General Electric Company

Ge Infrastructure Technology, LLC

Other

General Electric Technology Gmbh

Jon Conrad Schaeffer

Srikanth Chandrudu Kottilingam

William Scott Walston

Michael Douglas Arnett

Brian Lee Tollison

Mark Alan Rosenzweig

Yan Cui

Bangalore Aswatha Nagaraj

David John Wortman

Robert William Bruce

Canan Uslu Hardwicke

Krishnamurthy Anand

Ganjiang Feng

Irene T Spitsberg

David Edward Schick

David Vincent Bucci

Surinder Singh Pabla

Jason Robert Parolini

Jeffrey Allen Conner

Ching-Pang Lee

Melvin Robert Jackson

Michael James Weimer

Pazhayannur Ramanathan Subramanian

Nripendra Nath Das

Nesim Abuaf

Robert Alan Johnson

Warren Davis Grossklaus, Jr

Warren Arthur Nelson

Joshua Lee Margolies

Gary Eugene Wheat

Ronald Scott Bunker

Ramgopal Darolia

Benjamin Paul Lacy

Bin Wei

James Anthony Ruud

Alston Ilford Scipio

Sanji Ekanayake

Joseph David Rigney

Wayne Charles Hasz

John Frederick Ackerman

Paul Stephen DiMascio

Dechao Lin

Ji-Cheng Zhao

Michael F Henry

Dennis Michael Gray

Maxim Konter

Michael Francis Xavier Gigliotti, Jr

Roger Dale Wustman

Charles Gitahi Mukira

David F Lahrman

Iain Robertson Kellock

Wendy Howard Murphy

Arthur Samuel Peck

Jianqiang Chen

Shenyan Huang

Kathleen Blanche Morey

Shan Liu

Robert Romany By

Christopher Raymond Hanslits

William B Connor

Norman R Lindblad

Junyoung Park

Matthew Joseph Laylock

Kevin S O'Hara

David Vincent Rigney

Sundar Amancherla

Akane Suzuki

Thomas Michael Moors

Susan Marie Hyde

Ariel Caesar-Prepena Jacala

Calvin Levy Sims

Padmaja Parakala

Robert D Field

Kevin G McAllister

Paul S Dimascio

Thomas Froats Broderick

Antonio Frank Maricocchi

Wilbur Douglas Scheidt

John Matthew Powers

Judd Dodge Tressler

Paul Stuart Wilson

Ibrahim Ucok

Rudolfo Viguie

Wenwu Zhang

John Zhiqiang Wang

Joseph Aloysius Heaney

Steven John Barnell

Mark Alan Rhoads

Dennis Paul Dry

P Kennard Wright, Iii

Doyle Clyde Lewis

Martin Mathew Morra

Lacey Lynn Schwab

Jared Micheal Iverson

Vinod Kumar Pareek

Andrew John Elliott

Eugene Clemens

Sharon Trombly Swede

Martin Matthew Morra

Paul John Fink

A method of forming a component. The method includes applying a thermal barrier coating to the component to facilitate decreasing heat transfer to the component, wherein the thermal barrier coating includes at least one thermal insulating layer and a metallic bond coat layer in contact with an outer surface of the component. The method also includes forming a plurality of grooves in the at least one thermal insulating layer of the thermal barrier coating to facilitate increasing a strain tolerance of the thermal barrier coating, wherein each of the plurality of grooves extends a depth into the at least one thermal insulating layer. The method further includes depositing a material within the plurality of grooves to facilitate increasing an amount of thermal protection of the metallic bond coat layer within those areas of the thermal barrier coating in which the plurality of grooves are formed.

Thermal protection methods using barrier coatings with strain tolerance grooves

A method of forming a directionally-solidified casting component using a casting system is provided. The casting system includes a chamber having a heating zone and a cooling zone separated by a baffle plate. The method includes pouring an alloy in a liquid state into a mold shell. The mold shell is positioned on a chill plate within the heating zone. The method further includes moving the mold shell from the heating zone into the cooling zone. The alloy transfers from the liquid state to a solid state within the mold shell while moving the mold shell from the heating zone to the cooling zone. The method further includes contacting the mold shell with a heat transfer member.

