General Electric Company

Bell Helicopter Textron Inc.

Elliott Keller Schulte

Ming Xie

Mark Ernest Vermilyea

Bowden Kirkpatrick

Mitchell Harold Boyer

Benjamin Ferrell

Brian Stephens

Robert Arnold Brack

Kathleen Oldham

Brian Dominic Stephens

Benjamin Wayne Ferrell

Johnny Ray Gentry

Robert Brack

A method is provided for forming a composite article to have a primary composite structure and an integral secondary composite structure that extends out of a plane defined by the primary composite structure. The method includes laying-up first plies to construct the primary composite structure. The first plies contain continuous reinforcement material and extend from a first zone that will define the primary composite structure into a second zone that will define the secondary composite structure. During laying-up of the first plies, additional plies are interleaved with the first plies within the second zone but not the first zone. The additional plies originate within a build-up zone between the first and second zones and extend therefrom into the second zone. After interleaving the plies, the build-up zone is deformed to orient the second zone and form the secondary composite structure that extends out of the plane defined by the continuous reinforcement material of the first plies.

Composite article and methods therefor

One aspect of a method of manufacturing a honeycomb core includes positioning a first thermoplastic columnar cell adjacent a second thermoplastic columnar cell, modifying a thermoplastic property of the first thermoplastic columnar cell, wherein the modified thermoplastic property permits joining a circumferential surface of the first thermoplastic columnar cell to a circumferential surface of the second thermoplastic columnar cell. The method also includes joining the circumferential surface of the first thermoplastic columnar cell having the modified thermoplastic property to the circumferential surface of the second thermoplastic columnar cell resulting in the honeycomb core.

Manufacture of thermoplastic core

An apparatus and methods for manufacturing a flanged component from a composite lay-up are provided. The apparatus includes a support structure coupled to the composite lay-up and a mold ring coupled to the support structure. The mold ring includes a ring guide surface and a radial contact surface that is configured to couple to the composite lay-up. The apparatus further includes a mold plate coupled to the mold ring. The mold plate includes a recessed surface and a plate guide surface, where the recessed surface is configured to couple to the composite lay-up and the plate guide surface is configured to couple to the ring guide surface. The apparatus also includes an autoclave that applies pressure to the mold ring and the mold plate to move the plate guide surface along the ring guide surface to apply pressure to the composite lay-up.

Apparatus for manufacturing a flanged component and methods of manufacturing the same

Methods for making a self-conforming non-crimp fabric involving tailoring at least a first parameter to anchor the fabric and at least a second parameter to provide conformability of the fabric, the first and second parameters selected from stitch type, stitch spacing, stitch density, stitch material, stitch weight, stitch tension, and combinations of the same.

Methods for improving conformability of non-crimp fabric and contoured composite components made using such methods

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Hurst, TX, United States of America

Elliott Keller Schulte