General Electric Company

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Bangalore Aswatha Nagaraj

Irene T Spitsberg

Brian Thomas Hazel

Christine Govern

Mark Daniel Gorman

Ramgopal Darolia

John Frederick Ackerman

David John Wortman

Craig Douglas Young

Brett Allen Rohrer Boutwell

Curtis Alan Johnson

Robert William Bruce

Michael James Weimer

Jon Conrad Schaeffer

Brett Allen Boutwell

Paul Vincent Arszman

Joseph Aloysius Heaney

Ching-Pang Lee

Joseph David Rigney

Lawrence Bernard Kool

Alfred Albert Mancini

William Randolph Stowell

William Scott Walston

Bhupendra Kumar Gupta

Hongyu Wang

David Vincent Rigney

David Joseph Mitchell

Rudolfo Viguie

John Frederick Ackermann

Nicole Justis

Nripendra Nath Das

Thomas John Tomlinson

Ming Fu

William B Connor

Eva Zielonka Lanman

Jeffrey Lawrence Williams

Michael Anthony Benjamin

Glen Harold Kirby

Krishan Lal Luthra

Lawrence E Szala

Robert A Miller

Peter Joel Meschter

Jeffrey Allen Conner

Roger Dale Wustman

D Sangeeta

Jeffrey Allan Pfaendtner

David Winfield Woodruff

Clifford L Spiro

Joshua L Miller

Warren Arthur Nelson

Mark Alan Rosenzweig

John W Devitt

William Patrick Allen

Seetha Ramaiah Mannava

James L Smialek

David William Skelly

Kang Neung Lee

Yan Gao

Harry Edwin Eaton, Jr

Nathan S Jacobson

Elizabeth J Opila

Michael David Clark

James Andrew Hahn

Robert George Baur

Thomas George Holland

Ronald T Murach

Antoinette E Weil

Susan Lee Sheets

Venkat Subramaniam Venkataramani

Douglas Gerard Konitzer

Yuk-Chiu Lau

Todd Jay Rockstroh

Seetharamaiah Mannava

Larry W Plemmons

Himanshu B Vakil

Eric Alan Estill

Robert Edward Schafrik

Rajasingh Schwartz Israel

Raymond William Heidorn

Marie Ann McMasters

Wendy Howard Murphy

Antonio Frank Maricocchi

Wilbur Douglas Scheidt

Wenfeng Lu

Jim D Reeves

Kevin S O'Hara

David Allen Kastrup

Robert George Zimmerman, Jr

David Walter Parry

Richard William Jendrix

Matthew David Saylor

Joseph M Guentert

Jackie Lee King

Julie Marie Chapman

Joseph A Heaney, Iii

D Keith Patrick

Aaron Dennis Gastrich

Siva Ram Surya Sanyasi Adavikolanu

Deborah Anne Schorr

Michal Stanislaw Chomka

A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits

A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Surfaces for contacting a hydrocarbon fluid and methods for preparing the same

A coating system for a surface of a superalloy component is provided. The coating system includes a MCrAlY coating on the surface of the superalloy component, where M is Ni, Fe, Co, or a combination thereof. The MCrAlY coating generally has a higher chromium content than the superalloy component. The MCrAlY coating also includes a platinum-group metal aluminide diffusion layer. The MCrAlY coating includes Re, Ta, or a mixture thereof. Methods are also provided for forming a coating system on a surface of a superalloy component.

Airfoil with improved coating system and methods of forming the same

A method for forming a coating on a surface of an airfoil is provided, where the airfoil has a leading edge, a trailing edge, a pressure side, and a suction side. The method can include forming a platinum-group metal layer on the surface of the airfoil along at least a portion of the trailing edge, and forming an aluminide coating over the surface of the airfoil of the leading edge, the trailing edge, the pressure side, and the suction side. The leading edge may be substantially free from any platinum-group metal. The method may further include, prior to forming the aluminide coating, forming a bond coating on the surface of the airfoil along the leading edge, and after forming the aluminide coating, forming a thermal barrier coating over the bond coating. A method is also generally provided for repairing a coating on a surface of an airfoil.

