General Electric Company

Other

Michael John Franks

Nicholas Joseph Kray

Jason David Shapiro

Arthur William Sibbach

Elzbieta Kryj-Kos

Roger Lee Doughty

Joshua L Miller

Gary Willard Bryant, Jr

Gregory Carl Gemeinhardt

Samuel Ross Rulli

Manuel Acosta

Benjamin Thomas Van Oflen

James Andrew Hahn

Lara Liou

Jan Christopher Schilling

David William Crall

David Scott Stapleton

Tod Winton Davis

Joshua Brian Jamison

Kevin Lee Kirkeng

Randall Maurice Prather

John Joseph Wunsch

Christopher Lee McAfee

Michael Stephens Bodey

Danielle Marie Greenfield

Norman A Franks

A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.

Turbine engine airfoil with a woven core

A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.

Turbine engine including a composite airfoil assembly having a dovetail portion

A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

Turbine engine with a composite-airfoil assembly having a dovetail portion

Difficulties associated with transferring fluids are overcome by providing jugs for such containers that are stackable and attachable to wheel assemblies and a pole that can serve as a handle for pulling or pushing the containers.

Stackable fluid containers with attachable wheel assembly

A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.

Composite airfoil assembly having a dovetail portion

A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.

Shroud hanger assembly

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

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.

A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.

Multi-piece shroud hanger assembly

A shroud and shroud hanger are provided wherein at least the shroud is formed of ceramic matrix composite material. The shroud and hanger extend in a circumferential direction. A generally C-shaped clip extends radially to retain the hanger and shroud together.

CMC shroud support system

A composite duct panel assembly is provided. The composite duct panel assembly includes a composite duct panel having a curved cross-section in a circumferential direction and a width based on the panel including a portion of a circumference of an annular bypass duct. In one embodiment, at least two adjacent corners of the panel are greater than 90&#xb0;. In one embodiment, the panel includes a circumferential flange along a circumferential edge and an axial flange along an axial edge, and the assembly further includes a corner bracket coupled to the panel, the circumferential flange, and the axial flange. The corner bracket includes a flange corner having an approximate 90&#xb0; angle, the flange corner extending the axial flange and the circumferential flange to an intersection at a corner of the panel.

Method and system for improving structural characteristics of composite component corners

A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.

Mounting apparatus for low-ductility turbine shroud

A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.

Low-ductility turbine shroud

A method of manufacturing a blade is provided. The method includes providing a plurality of first plies, each of the first plies sized to extend substantially the length of a span of the blade and providing a plurality of second plies, each of the second plies sized to extend only partially the length of the span of the blade. The method also includes layering the plurality of first plies and the plurality of second plies in a mold such that the plurality of second plies is interspersed throughout the plurality of first plies to spread apart the plurality of first plies to facilitate increasing a cross-sectional area of the blade and bonding the plurality of first plies to the plurality of second plies to facilitate forming a structural core of the blade.

Method and system for manufacturing a blade

Embodiments of the present invention allow an operator to select one, two, or more tires in the system to have their individual pressure measured or equalized and set by either connecting it to a compressed air supply or by bleeding out excess air to reduce tire pressure. This is all done by operating the push-button valves on the gauge handle to read and/or bleed when the push-button valve for reading is not actuated; it isolates the gauge from the compressor's air pressure during a filling phase to prevent its being damaged.

Growing community of inventors

Cincinnati, OH, United States of America

Michael John Franks