Paul V Arszman

US Patent:

6884460, Apr 26, 2005

Filed:

Dec 20, 2002

Appl. No.:

10/324704

Inventors:

John Frederick Ackerman - Laramie WY, US
Paul Arszman - Cincinnati OH, US
Andrew J. Skoog - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D001/38
B05D003/04
B05D007/14

US Classification:

427229, 427226, 4273764, 4273766, 427377, 427380, 427405, 4274192, 4274193

Abstract:

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.

US Patent:

6884461, Apr 26, 2005

Filed:

Dec 20, 2002

Appl. No.:

10/325000

Inventors:

John Frederick Ackerman - Laramie WY, US
Paul Arszman - Cincinnati OH, US
Andrew J. Skoog - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D001/38
B05D003/04
B05D007/14

US Classification:

427229, 427226, 4273764, 4273766, 427377, 427380, 427405, 4274192, 4274193

Abstract:

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.

US Patent:

6884515, Apr 26, 2005

Filed:

Dec 20, 2002

Appl. No.:

10/324550

Inventors:

John Frederick Ackerman - Laramie WY, US
Paul Arszman - Cincinnati OH, US
Andrew J. Skoog - Wester Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B015/04
F03B003/12

US Classification:

428469, 428697, 428699, 428701, 428702, 4284722, 416241 R

Abstract:

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.

US Patent:

6884524, Apr 26, 2005

Filed:

Dec 27, 2002

Appl. No.:

10/330702

Inventors:

John F. Ackermann - Laramie WY, US
Paul V. Arszman - Cincinnati OH, US
Andrew J. Skoog - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B015/00
B05D003/02

US Classification:

428650, 428651, 428666, 4273741, 4273768, 427380, 4273837, 427405, 4274191

Abstract:

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.

US Patent:

6893737, May 17, 2005

Filed:

Dec 27, 2002

Appl. No.:

10/331054

Inventors:

John F. Ackermann - Laramie WY, US
Paul V. Arszman - Cincinnati OH, US
Andrew J. Skoog - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B015/00
B32B015/20
B05D003/02
B05D001/36

US Classification:

428650, 428651, 428680, 4273761, 4273766, 4273768, 4273741, 4273831, 4273837, 427379, 427380, 427404, 427405, 4274191, 4274192

Abstract:

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.

US Patent:

6925811, Aug 9, 2005

Filed:

Dec 31, 2002

Appl. No.:

10/335442

Inventors:

Nicole Justis - San Diego CA, US
John F. Ackermann - Laramie WY, US
Paul V. Arszman - Cincinnati OH, US
Bangalore A. Nagaraj - West Chester OH, US
Craig D. Young - Maineville OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23M005/00

US Classification:

60753, 428622

Abstract:

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.

US Patent:

6926496, Aug 9, 2005

Filed:

Dec 31, 2002

Appl. No.:

10/335486

Inventors:

John F. Ackermann - Laramie WY, US
Paul V. Arszman - Cincinnati OH, US
Bangalore A. Nagaraj - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D009/02

US Classification:

415191, 415200, 416241 B

Abstract:

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.

US Patent:

7003959, Feb 28, 2006

Filed:

Dec 31, 2002

Appl. No.:

10/335657

Inventors:

John F. Ackermann - Laramie WY, US
Paul V. Arszman - Cincinnati OH, US
Bangalore A. Nagaraj - West Chester OH, US
Craig D. Young - Maineville OH, US
Nicole Justis - San Diego CA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F23M 5/00

US Classification:

60753, 428622

Abstract:

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.