General Electric Company

Joshua Brian Jamison

Mark Willard Marusko

Toby George Darkins, Jr

John Peter Heyward

Toby George Darkins

Mark Eugene Noe

Eric Alan Estill

James Thomas Hawkins

Michael James Verrilli

James Herbert Deines

Paul Izon

Anthony Reid Paige

Roger Lee Doughty

Jason David Shapiro

Patrick Joseph Howard

Michael John Franks

Samuel Ross Rulli

Joseph Manuel Portaz

Michael Verrilli

Chad Daniel Kleinow

Andrew John Breslin

Matthew Edward Dragovich

Ii Paige Anthony Reid

Toby George Darkins Jr

Mark Msrusko

Anthony Reid Paige Ii

A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank. The at least one top ply and at least one side ply form an angel wing and a skirt with on the shank of the ceramic matrix composite component.

Turbine blade sealing structure

A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.

Turbine rotor blade assembly and method of assembling same

A turbine component assembly for a gas turbine engine includes: a first component having a first coefficient of thermal expansion and including an end face; a second component including a mating surface abutting the end face; and a fastener having a second coefficient of thermal expansion different from the first coefficient of thermal expansion, the fastener including a shank engaging the second component and an enlarged head engaging a mounting slot in the first component; wherein the mating surface and the end face shaped to permit relative pivoting movement between the first and second components.

Turbine component connection with thermally stress-free fastener

A process for producing airfoil components containing ceramic-based materials and having a tip cap. The process entails forming an airfoil portion of the component from an airfoil portion material that contains a precursor of a ceramic-based material. The airfoil portion material defines concave and convex walls of the airfoil portion, and the concave and convex walls define a tip region of the airfoil portion and at least one cavity within the airfoil portion. At least a first ply is formed that contains a precursor of a ceramic-based material, and the first ply at least partially closes the cavity at the tip region of the airfoil portion. The airfoil portion material and the first ply are then cured so that the first ply forms a tip cap that closes the cavity and the precursors of the airfoil portion material and first ply are converted to the ceramic-based materials thereof.

Airfoil components containing ceramic-based materials and processes therefor

Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.

Turbine airfoil components containing ceramic-based materials and processes therefor

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 turbomachinery blade includes: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix The shank includes a pair of spaced-apart side faces that cooperatively define: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum.

Interlaminar stress reducing configuration for composite turbine components

Hybrid components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the components. The components includes a first subcomponent formed of a ceramic-based material and a second subcomponent formed of a metallic material. The first subcomponent has a nub and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent is attached to the first subcomponent by a compression fit and encapsulation of the second subcomponent on the nub of the first subcomponent. The nub has a compliant coating system that provides thermal expansion compliance between the metallic material of the second subcomponent and the ceramic-based material of the first subcomponent.

Components containing ceramic-based materials and coatings therefor

A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.

Processes for producing a component containing a ceramic-based material and having detailed features formed from materials other than ceramic materials. Such a process entails producing the component to include a first subcomponent and at least a second subcomponent having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent. The first subcomponent is formed of a ceramic-based material, and the second subcomponent and its off-axis geometric feature are separately formed of a metallic material and attached to the first subcomponent to yield a robust mechanical attachment. The component may be, for example, a gas turbine airfoil component.

Processes for producing components containing ceramic-based and metallic materials

A method and system for nondestructively detecting and quantifying material anomalies within materials, including composite articles. The method entails performing a three-dimensional imaging scan technique, such as a computed tomography scan, of the material and a reference standard such that a test image of the material and a reference image of the reference standard appear in a plurality of two-dimensional scan views generated by the scan technique. The reference images are located in the scan views and normalized to determine at least an average value of the pixel data for the reference images. Values of pixel data of the test image are determined in each scan view, and then compared to the pixel data of the reference images to detect the presence of an anomaly in the test images. The detected anomaly in at least one of the test images of the scan views is then compared to a requirement standard for the material.

Growing community of inventors

Liberty Township, OH, United States of America

Joshua Brian Jamison