAfee

James Francis Brown

Tomas Muchenik

Thomas Brinck

Chad Harbert

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.

Composite airfoil assembly for a turbine engine

An airfoil assembly for a turbine engine having a composite spar, a sleeve, and a set of lobes. The composite spar includes an exterior spar portion, where at least part of the exterior spar portion of the composite spar is received at a sleeve inner surface of the sleeve. The set of lobes extends from the composite spar and is received by a set of recesses at the sleeve inner surface.

Airfoil assembly having a composite spar

An airfoil assembly for a turbine engine. The airfoil assembly has an airfoil, and a spa. The airfoil has a wall bounding an interior and defining an exterior surface. The wall extends between a leading edge and a trailing edge to define a chordwise direction, and between a root and a tip to define a spanwise direction. The spar includes a centerline axis, the spar extends into the interior of the airfoil.

Airfoil assembly having an airfoil and a spar

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.

Composite airfoil assembly and method of forming a composite airfoil assembly

A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.

Composite airfoil assembly having a dovetail portion

An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, a skin, and an insert. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket. The skin having a braided or woven fiber.

Airfoil assembly with a trunnion and spar

An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, and a set of inserts. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket.

A method for making a metallic leading edge guard of the type having a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.

Method for manufacturing leading edge guard

An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.

Turbine engine airfoil assembly

A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.

Platform apparatus for propulsion rotor

An airfoil includes: an airfoil body having convex and concave sides extending between a leading edge and a trailing edge, the airfoil body including primary and secondary regions having differing physical properties; and at least one metallic cladding element attached to the airfoil body.

Airfoil with multi-material reinforcement

A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.

Metal leading edge protective strips for airfoil components and method therefor

A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.

Low radius ratio fan for a gas turbine engine

A method of manufacturing a blade is provided. The method includes providing a plurality of first plies, each of the first plies sized to extend substantially the length of a span of the blade and providing a plurality of second plies, each of the second plies sized to extend only partially the length of the span of the blade. The method also includes layering the plurality of first plies and the plurality of second plies in a mold such that the plurality of second plies is interspersed throughout the plurality of first plies to spread apart the plurality of first plies to facilitate increasing a cross-sectional area of the blade and bonding the plurality of first plies to the plurality of second plies to facilitate forming a structural core of the blade.

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Liberty Township, OH, United States of America

Tod Winton Davis