General Electric Company

Paul Vincent Arszman

John Frederick Ackerman

Andrew Jay Skoog

John Frederick Ackermann

Bangalore Aswatha Nagaraj

Nicole Justis

Craig Douglas Young

Jane Ann Murphy

Bryan Thomas Bojanowski

Timothy Ray Lattire

Nicole Barbara Justis

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 high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector 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. A thin layer of the high temperature reflector the 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 high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody. The surface 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 wall that only serves to increase the temperature of the wall.

High temperature centerbody for temperature reduction by optical reflection and process for manufacturing

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

A high temperature splash plate for use in the combustor of a gas turbine engine that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the surface of the splash plate 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. A thin layer of the high temperature reflector then 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 surface reflects radiation in the direction of the turbine back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component. The design of the splash plate is such that the radiation is not directed to an adjacent component, which only serves to increase the temperature of the wall of the component.

High temperature splash plate for temperature reduction by optical reflection and process for manufacturing

A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the flow path surface 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. A thin layer of the high temperature reflector then 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 high temperature reflector can be applied to any surface aft of the compressor, such as on a combustor wall. The surface reflects radiation back into the hot gas flow path. 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 rather than absorbed into a component wall which only serves to increase the temperature of the wall.

High temperature combustor wall for temperature reduction by optical reflection and process for manufacturing

A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector 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. A thin layer of the high temperature reflector the 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 high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path. 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 rather than absorbed into a component wall that only serves to increase the temperature of the wall.

High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing

A low cost aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.

Low cost aluminide process for moderate temperature applications

A method for applying a coating system that is applied to a surface of a component for preventing or at least substantially preventing interdiffision 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.

Afterburner seals with heat rejection coats

Combustion liner with heat rejection coats

A low cost chromide and chromide/aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally chromium or chromium and aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.

Low cost chrome and chrome/aluminide process for moderate temperature applications

A method for applying a coating system that is applied to a surface of a component, such as a turbine nozzle, 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.

Turbine nozzle with heat rejection coats

A heat-rejection coating is applied to a metallic component of a gas turbine engine, preferably made of a nickel-base superalloy. A component surface is preferably pre-treated, as by polishing the component surface, thereafter pre-oxidizing the component surface, and thereafter applying a ceramic barrier coating onto the component surface. A reflective-coating mixture is air sprayed onto the pre-treated component surface. The reflective-coating mixture includes a metallic pigment, such as platinum, gold, palladium, and alloys thereof, and a reflective-coating-mixture carrier. The component with the reflective-coating mixture sprayed thereon is fired.

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Cincinnati, OH, United States of America

Paul Vincent Arszman