General Electric Company

University of Wyoming

John Frederick Ackerman

William Randolph Stowell

Andrew Jay Skoog

Bangalore Aswatha Nagaraj

Paul Vincent Arszman

Glen Harold Kirby

George A Coffinberry

Brett Allen Boutwell

Jane Ann Murphy

Matthew Bernard Buczek

Ching-Pang Lee

Michael James Weimer

Kevin Richard Leamy

Joseph Aloysius Heaney

William Kent Wagner

Alok Mani Srivastava

Alfred Albert Mancini

William Scott Walston

Jeffrey Allen Conner

Siegfried Aftergut

Robert Alan Johnson

Adrian M Beltran

John Herbert Wood

Israel S Jacobs

Catherine Procik Dulka

Daniel G Backman

John Erik Hershey

Joseph Michael Ranish

Ramgopal Darolia

Anil Raj Duggal

Jon Conrad Schaeffer

Irene T Spitsberg

Venkat Subramaniam Venkataramani

Lionel M Levinson

Andrew Philip Woodfield

Darrell Glenn Senile

Nripendra Nath Das

Brian Thomas Hazel

Michael Francis Xavier Gigliotti

Eric Allen Ott

David Allen Bell

David Paul Mourer

Himanshu B Vakil

Bhupendra Kumar Gupta

Egidijus Edward Uzgiris

Robert Edward Schafrik

Rajasingh Schwartz Israel

Brock Estel Osborn

Thomas Froats Broderick

Robert D Lillquist

Antonio Frank Maricocchi

Thomas Walter Rentz

Richard August Korkosz

Ronald H Wilson

John Matthew Powers

George A Durgin

John Douglas Evans, Sr

Robert George Zimmerman, Jr

Nicolas Wadih Chbat

Jon Raymond Groh

Kenneth Rees Bain

Laurence Bigio

Kenneth L Johnson

Clyde L Briant

James Edgar Burner

Sang Yeng Park

Randy Lee Lewis

David Wesley Sandusky

Daniel Peter Ivkovich, Jr

George E Cook

Morris Dee Argyle

Brian Keith Flandermeyer

Robert W Harris

Bryan Thomas Bojanowski

Glen Arthur MacMillan

Timothy Ray Lattire

Jeffrey Lawrence Williams

Nicole Justis

Matthew Timothy Franer

Amy Victoria Aragones

James Andrew Hahn

Leland L Lantz

Mark Olaf Lenz

Anthony Wayne Reynolds

David Dye

Gail E Dunning

Frederick J Sellers

Brian Francis Towler

Vijay Kumar Millikarjun Hanagandi

Michael B McMahan

Richard Oran Kilgo

Edwin R Baker

Soon Jai Khang

Dan Ivkovich

Jennifer Ann Pinson

Brian Thomas Pothier

Glenn E Varney

Rekha Agarwal, Legal Representative

Ron Borgialli

Jerry Hamann

Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability include providing a component, applying an environmental barrier coating to the component, where the environmental barrier coating includes a CMAS mitigation composition selected from the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.

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

A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture.

System and method of operating a power generation system with an alternative working fluid

A coating system that includes a plurality of portions, each portion comprising one or more layers. The coating system includes an outer portion, which is an infrared radiation (IR) interaction portion, that dissipates incident (IR). Underlying this outer portion is a performance portion. The performance portion comprises at least one layer that includes microspheres. Between the substrate and performance portion is a compliance portion. The compliance portion comprises at least one layer of high temperature material that has a coefficient of thermal expansion (CTE) intermediate the performance layer and the substrate. The compliance portion thus reduces any high temperature thermal mismatch between the substrate and the performance portion.

Low thermal and radiation conductivity coating

Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability including 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 the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.

Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising aluminide-alumina TGO; and an outer layer selected from the group consisting of AeAl2O19, AeHfO3, AeZrO3, ZnAl2O4, MgAl2O4, Ln4Al2O9, Lna4Ga2O9, Ln3Al5O12, Ln3Ga5O12, Ga2O3, HfO2, and LnPO4.

Environmental barrier coatings providing CMAS mitigation capability for ceramic substrate components

Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising silicon or silicide, and an outer layer selected from the group consisting of LnAlO, and LnaGaO.

Environmental barrier coating having CMAS mitigation capability for oxide components. In one embodiment, the barrier coating includes an outer layer selected from AeAlO, AeHfO, AeZrO, ZnAlO, MgAlO, LnAlO, LnaGaO, LnAlO, LnGaO, and GaO.

