General Electric Company

Other

William Randolph Stowell

John Frederick Ackerman

Andrew Jay Skoog

Jane Ann Murphy

Thomas Walter Rentz

Ching-Pang Lee

Daniel Peter Ivkovich, Jr

Bangalore Aswatha Nagaraj

Robert Alan Johnson

George A Coffinberry

Joseph Thomas Begovich

Dainel P Ivkovich, Jr

Alfred Albert Mancini

Jeffrey Allen Conner

Raymond Grant Rowe

Adrian M Beltran

John Herbert Wood

Kevin Richard Leamy

Tara Easter McGovern

Bryan Thomas Bojanowski

Gregory Vincent Meholic

David Elson Caldwell

Michael R Steele

Darrell Glenn Senile

Rajasingh Schwartz Israel

John Ellington Greene

Thomas Froats Broderick

Antonio Frank Maricocchi

John Matthew Powers

George A Durgin

John Douglas Evans, Sr

Paul Thomas Marks

Randy Lee Lewis

Sang Yeng Park

John Frederick Ackermann

George E Cook

Glen Arthur MacMillan

Robert W Harris

Timothy Ray Lattire

Timothy Lance Manning

Terry James Kent

Lisa DeBellis

Aaron Dennis Gastrich

James Hayward Clare

David E Caldwell

Dan Ivkovich

Soon Jai Khang

Mathew Curtis Roling

Glenn E Varney

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

A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating.

Methods and apparatus for coating gas turbine engines

Methods are provided for producing large volumes of small antenna arrays. In one embodiment, the method comprises the steps of creating an antenna array pattern as a computer file, printing the created pattern onto the surface of a suitable transfer paper, placing the printed image surface in contact with the surface of a material to be etched, and transferring the printed image to the surface of the material to be etched. The transfer can be effected by any combination of chemicals, heat, and/or pressure. After transfer of the printed image, the transfer paper is removed. The step of removing the transfer paper optionally includes wetting the transfer paper in a manner that dissolves the transfer paper leaving the printed antenna pattern on the surface of the material to be etched. The method further includes the step of etching the non-printed portions of the material, preferably by chemical etching, and removing the printed pattern from the surface of the material to yield an antenna array comprising a non-etched portion of the substrate surface. Arrays, and substrates having an etch-resistant mask for making the arrays, are also provided.

Low cost antenna array fabrication technology

A chemical composition and method for repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating on a component that has suffered localized damage to the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a paste-like mixture of a ceramic composition comprising ceramic powders and nano-sized ceramic materials in a binder, further including an accelerant, is applied to the surface area of the component, and is optionally smoothed using mechanical means. The composition is then allowed to dry and cure to form a dried coating having polymeric characteristics. Upon subsequent heating, the dried coating reacts to produce a glassy ceramic repair coating. Due to the thixotropic properties of the coating composition upon application to a component, the repair method can be performed in-situ while the component remains installed in its operating environment.

Field repairable high temperature smooth wear coating

An optical coating is applied to an article surface of an article by providing a deposition substrate other than the article surface, wherein the deposition substrate is made of a removable material. The optical coating is thereafter deposited onto the deposition substrate. The optical coating is thereafter transferred to the article surface using a transfer support, which may be the deposition substrate or may be a different piece. The method includes thereafter affixing the optical coating to the article surface, and thereafter removing the transfer support.

Method for applying an optical coating to a surface of an article

A method for forming a ceramic layer on the surface of a turbine component. This method comprises the following steps: (a) providing a turbine component having a surface; (b) providing at least one ceramic tape overlaying the component surface; and (c) manually pressing the at least one ceramic tape against the component surface at a temperature of from about 150&#xb0; to about 700&#xb0; F. (from about 66&#xb0; to about 371&#xb0; C.) so as to cause the at least one ceramic tape to adhere to the component surface.

Method of forming ceramic layer

A chemical composition and method for repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating on a component that has suffered localized damage to the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a paste-like mixture of a ceramic composition comprising ceramic powders and nano-sized ceramic materials in a binder is applied to the surface area of the component, and is optionally smoothed using mechanical means. The composition is then allowed to dry and cure to form a dried coating having polymeric characteristics. Upon subsequent heating, the dried coating reacts to produce a glassy ceramic repair coating. Due to the thixotropic properties of the coating composition upon application to a component, the repair method can be performed in-situ while the component remains installed in its operating environment.