Article with improved coating system and methods of forming the same

Airfoil with improved coating system

Coating systems and processes by which the coating systems can be deposited to be resistant to contaminants, and particularly resistant to infiltration and damage caused by CMAS. The coating systems include inner and outer ceramic layers. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria and optionally contains greater than 0.5 to 10 weight percent hafnium oxide. The outer ceramic layer overlies and contacts the inner ceramic layer to define the outermost surface of the coating system. The outer ceramic layer consists essentially of zirconia stabilized by about 25 to about 75 weight percent yttria, has a thickness that is less than the thickness of the inner ceramic layer and further contains greater than 0.5 to 10 weight percent hafnium oxide and optionally 1 to 10 weight percent tantalum oxide. The outer ceramic layer has a porosity level that is lower than that of the inner ceramic layer.

Thermal barrier coating systems and processes therefor

Coating systems and processes by which the coating systems can be deposited to be resistant to contaminants, and particularly resistant to infiltration and damage caused by CMAS. The coating systems include inner and outer ceramic layers, each having a microstructure characterized by splats and horizontal porosity. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria. The outer ceramic layer overlies and contacts the inner ceramic layer to define the outermost surface of the coating system. The outer ceramic layer consists essentially of zirconia stabilized by about 25 to about 75 weight percent yttria, has a thickness that is less than the thickness of the inner ceramic layer, and has a porosity level that is lower than that of the inner ceramic layer.

A method and system for enhancing the heat transfer of turbine engine components is disclosed that includes applying a metallic coating having a high thermal conductivity to the cold side of a turbine component to enhance heat transfer away from the component. The metallic coating may be roughened to improve heat transfer. The metal coating may be a Ni&#x2014;Al bond coating having an aluminum content greater than about 50 weight percent.

Method and system for enhancing heat transfer of turbine engine components

Calcium magnesium aluminosilicate (CMAS) mitigation compositions selected from rare earth elements, rare earth oxides, zirconia, hafnia partially or fully stabilized with alkaline earth or rare earth elements, zirconia partially or fully stabilized with alkaline earth or rare earth elements, magnesium oxide, cordierite, aluminum phosphate, magnesium silicate, and combinations thereof when the CMAS mitigation composition is included as a separate CMAS mitigation layer in an environmental barrier coating for a high temperature substrate component.

CMAS mitigation compositions, environmental barrier coatings comprising the same, and ceramic components comprising the same

Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability involving providing a component; applying an environmental barrier coating to the component, the environmental barrier coating having a separate CMAS mitigation layer including a CMAS mitigation composition selected from rare earth elements, rare earth oxides, zirconia, hafnia partially or fully stabilized with alkaline earth or rare earth elements, zirconia partially or fully stabilized with alkaline earth or rare earth elements, magnesium oxide, cordierite, aluminum phosphate, magnesium silicate, and combinations thereof.

Methods for making environmental barrier coatings and ceramic components having CMAS mitigation capability

Thermal barrier coating systems for use with hot section components of a gas turbine engine include an inner layer overlying a bond coated substrate and a top layer overlying at least a portion of the inner layer. The inner layer includes a thermal barrier material such as yttria-stabilized zirconia. The top layer includes a rare earth aluminate. The thicknesses and microstructures of the layers may be varied depending on the type of component to be coated. Articles incorporating the thermal barrier coating system exhibit improved resistance to CMAS infiltration.

Thermal barrier coating systems including a rare earth aluminate layer for improved resistance to CMAS infiltration and coated articles

A gas turbine engine turbine blade comprising an airfoil section, a platform section, an under platform section, and a dovetail section, an exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further comprises a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of an exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the silicon modified diffusion aluminide layer having a concentration of silicon at a surface of the silicon-modified diffusion aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the silicon modified diffusion aluminide layer in the range of about 5 weight percent to about 25 weight percent.

Corrosion coating for turbine blade environmental protection

A thermal barrier coating and deposition process for a component intended for use in a hostile thermal environment, such as the turbine, combustor and augmentor components of a gas turbine engine. The TBC has a first coating portion on at least a first surface portion of the component. The first coating portion is formed of a ceramic material to have at least an inner region, at least an outer region overlying the inner region, and a columnar microstructure whereby the inner and outer regions comprise columns of the ceramic material. The columns of the inner region are more closely spaced than the columns of the outer region so that the inner region of the first coating portion is denser than the outer region of the first coating portion, wherein the higher density of the inner region promotes the impact resistance of the first coating portion.

Thermal barrier coating and process therefor

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West Chester, OH, United States of America

Bangalore Aswatha Nagaraj