General Electric Company

Mitchell Harold Boyer

Ming Xie

Mark Ernest Vermilyea

Tod Winton Davis

Mingchao Wang

Bowden Kirkpatrick

Douglas Lorrimer Armstrong

Elliott Keller Schulte

Benjamin Ferrell

Douglas Duane Ward

Viswanadha Gupta Sakala

Kevin Daniel Gordin

Stephanie Glynn Cotten

Benjamin Wayne Ferrell

James Kenton Pullins

Christopher Timothy Roll

Kristin Lynn Bolte Baxter

Joseph Saeler

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 method of manufacturing a composite component including an outer shell, an inner hub, and a plurality of struts connecting the outer shell and the inner hub. The method includes installing an outer shell hoop preform on a mold tooling structure, installing an inner hub hoop preform on the mold tooling structure, and inserting strut preforms through outer shell strut slots, and through inner hub strut slots. A first end of the strut preform has bifurcated end portions that are overlayed onto the outer shell hoop preform, and a second end of the strut preform has bifurcated end portions that are overlayed onto one of the outer shell hoop preform or the inner hub hoop preform. A matrix material is injected into the mold tooling structure and a curing process is applied to the mold tooling structure to obtain a molded composite component.

Composite structure for a turbine engine

A preform for making a casing structure for turbine engines. The preform includes a plurality of reinforcing fiber tows arranged in a two-dimensional weave structure, a three-dimensional weave structure, or a braided structure. The plurality of reinforcing fiber tows include integrally woven or braided fiber tows having a diameter or a density greater than a respective diameter or density of other woven or braided fiber tows in the two-dimensional weave structure, the three-dimensional weave structure, or the braided structure. The integrally woven or braided fiber tows are located in an area of the preform that is bent to form an angled corner to thereby provide strength to a casing structure comprising the angled corner.

Preform for making a casing structure for turbine engines

A composite component for a gas turbine engine includes a body including a composite material. Furthermore, the composite component includes a connection feature integrally woven to the body. Additionally, the connection portion includes a composite material. Moreover, the composite material of the body and the composite material of the connection feature include alternating layers of fiber tows integrally woven together.

Composite component for a gas turbine engine

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.

Airfoil assembly with a trunnion and spar

A containment assembly for use in a turbine engine includes a fan case formed from a composite material. The fan case includes a forward end, an aft end, and an opening defined through the fan case between the forward and aft ends. The containment assembly further includes a structural attachment member formed from a metallic material and coupled to the fan case. The structural attachment member is positioned within the opening in the fan case and is configured to receive at least one fastener to couple a component to the structural attachment member.

Turbine engine containment assembly and method for manufacturing the same

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

Composite fan blade platform includes forward and aft portions and transition portion therebetween. Platform mounting holes extend through increased section thickness in transition portion and conical countersinks centered about centerlines of mounting holes extend into transition portion. Bolts include bolt shanks extending away from boltheads through center bolt holes in conical load spreaders in conical countersink. Boltheads engage conical load spreader. Bolthead is disposed entirely within cylindrical counterbore into top of load spreader and engages shoulder at bottom of cylindrical counterbore. Radial gap between bolthead and cylindrical counterbore surface of cylindrical counterbore may be filled by filler or filler ring. Bolts may join platform supports to disk hooks attached, fixed or joined to, or integral with disk posts of disk. Nuts threaded on threaded inner end of bolt shank may secure bases attached to platform supports to fan blade platform.

Conical load spreader for composite bolted joint

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.

Growing community of inventors

Cincinnati, OH, United States of America

Mitchell Harold Boyer