Heat extraction or retention during directional solidification of a casting component

The present application provides a replaceable galvanic protection anode system for preventing and limiting the effects of liberation and damage to airfoils in a gas turbine, wherein turbine components are covered by a sacrificial material. The galvanic protection layer of the replaceable anodes may include a sacrificial material, such as aluminum, wherein the material provides corrosion resistance to the substrate. Additionally, the galvanic protection layer may include a sacrificial conductive material insert for increasing the conductivity of the sacrificial material and further improve the corrosion resistance of the replaceable anodes.

Systems and methods for preventing liberation and damage to airfoils in a gas turbine

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

A composition includes, by weight percent: Cobalt (Co) between about 4.5 and about 7.0; Chromium (Cr) between about 10.2 and about 11.5; Molybdenum (Mo) between about 0.5 and about 2.5; Tungsten (W) between about 4.0 and about 5.5; Rhenium (Re) between about 0 and about 1.2; Aluminum (Al) between about 6.2 and about 6.8; Tantalum (Ta) between about 4.5 and about 6.0; Titanium (Ti) between about 0 and about 0.5; Hafnium (Hf) between about 0 and about 0.5; Carbon (C) between about 0 and about 0.2; Boron (B) between about 0 and about 0.02; and the balance Nickel (Ni), and other incidental impurities.

Nickel-based superalloy

Compositions, and articles and methods for forming articles which include said compositions, are disclosed. The compositions include, by weight percent, about 13.7% to about 14.3% chromium (Cr), about 9.0% to about 9.9% cobalt (Co), about 4.0% to about 5.25% aluminum (Al), about 0.5% to about 3.0% titanium (Ti), about 4.5% to about 5.0% tungsten (W), about 1.4% to about 1.7% molybdenum (Mo), about 3.25% to about 3.75% niobium (Nb), about 0.08% to about 0.12% carbon (C), about 0.005% to about 0.04% zirconium (Zr), about 0.010% to about 0.014% boron (B), and balance nickel (Ni) and incidental impurities.

Compositions, articles and methods for forming the same

A nickel-based superalloy composition including by weight percent: Cobalt 7.5; Chromium 9.75; Aluminum 5.45; Titanium 1.0; Niobium 3.5; Tungsten 6.0; Molybdenum 1.5; Carbon 0.08; Hafnium 0.15; Boron 0.01; and Nickel 65.0; and incidental impurities.

Nickel-based superalloys

Embodiments of the disclosure provide a system including: an enclosure having an interior sized to enclose and the workpiece and form a vacuum and pressurized atmosphere within the interior. A plurality of thermal applicators may be in thermal communication with first and second portions of the interior. First and second thermal applicators may independently heat and cool the first and second portions of the interior. The first thermal applicator may apply a first thermal treatment to a first portion of the workpiece in the first portion of the interior. A second thermal applicator may apply a second thermal treatment to a second portion of the workpiece in the second portion of the interior independently of the first thermal treatment.

System and method to apply multiple thermal treatments to workpiece and related turbomachine components

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

Embodiments of the disclosure provide a turbomachine component, including: a base portion configured for mounting on a rotor; an airfoil portion having a first end coupled to the base portion, and a second end opposite the first end. A creep resistance of the airfoil portion is greater than the base portion, and a fracture toughness of the airfoil portion is less than the base portion. A tip portion may be coupled to the second end of the airfoil portion. A creep resistance of the tip portion is less than the airfoil portion and greater than the base portion. A fracture toughness of the tip portion is less than the base portion and greater than the airfoil portion.

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

In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Nickel-based superalloy with microstructure including rafting-resistant gamma prime phase and article prepared therefrom

A cast nickel-base superalloy that includes iron added substitutionally for nickel. The cast nickel-base superalloy comprises, in weight percent about 1-6% iron, about 7.5-19.1% cobalt, about 7-22.5% chromium, about 1.2-6.2% aluminum, optionally up to about 5% titanium, optionally up to about 6.5% tantalum, optionally up to about 1% Nb, about 2-6% W, optionally up to about 3% Re, optionally up to about 4% Mo, about 0.05-0.18% C, optionally up to about 0.15% Hf, about 0.004-0.015 B, optionally up to about 0.1% Zr, and the balance Ni and incidental impurities. The superalloy is characterized by a &#x3b3;' solvus temperature that is within 5% of the &#x3b3;&#x2032; solvus temperature of the superalloy that does not include 1-6% Fe and a mole fraction of &#x3b3;&#x2032; that is within 15% of the mole fraction of the superalloy that does not include 1-6% Fe.

Cast nickel-base superalloy including iron

Growing community of inventors

Simpsonville, SC, United States of America

Jon Conrad Schaeffer