An optical coating is applied to an article surface of an article by applying a first release system to a deposition substrate, and depositing the optical coating onto the deposition substrate. A second release system and transfer substrate is applied to the second face of the optical coating. The first release system is dissolvable in a first-release-coating solvent that does not dissolve the second release system. The first release system is dissolved in the first-release-coating solvent that does not dissolve the second release system, to separate the optical coating from the deposition substrate. The first face of the optical coating is affixed to the article surface, and the transfer substrate is separated from the optical coating. Any of a variety of affixing techniques may be used.

Method of applying an optical coating to an article surface

A coating and method for overcoating a TBC on a component used in a high-temperature environment, such as the combustor section of an industrial gas turbine. The coating defines the outermost surface of the component and is formed of at least two layers having different compositions. An inner layer of the coating contains alumina in a first silica-containing matrix material that is free of zinc titanate. An outer layer of the coating contains alumina, a glass material, and zinc titanate in a second silica-containing matrix material. The outer layer of the coating has a surface roughness of not greater than three micrometers Ra and forms the outermost surface of the component. The coating reduces the component temperature by reducing the convective and radiant heat transfer thereto.

Smooth outer coating for combustor components and coating method therefor

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 thermal barrier coating for an underlying metal substrate of articles that operate at, or are exposed to, high temperatures, as well as being exposed to environmental contaminant compositions. This coating includes an inner layer nearest to the underlying metal substrate comprising a ceramic thermal barrier coating material, as well as an outer layer having an exposed surface and comprising tantalum oxide in an amount sufficient to protect the thermal barrier coating at least partially against environmental contaminants that become deposited on the exposed surface and optionally an intermediate layer between the inner and outer layers comprising alumina. This coating can be used to provide a thermally protected article having a metal substrate and optionally a bond coat layer adjacent to and overlaying the metal substrate. The thermal barrier coating can be prepared by forming the inner layer comprising the ceramic thermal barrier material, optionally forming the intermediate layer comprising the alumina over the inner layer, and then forming the outer layer comprising the tantalum oxide over the intermediate (inner) layer.

Thermal barrier coating protected by tantalum oxide and method for preparing same

A method of repairing a thermal barrier coating () on a component () designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating () on a component () that has suffered localized spallation () of the thermal barrier coating (). After cleaning the surface area () of the component () exposed by the localized spallation (), a ceramic paste () comprising a ceramic powder in a binder is applied to the surface area () of the component (). The binder is then reacted to yield a ceramic-containing repair coating () that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating () has a ceramic matrix. The repair method can be performed while the component () remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.

Component with repaired thermal barrier coating

A chemical composition and method for repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method repairs a thermal barrier coating on a component that has suffered localized damage to the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a mixture of a ceramic composition comprising a ceramic powder in a binder is applied, preferably by spraying, to the surface area of the component. The binder is then allowed to dry to form a dried coating. Upon subsequent heating, the dried coating reacts to produce a ceramic-containing repair coating, wherein the coating comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic. The repair method can be performed while the component remains installed, e.g., in a gas turbine engine. The chemical composition is a liquid mixture that comprises ceramic material in at least two particle size ranges, as well as a nano-sized ceramic material and a binder that imparts thixotropic properties to the coating composition upon application to a component.

A coating system and method for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to the walls of a containment article. Of particular concern are carbonaceous deposits that form at temperatures below about 650&deg; F. (about 345&deg; C.). The coating system combines an outermost layer of platinum with a ceramic barrier layer. The coating system has been shown to significantly reduce the formation of carbonaceous deposits at temperatures between about 220&deg; F. and 650&deg; F. (about 105&deg; C. to about 345&deg; C.), as well as reduce the adhesion of such deposits. The platinum outermost layer also serves as a radiation shield to reduce heat transfer from the containment article to the hydrocarbon fluid. The outermost layer is preferably deposited as an extremely thin film by chemical vapor deposition. The barrier layer is deposited to a thickness sufficient to prevent interdiffusion of the platinum outermost layer with the containment wall.

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Rising Sun, IN, United States of America

William Randolph Stowell