General Electric Company

Kimberly-clark Worldwide, Inc.

Other

Ming Xie

Donald George LaChapelle

Mitchell Harold Boyer

Stephen Craig Mitchell

Tod Winton Davis

Michael Braley

Nicholas Joseph Kray

Mark Ernest Vermilyea

Curt Brian Curtis

Elliott Keller Schulte

Donald George Lachapelle

Herb F Velazquez

Philip D Palermo

Russell J Kroll

Donald Michael Corsmeier

Debra Nell Welchel

Mark Eugene Noe

Suzuko Hisata

Warren Rosal Ronk

Douglas Duane Ward

Viswanadha Gupta Sakala

Bowden Kirkpatrick

Mingchao Wang

Gerald Alexander Pauley

Lee Alan Blanton

Michael Todd Radwanski

Jessica Licardi Subit

Matrice Brown Jackson

Douglas Lorrimer Armstrong

Megan Christine Hansen Smith

Jorge Orlando Lamboy

Benjamin Ferrell

Oliver Roghe

Brian Stephens

Herb Flores Velazquez

Megan Christine Smith

Arthur William Sibbach

Qiang Li

David William Crall

Ian Francis Prentice

Wendy Wen-Ling Lin

Scott Roger Finn

Joseph D Mitchell

Frank Worthoff

James William Clark

Mark Londborg

Xiaomei Fang

Leslie L Langenbrunner

Ralph Solarski

Gary D Roberts

Richard Thomas Price

Daniel Allen Wilkin, Ii

James Joseph Detamore

Matthew G Gann

Yosang Yoon

Dingzhong Xie

Hui Zeng

Brian Dominic Stephens

Andrew Joseph Beltz

Yong Feng

Benjamin Wayne Ferrell

Rosa Lee Nemec

Scott Francis Neis

Teresa Tiashu Chen-Keat

Mark D Londborg

Isak Varol

Andrew McGee

Som R Soni

Charles J Cross

Gary E Terborg

Dale Hopkins

Lourdes Lizzette Sheffield

Paul Edward Wilkerson

Lori Renee McGrath

Johnny Ray Gentry

Adam Max Aresty

Steven Todd Slusher

Megan Christine-Hansen Smith

Ralph Andrew Solarski

Lori Renee Mcgrath

A casing for a turbine engine including a composite section. The composite section has (i) an arcuate shape or an annular shape and (ii) a circumferential direction. The composite section includes a matrix and a plurality of circumferential reinforcing fiber tows embedded in the matrix. Each circumferential reinforcing fiber tow of the plurality of circumferential reinforcing fiber tows extends in the circumferential direction and has a plurality of undulations in the circumferential direction to allow the matrix material of the composite section to expand circumferentially.

Composite casing for a turbine engine

An engine component for a turbine engine. The engine component has a composite structure and a cover structure. The composite structure has a composite structure outer wall and a composite structure edge. The cover structure encases at least a portion of the composite structure outer wall. The cover structure has a main body. The main body extends along the at least a portion of the composite structure outer wall.

Engine component

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

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.

Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.

Composite hollow blade and a method of forming the composite hollow blade

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 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

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

A composite panel structure and a method of fabricating the composite panel structure are provided. A fan assembly includes a plurality of blades circumferentially spaced about a fan disk. Each blade of the plurality of blades extends radially outwardly from the disk to a blade tip. A fan case assembly circumscribes the plurality of blades. The fan case assembly includes a radially outer casing including a radially inner side, an inner structure including an inner surface and a honeycomb layer extending along the radially inner side, and a composite panel structure including an inner surface and extending circumferentially along the inner structure inner surface. The composite panel structure includes short fiber tows extending only partially along at least one of a circumferential path, an axial path, and a diagonal path in the composite panel structure.

Method and system for fiber reinforced composite panels

Composite airfoil singlet, includes airfoil extending from base to tip of airfoil, integrally formed with no more than one outer platform at tip and/or no more than one inner platform at base. Parallel composite plies or woven fibers extend through airfoil and through outer and/or inner platforms. Outer and/or inner curved sections extend between outer and/or inner platforms and airfoil respectively. Assembly includes circular row of the composite airfoil singlets depending radially inwardly from and mounted to an outer shroud or casing. Outer and/or inner fasteners may secure outer and inner platforms to outer shroud or casing and an inner shroud respectively and include shanks extending substantially perpendicularly from outer and inner fastening plates though platform holes in outer and inner platforms and through outer and inner holes in outer shroud or casing and inner shroud respectively. Nuts are screwed on threaded ends of shanks.

Airfoil singlets

A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.

Gas turbine engine combustor with CMC heat shield and methods therefor

Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.

Non-integral fan blade platform

Growing community of inventors

Beavercreek, OH, United States of America

Ming Xie