General Electric Company

Charles Richard Evans

Douglas Duane Ward

Weiping Wang

Joseph T Begovich, Jr

Michael Evans Graham

Wendy Wen-Ling Lin

Michael Kent Cueman

Herbert S Chao

Emily Yixie Shu

Jackie D Jones

Meng-Ling Hsiao

Thomas Huei Hwang

Robert Paul Tyler

Richard Alan Ridilla

Wendy Wenling Lin

Mark Alan Rosenzweig

Jack W Baldwin

William Elliot Bachrach

Jeffrey Lynn Schworm

John Michael Muldoon

Scott A Welsh

Albert Benjamen Crogan

Barrett J Fuhrman

Richard A Ridilla

Kathryn Ann Evans

James M Campbell

The present invention provides a process for the lay-up of a composite laminate article, the article produced by this process, and the apparatus used to produce the composite laminate article. The composite laminate article may be, for example, an airfoil, particularly useful as a fan blade in a large high bypass ratio turbofan engine, wherein the blade is generally regarded as large and having a high degree of twist. In a preferred embodiment, the present invention provides a process for laying up a composite laminate article comprising a) reading a data set to enable the projection of an image of a ply section onto a work surface, the image indicating a ply section target point; b) laying up a ply section of composite laminating material within the image, wherein the ply section first contacts the work surface at the target point; and c) repeating steps (a)-(b) until the composite laminate article is complete. In a second preferred embodiment, the present invention provides for a lamination apparatus for use in making a composite laminate article comprising a work surface for receiving, in a predetermined sequence, a plurality of ply sections of composite laminating material; a laser projection system using predetermined projection points for outlining an image of a ply section onto the work surface, the image further indicating a ply section target point for making first contact of the ply section with the work surface; and a data set for providing the predetermined projection points to the laser projection system.

Laser projection system to facilitate layup of complex composite shapes

A jet aircraft fan case containment design that uses polyurethane to absorb fan blade fragments and uses polyurethane to prevent fan blade fragments from penetrating the fan case. The polyurethane is used in place of or to supplement KEVLAR&reg; and/or fiberglass wraps used to contain fan blade fragments. The polyurethane is also used in place of aluminum alloy and stiffening ribs in the fan case.

Jet aircraft fan case containment design

A grit blasting and alkaline etch surface pretreatment that is applied to a metallic airfoil. The metallic airfoil includes pockets or cavities that have been fabricated into the airfoil to reduce the weight of the airfoil. The pretreatment includes grit blasting the surface of the pockets or cavities, followed by washing the airfoil and treating the airfoil in an alkaline etch bath. After any remaining solution from the bath is neutralized and within twenty-four hours of the end of the pretreatment, primer is applied to the surface of the pockets or cavities. After the primer is applied to the surface of the pockets, a lightweight resin is injected into the pockets and bonds to the primer forming a mechanical bond with good fracture toughness at elevated temperatures.

Method of chemical pretreatment of a lightweight jet engine fan blade

A thin film that forms an interface between metal surfaces and polymeric inserts of aircraft engine fan blades. The thin film is formed from a chemical comprised of carbon black, at least one evaporable solvent, a combination of phenolic-like resins dissolved in the solvent and the balance filler and inert ingredients. The thin film, upon drying of the evaporable solvent, forms a phenolic that bonds with the metallic portion of the fan blade. After the polymeric material is applied to recesses in the fan blade and cured, a chemical bond is formed between the thin film and the elastomeric inserts. The bonded structure has improved FWT peak stresses and improved fracture toughness.

Adhesion enhancers to promote bonds of improved strength between elastomers metals in lightweight aircraft fan blades

A flexible tool that fits over the pressure or concave side of a metallic airfoil that includes a lightweight material component for a gas turbine engine during the fabrication of the airfoil. The metallic fan airfoil includes pockets or cavities that have been machined into the airfoil in order to reduce the weight of the airfoil. The tool is a flexible body manufactured from sheets of composite material and includes an integral elastomeric seal. The tool is placed over the airfoil and forms a seal against the pressure side of the airfoil so that lightweight resin can be injected into the pockets and retained in position during curing. The flexible tool is formed by laying up thin sheets of composite material that includes fiber over a metallic master tool after partially cured elastomeric material is placed inside a marking corresponding to the airfoil perimeter. The metallic master tool also includes slot positions corresponding to preselected positions, that form integral projections which allow the flexible tool to be correctly assembled and sealed against the airfoil.

Composite caul sheet with integral seal used in the fabrication of lightweight airfoils and method of making

A caul is used in an autoclave process for consolidating a composite, multi-ply, gas turbine fan blade preform having first and second opposite sides and a varying thickness therebetween. The caul includes a body having fibers situated in a matrix. The caul is complementary in shape to the preform first side and has a bending flexibility varying over the body for correspondingly varying consolidation of the preform. The second side of the preform is shaped by a bottom mold in the autoclave chamber.

Selectively flexible caul and method of use

Elastomeric formulation used in the construction of lightweight aircraft engine fan blades

A hybrid gas turbine engine airfoil is made by forming a metal airfoil with a pocket in one side thereof. The pocket is covered by a caul. An elastomeric fluid is injected into the pocket and cured therein for bonding thereto. The caul is removed from the airfoil to expose the cured elastomer conforming to the aerodynamic profile thereof.

Method of making injection formed hybrid airfoil

A method for detecting misalignment of initially-aligned fiber filaments in a composite. An optical fiber is placed among the fiber filaments in the composite, light is directed into the optical fiber, the intensity of the light in the optical fiber is measured during subsequent composite processing, and attenuation in such light intensity is ascertained which indicates such misalignment (e.g., wrinkling, bending, buckling, porosity, delamination and the like) is being detected during such processing. In another preferred method, before-processing and after-processing x-ray images are taken of an x-ray-attenuating fiber which has been placed among x-ray-transparent fiber filaments in a composite.

Method for detecting fiber misalignment in composite manufacturing

Detecting and minimizing fiber misalignment in a composite during

A method for compression molding a resin-impregnated preform to fabricate an impact-resistance, fiber-reinforced composite fan blade for use in a high bypass turbofan engine. The method is compatible with the use of high viscosity resin systems that contribute greater impact resistance to the fan blade, but whose flow through the fan blade during molding would cause unacceptable movement of the reinforcing fibers. The method entails restricting the flow of the resin system within the preform through selective placement of a resin-impervious material on certain surfaces of the preform, so as to prevent resin loss and fiber movement during the compression molding operation.

Method for compression molding a fan blade

The present invention provides a composite airfoil particularly useful as a fan blade, having a high degree of twist, in a large high bypass ratio turbofan engine. The composite airfoil of the present invention has a progression of filament reinforced airfoil laminations of varying span, arranged in order by span, and interrupted by at least one filament reinforced airfoil lamination having a span out of height order to form what is called a confused or broken shear plane where radially outer tips of the laminations end.

Growing community of inventors

Cincinnati, OH, United States of America

Charles Richard Evans