An article is prepared by furnishing a plurality of powder particle substrates made of a substrate metal, providing a nonmetallic precursor of a metallic coating material, wherein the metallic coating material comprises an alloying element that is thermophysically melt incompatible with the substrate metal, contacting the powder particle substrates with the nonmetallic precursor, chemically reducing the nonmetallic precursor to form coated powder particles comprising the powder particle substrates having a surface-enriched layer of the metallic coating material thereon without melting the powder particle substrates, and processing the coated powder particles to form the article, without melting the powder particle substrates.

Article prepared by depositing an alloying element on powder particles, and making the article from the particles

A coated fan rotor blade and method for coating a fan rotor blade. The coated fan rotor blade includes a fan rotor blade; and a coating disposed on said fan rotor blade. The coating comprises a binder; and a filler made up of a plurality of particles. The filler material is incorporated into the binder material, and the particles in the filler interact to produce vibrational damping. In particular, the coating includes small, dense, flattened particles or plates that are incorporated into a thin layer of visco-elastic material, such as rubber, silicone, fluoro-elastomer, or urethane and bonded to the surface of the rotor blade to provide damping of high frequency excitation.

Vibration damper coating

A coating system for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to fluid containment surfaces. The coating system combines an outermost layer of platinum with an inner ceramic barrier layer of silica and/or tantala. The platinum layer catalyzes the hydrocarbon fluid to form particles of carbonaceous gum substances, and the ceramic barrier layer seals the containment surface from the hydrocarbon fluid to eliminate attachments points for deposits and inhibit interdiffusion between the platinum layer and the containment surface. The invention also encompasses a coating apparatus and process for depositing the coating system.

Coating system and process and apparatus for depositing a coating system

A coating system and method for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to a wall of a containment article. Of particular concern are carbonaceous deposits that form at temperatures below about 650&#xb0; F. (about 345&#xb0; C.). The coating system combines an outermost layer of platinum with a ceramic barrier layer. The coating system significantly reduces the formation of carbonaceous deposits and the adhesion of such deposits. To further reduce wall and hydrocarbon fluid temperatures and formation of carbonaceous deposits, the coating system is preferably applied to the surface of the wall wetted by the fluid, as well as the opposite surface of the wall exposed to a surrounding environment. The outermost layers serve as radiation shields to reduce heat transfer from the surrounding environment to the wall, and from the wall to the hydrocarbon fluid.

Method and coating system for reducing carbonaceous deposits on surfaces exposed to hydrocarbon fuels at elevated temperatures

A high temperature gas turbine component for use in the gas flow path that comprises a specular optical reflector coating system. A thin specular optical reflector coating system is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. The thin reflector coating system comprises a thin high temperature and corrosion resistant refractory stabilizing layer, which is applied over a thin reflective metal layer, which is applied over a thin high temperature and corrosion resistant refractory sealing layer. The coating system is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The coating system reflects radiation back into the hot gas flow path or into the atmosphere. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path or sent to the atmosphere rather than absorbed into a component that only serves to increase the temperature of such a component.

Optical reflector for reducing radiation heat transfer to hot engine parts

A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine. The method comprises coupling a semi-permeable membrane to the engine adjacent an outer surface of the engine, coupling a fluid reservoir to the aircraft engine in flow communication with the semi-permeable membrane, and supplying fluid from the fluid reservoir to the semi-permeable membrane to facilitate preventing ice accumulation on the aircraft engine outer surface.

Methods for operating gas turbine engines

A process for depositing pure platinum on a substrate is disclosed. In accordance with one embodiment, the process comprises applying a solution consisting of Pt(acetylacetonate)and ethanol or acetone onto a substrate and wrapping at least a portion of the substrate with aluminum foil. The process further comprises heating the substrate wrapped with the aluminum foil to about 300&#xb0; C. at a rate of about 10&#x2013;25&#xb0; C. per minute and then holding at about 300&#xb0; C. for about 1 hour, wherein the Pt(acetylacetonate)decomposes to deposit pure platinum on the substrate.

Platinum coating process

A method for applying a coating system that is applied to a surface of a component for preventing or at least substantially preventing interdiffusion between the component surface and a protective thermal layer applied to the component surface when the thermal layer is exposed to elevated temperatures. The method includes applying a carrier layer containing aluminum to the component surface. Next, the layer is heated to a first predetermined temperature for a first predetermined period of time in the substantial absence of oxygen to bond the aluminum with the component surface, the heat dissolving the carrier portion of the aluminum layer. The remaining portion of the aluminum layer is then heated to a second predetermined temperature for a second predetermined period of time to form an oxidized aluminum layer. Finally, at least one protective thermal layer is applied over the oxidized aluminum layer.

Method for applying a coating system including a heat rejection layer to a substrate surface of a component

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Laramie, WY, United States of America

John Frederick Ackerman