General Electric Company

John Frederick Ackermann

Paul Vincent Arszman

Bangalore Aswatha Nagaraj

Craig Douglas Young

Nicole Justis

Andrew Jay Skoog

William Randolph Stowell

Randy Lee Lewis

Paul V Arszman

Nicole Barbara Justis

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 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 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 process for carrying out chemical reactions in the gas phase or gas-liquid phase comprises feeding the chemical reagents under pressure into the combustion chamber of a turbine engine, where they react to form a desired chemical product. The heat energy evolved in the process can be utilized through the action of the turbine to power auxiliary equipment attached to the turbine engine, such as an electrical generator. In another embodiment, the turbine engine is utilized to carry out at least two reactions: a primary reaction which occurs in the combustion chamber of the engine, and a second reaction which occurs in an augmentor-section of the engine, utilizing the product of the primary reaction as a reagent in the production of a final product.

Growing community of inventors

Laramie, WY, United States of America

John Frederick Ackermann