General Electric Company

Genearl Electric Company

General Electric Technology Gmbh

Victor John Morgan

Neelesh Nandkumar Sarawate

Benjamin Paul Lacy

Jacob John Kittleson

Frederic Woodrow Roberts, Jr

Matthew Troy Hafner

David Wayne Weber

Jonathan Dwight Berry

Kevin Weston McMahan

Deepak Trivedi

Brian Peter Arness

Brian Gene Brzek

Ibrahim Sezer

Russell Pierson DeForest

George Andrew Gergely

Gary Michael Itzel

John McConnell Delvaux

Aaron Ezekiel Smith

Gregory Thomas Foster

Andres Jose Garcia-Crespo

James Albert Tallman

John Wesley Harris, Jr

David Richard Johns

Jesse Ellis Barton

Thomas James Brunt

Stephen William Tesh

Stephen Gerard Pope

Srikanth Chandrudu Kottilingam

Christopher Edward Wolfe

Michael John Hughes

Curtis Alan Johnson

David Edward Schick

Zachary John Snider

Paul Stephen DiMascio

Andrew Philip Shapiro

Richard Martin DiCintio

Jason Robert Parolini

Brendon James Leary

Glenn Curtis Taxacher

Kevin Richard Kirtley

Thomas Earl Dyson

Rebecca Evelyn Hefner

Brad Wilson Vantassel

Joshua Lee Margolies

Michael James Healy

Alexander Stein

Omprakash Samudrala

James Fredric Wiedenhoefer

Bryan David Lewis

Kevin Thomas McGovern

Richard William Johnson

John Franklin Ryman

Mary Virginia Holloway

Donald Earl Floyd

John Alan Eastman

Jonathan Glenn Reed

Charles Andrew Malinowski

Joseph H Fagan

Tyler Christopher Henson

Jason Ray Gregg

Elisabeth Kraus Black

David Benjamin Helmer

Lawrence Matthew Levy

Bradley Thomas Richards

Tomas A Velez

Earl Thomas Dyson

John Mcconnell Delvaux

Kevin Weston Mcmahan

Richard Martin Dicintio

Russell Pierson Deforest

Kevin Thomas Mcgovern

A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

Curved seal for adjacent gas turbine components

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

Component with mechanical locking features incorporating adaptive cooling and method of making

A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed on the exterior surface. The coating system has a thickness. The component further includes a plurality of adaptive cooling openings defined in the outer wall. Each of the adaptive cooling openings extends from a first end inflow communication with the at least one plenum, outward through the exterior surface and to a second end covered underneath at least a portion of the thickness of the coating system.

Coated components having adaptive cooling openings and methods of making the same

An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.

Integrated combustor nozzles with continuously curved liner segments

A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover may include a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface.

Adaptive cover for cooling pathway by additive manufacture

A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; a thermal barrier coating over the outer surface; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover includes a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface, e.g., when a spall in a thermal barrier coating thereover occurs.

A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.

Pressure-loaded seals

A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.

Coated turbine component and method for forming a component

A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.

Adaptively opening backup cooling pathway

A hot gas path component of an industrial machine includes a cooling pathway. The component includes a body including an outer surface; a thermal barrier coating (TBC) over the outer surface, the TBC exposed to a working fluid having a high temperature; and an internal cooling circuit in the body carrying a cooling medium. A cooling pathway is in the body and in fluid communication with the internal cooling circuit. The cooling pathway includes a terminating end in the body and a length extending along and spaced internally from the outer surface by a first spacing. In response to a spall in the TBC occurring at a location over the cooling pathway and the high temperature reaching or exceeding a predetermined temperature of the body, the cooling pathway opens at the location through the first spacing to allow a flow of the cooling medium therethrough.

Adaptively opening cooling pathway

A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first portion that is axially offset from the first inner seal and the second inner seal and a second portion abutting the first inner seal and the second inner seal. Also disclosed is an aft frame having a forward face and an aft face. The aft frame includes at least one side seal slot that extends along a side portion. A first portion of the side seal slot is axially offset from the aft face. A second portion of the side seal slot is axially and radially offset from the first portion.

Side seal with reduced corner leakage

An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

Systems and methods for assembling flow path components

A method of providing cooling structure for a component including forming a first cavity in the component and forming a first passageway in the first cavity in fluid communication with a second cavity positioned inside the component, the second cavity in fluid communication with a cooling air source. The method includes forming a unitary insert including a first surface, a second surface, the insert having an inlet formed in the first surface and an outlet formed in the second surface. A second passageway is in fluid communication with the inlet and the outlet. The method includes positioning the insert in the first cavity into fluid communication with the first passageway, the first surface facing the first cavity; and rigidly attaching the insert in the first cavity.

Method of providing cooling structure for a component

A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

Ceramic matrix composite component and process of producing a ceramic matrix composite component

Growing community of inventors

Simpsonville, SC, United States of America

Victor John Morgan