General Electric Company

Ge Infrastructure Technology, LLC

Srikanth Chandrudu Kottilingam

Yan Cui

Brian Lee Tollison

David Edward Schick

Dechao Lin

Benjamin Paul Lacy

David Vincent Bucci

Jon Conrad Schaeffer

Surinder Singh Pabla

Sandip Dutta

Canan Uslu Hardwicke

Ganjiang Feng

Daniel Anthony Nowak

Matthew Troy Hafner

Jason Robert Parolini

Christopher Donald Porter

Brad Wilson Vantassel

Gary Michael Itzel

Zachary John Snider

John Wesley Harris, Jr

Carlos Miguel Miranda

Cem Murat Eminoglu

Bill Damon Johnston, Jr

Steven John Barnell

Prabhjot Singh

Jonathan Matthew Lomas

Arthur Samuel Peck

Matthew Joseph Laylock

Brian Leslie Henderson

Jonathan Dwight Berry

John McConnell Delvaux

Richard Martin DiCintio

Stephen Paul Wassynger

Brian Gene Brzek

Michael Douglas Arnett

Richard Ryan Pilson

Joseph Leonard Moroso

Kathleen Blanche Morey

James Murray

Ibrahim Ucok

James Joseph Murray, Iii

Lacey Lynn Schwab

Biju Dasan

Gareth William David Lewis

Xiaoxue Diao

John Gregory Obeirne

Steven Charles Rauch

Lucas John Stoia

David Wayne Weber

Kwok Pong Chan

Michael John Hughes

William Edward Adis

Gregory Thomas Foster

Paul Stephen DiMascio

Kurt Kramer Schleif

Victor John Morgan

Neelesh Nandkumar Sarawate

Arunkumar Natarajan

Andrew Lee Trimmer

Vadim Bromberg

Charles Gitahi Mukira

Bradley Taylor Boyer

Nicholas Thomas

Joseph Anthony Weber

Melbourne James Myers

Laura Cerully Dial

Michael Dennis Mack

Johnie Franklin McConnaughhay

Kassy Moy Hart

Bryan Joseph Germann

Liangde Xie

Daniel James Dorriety

Timothy James Purcell

Matthew Paul Berkebile

Ariel Caesar Prepena Jacala

Jeffrey Jon Schoonover

Matthew Durham Collier

Jere Allen Johnson, Jr

Martin James Jasper

Christopher Michael Penny

Jacob Andrew Salm

Dennis William Cavanaugh

Jamison William Janawitz

Daniel Howard Tragesser

Doyle Clyde Lewis

Lawrence James Whims

Warren Tan King

Ronald Lee Souther

Eric Eicher McConnell

Michael David McDufford

Dheepa Srinivasan

Warren Martin Miglietti

John D Ward

Daniel Frederick Purdy

Lyndsay Marie Kibler

Carlos Bonilla Gonzalez

Kenneth Burrell Potter

Jian Zheng

Patrick Thomas Walsh

Dayananda Narayana

A system includes a powder reuse system (PRS) executable via a processor and configured to receive one or more inputs for a build of a first machine component in a sintering system. The PRS is further configured to retrieve a model configured to model a reuse of a sintering powder, and to derive a time during which a surplus unsintered powder left after printing the machine component via the sintering system using the sintering powder may be reused to build a second machine component by applying the one or more inputs to the model.

System and method for reusing powder in additive manufacturing

A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

Oxidation and wear resistant brazed coating

A process includes forming a printed article having an external surface and at least one microfeature with an internal surface by additive manufacture, coating the external surface and the internal surface of the printed article with a metallic microlayer to form a coated article, and densifying the coated article to form a component. After formation, the printed article has a porosity such that the printed article is not at full density. A densified component includes a printed article having an external surface and at least one microfeature with an internal surface and a metallic microlayer coating the external surface and the internal surface of the printed article. The printed article is formed by additive manufacture.

Process and printed article

At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

Turbine components and methods of manufacturing

A multi-piece part includes multiple pieces fabricated via different types of fabrication processes, wherein the multiple parts are configured to be coupled to one another to form the assembly. At least one of the multiple parts is fabricated via an additive manufacturing method. The multi-piece part also includes a holder assembly that couples and holds together the multiple pieces of the multi-piece part, wherein the holder assembly comprises a reversible, mechanical-type coupling.

Method for the hybrid construction of multi-piece parts

Systems and methods for infiltrating porous ceramic matrix composite (CMC) preforms to form CMC articles are disclosed. One method may include positioning the porous CMC preform in an opening of a die set for an infiltration system, and flowing a molten densifier over the porous CMC preform in a first flow direction to infiltrate a plurality of voids formed between each of a plurality of ply stacks of the CMC preform. The method may also include flowing the molten densifier over the porous CMC preform in a second flow direction, distinct from the first flow direction, to infiltrate the plurality of voids formed between each of the plurality of ply stacks of the CMC preform. The second flow direction may be substantially parallel to a predetermined, unidirectional material orientation of at least one ply stack of the plurality of ply stacks of the CMC preform.

Systems and methods for infiltrating porous ceramic matrix composite (CMC) preforms

A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

System for addressing turbine blade tip rail wear in rubbing and cooling

A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

Coolant delivery via an independent cooling circuit

An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.

An effusion cooling element for the surface of a hot gas path (HGP) component is disclosed. The effusion cooling element includes a coolant swirling chamber embedded within the body of the HGP component. A coolant delivery passage is in the body and configured to deliver a coolant to the coolant swirling chamber. The coolant swirling chamber imparts a centrifugal force to the coolant. An effusion opening is in the HGP surface and in fluid communication with the coolant swirling chamber, the effusion opening having a smaller width than the coolant swirling chamber. The coolant exits the effusion opening over substantially all of 360&#xb0; about the effusion opening, creating a coolant film on the HGP surface.

HGP component with effusion cooling element having coolant swirling chamber

A nozzle or blade for a turbomachine includes an airfoil body including at least one first coolant passage, and an edge opening in a leading edge or a trailing edge of the airfoil body. The edge opening has an edge coupon retention member seat in or on an inner surface of the airfoil body. An edge coupon has a shape at least partially configured for coupling to the edge opening in the airfoil body. The edge coupon includes an edge coupon body, at least one second coolant passage in the edge coupon body configured for fluid communication with the at least one first coolant passage in the airfoil body, and a retention member extending from the edge coupon body for coupling to the edge coupon retention member seat in the airfoil body.

Airfoil coupon attachment

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

Controlling extent of TBC sheet spall

A blade for a turbomachine, a tip for a blade of a turbomachine and a related method are disclosed. The blade may include a tip body having a shape at least partially configured for coupling to an airfoil body of the blade; at least one coolant passage in the tip body configured for fluid communication with at least one coolant passage in the airfoil body; and a retention member extending from the tip body for coupling to a tip retention member seat in the airfoil body. The tip can be replaced, allowing for changes in the coolant passages in the tip of a blade.

Turbomachine blade tip attachment

Growing community of inventors

Simpsonville, SC, United States of America

Srikanth Chandrudu Kottilingam