General Electric Company

Gregory Carl Gemeinhardt

Nicholas Joseph Kray

Douglas Duane Ward

Arthur William Sibbach

David William Crall

Scott Roger Finn

Suresh Subramanian

Peggy Lynn Baehmann

Joshua L Miller

Michael John Franks

Manuel Acosta

James Andrew Hahn

Phani Nandula

Lara Liou

Prakash Kashiram Jadhav

Dong Jin Shim

Jan Christopher Schilling

Wendy Wen-Ling Lin

Todd Alan Anderson

Warren Rosal Ronk

Shatil Sinha

Dong-Jin Shim

Michael Harvey Schneider

Andreas Mastorakis

Phillip W Rambo

Ross Ashely Spoonire

Douglas Edward Klei

A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.

Turbine engine with a blade having woven core and toughened region

A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.

Monolithic composite blade and platform

A bonded part includes: a substrate including a polymer matrix material; a metal layer; a layer of adhesive between the substrate and the metal layer; and a layer of smut between the layer of adhesive and the metal layer.

Metal surface preparation

An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.

Multi-material leading edge protector

A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.

Turbine engine blade with leading edge strip

A part that includes a metal layer positioned on it. The part includes a composite core. A metal layer is positioned on the composite core such that the layer of adhesive is sandwiched between the composite core and the metal layer. A layer of smut that is positioned between the layer of adhesive and the metal layer.

An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.

Frangible gas turbine engine airfoil

Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.

Composite compressor blade and method of assembling

An airfoil structure is presented. The airfoil structure includes an outer casing substantially surrounding a composite core. The composite core includes a plurality of fiber bands, each of the plurality of fiber bands is placed at a predetermined position and orientation at a time, wherein the plurality of fiber bands are interwoven in an in-plane and out-of-plane orientation by interleaving each of the plurality of fiber bands placed in a plane with one or more of the plurality of fiber bands of an adjacent plane to define an interleaved structure. A method for manufacturing an airfoil structure including the composite core is also presented.

Composite airfoil structures

A method of manufacturing a rotor blade is provided. The method includes forming a preform from a plurality of composite plies, the preform including an airfoil portion and a dovetail portion, removing a cutout portion from the dovetail portion of the preform to define a cutout in the preform, wherein the removing the cutout portion facilitates reducing residual stresses in the preform, and inserting an insert into the cutout formed by the removal of the cutout portion.

Blade and method for manufacturing blade

A housing that includes a polymer, a reinforcing material, and a thermally conductive filler. A first housing component is defined by the polymer such that the reinforcing material and a thermally conductive filler are embedded within the polymer. The thermally conductive filler is configured such that heat can be passively conducted through the first housing component. The housing can be configured to be an aircraft gearbox housing.

Composite gearbox housing

A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.

Attachment of composite article

A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.

Hybrid turbine blade including multiple insert sections

A composite article including a composite component, a metallic component and one or more interlock components. The composite component including a plurality of composite plies and extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges, the composite. The metallic component including a first surface and a second surface and a plurality of openings formed therein extending from the first surface to the second surface. The metallic component including at least a portion substantially or fully embedded in the composite component. The one or more interlock components is interwoven through one or more of the plurality of openings in the metallic component and extending into and at least partially embedded in the composite component to provide an interlocking system between the composite component and the metallic component. A method of fabrication of a composite article is also provided.

Growing community of inventors

Park Hills, KY, United States of America

Gregory Carl Gemeinhardt