Jane A Murphy

US Patent:

6413578, Jul 2, 2002

Filed:

Oct 12, 2000

Appl. No.:

09/687721

Inventors:

William R. Stowell - Rising Sun IN
Robert A. Johnson - Simpsonville SC
Andrew J. Skoog - West Chester OH
Joseph Thomas Begovich - West Chester OH
Thomas Walter Rentz - Cincinnati OH
Jane Ann Murphy - Middletown OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 106

US Classification:

427142, 427140, 427201, 427226, 427446, 427453

Abstract:

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.

US Patent:

6465090, Oct 15, 2002

Filed:

Oct 17, 2000

Appl. No.:

09/690860

Inventors:

William R. Stowell - Rising Sun IN
Joseph Thomas Begovich - West Chester OH
Thomas Walter Rentz - Cincinnati OH
Glen A. MacMillan - Simpsonville SC
John Greene - Simpsonsville SC
Jane Ann Murphy - Middletown OH
Andrew J. Skoog - West Chester OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B 312

US Classification:

428325, 428323, 428332, 428469, 428450, 428699, 428702, 416241 B

Abstract:

A protective coating and coating method for protecting a thermal barrier coating (TBC) on a component, such as a component of a gas turbine engine. The protective coating comprises alumina particles in a silica-containing matrix, and may be substantially homogeneous or formed of multiple layers having different compositions. The composition and relative amounts of alumina and matrix material in the protective coating enable the coating to react with molten compounds containing calcia, magnesia, alumina and/or silica (CMAS), forming a compound with a melting temperature that is significantly higher than CMAS. As such, infiltration of molten CMAS into the TBC is significantly reduced or entirely avoided.

US Patent:

6485590, Nov 26, 2002

Filed:

Oct 4, 2000

Appl. No.:

09/679656

Inventors:

Andrew J. Skoog - West Chester OH
Jane A. Murphy - Middletown OH
Thomas W. Rentz - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B 3120

US Classification:

156 8911, 156 8923, 123 1 R, 244 35 R

Abstract:

A method of forming a multilayer ceramic coating system on a substrate that requires thermal protection from a hostile thermal environment. The method generally entails forming at least one tape that contains ceramic particles dispersed in an organic constituent, such as a binder and/or plasticizer. If a single tape is used, the tape is formed of multiple layers of different compositions and applied as a unit to the substrate, thereby forming at least an innermost layer and an outermost layer on the substrate. If multiple tapes are used, a first tape is applied to the substrate to form the innermost layer, and a second tape is applied to form the outermost layer. The tape/tapes are then sintered to form innermost and outermost ceramic layers, respectively, on the substrate. The tape/tapes are formed and processed such that the innermost ceramic layer has submicron voids to provide a desired level of porosity, while the outermost ceramic layer is thinner, smoother and less porous than the innermost ceramic layer.

US Patent:

6649256, Nov 18, 2003

Filed:

Jan 24, 2000

Appl. No.:

09/489717

Inventors:

Matthew B. Buczek - Fairfield OH
Andrew J. Skoog - West Chester OH
Jane A. Murphy - Middletown OH
Daniel G. Backman - Melrose MA
Israel S. Jacobs - Schenectady NY
John F. Ackerman - Laramie WY

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B 516

US Classification:

428323, 428328, 428329, 428330, 428338, 428413, 428492, 428 31, 427547

Abstract:

Non-spherical particles including a major dimension, for example flakes of material, are positioned with the major dimension oriented generally along an article surface in respect to which the particle is disposed. The particles, disposed in a fluid medium, the viscosity of which can be increased to secure the particles in position, are positioned using a force on the particles. The force includes torque force from a magnetic field, force from flow of the fluid medium, the force of gravity, and the force of surface tension alone or in combination with the force of gravity.

US Patent:

6663918, Dec 16, 2003

Filed:

May 11, 2001

Appl. No.:

09/853228

Inventors:

Timothy Lance Manning - New Richmond OH
Timothy Ray Lattire - Sunman IN
Michael Dwayne Rutter - West Chester OH
Andrew Jay Skoog - West Chester OH
Jane Ann Murphy - Middletown OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 102

US Classification:

427421, 427256, 427287

Abstract:

A differential thickness pattern can be induced in a coating that is sprayed on an aircraft engine part using a robotic system. The robotic system includes a spray mechanism with a triggering device to spray the coating on the aircraft engine part and a controller. The controller is used to move the spray mechanism along a predetermined path and to activate and deactivate the triggering device. To obtain the differential thickness pattern, a predetermined profile of the aircraft engine part corresponding to areas of the aircraft engine part requiring a thicker coating is integrated into a control program used by the controller. The controller uses the control program to activate and deactivate the triggering mechanism to limit the spraying of the coating to only those areas of the part in the predetermined profile to obtain a different coating thickness.

US Patent:

6720034, Apr 13, 2004

Filed:

Apr 23, 2002

Appl. No.:

10/131518

Inventors:

Andrew Jay Skoog - West Chester OH
Jane Ann Murphy - Franklin OH
John Frederick Ackerman - Laramie WY
Paul Vincent Arszman - Cincinnati OH
Bryan Thomas Bojanowski - Cincinnati OH
Timothy Ray Lattire - Sunman IN

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 136

US Classification:

4274191, 427402, 4274192, 427421, 427427, 427429, 4273761, 4273762, 4273766, 4273833, 4273835, 4273837, 427327

Abstract:

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.

US Patent:

6827969, Dec 7, 2004

Filed:

Dec 12, 2003

Appl. No.:

10/735359

Inventors:

Andrew Jay Skoog - West Chester OH
Jane Ann Murphy - Franklin OH
William Randolph Stowell - Rising Sun IN
Timothy Ray Lattire - Sunman IN

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05D 102

US Classification:

427142, 427140, 427226, 427230, 427236, 427239, 427299, 427327, 4273722, 4273977, 427402, 427403, 4274191, 4274192, 427421, 427427, 427429

Abstract:

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.

US Patent:

6919121, Jul 19, 2005

Filed:

May 23, 2002

Appl. No.:

10/153929

Inventors:

William R. Stowell - Rising Sun IN, US
Robert A. Johnson - Simpsonville SC, US
Andrew J. Skoog - West Chester OH, US
Joseph Thomas Begovich - West Chester OH, US
Thomas Walter Rentz - Cincinnati OH, US
Jane Ann Murphy - Middletown OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B32B035/00

US Classification:

428161, 428 63, 428156, 428323, 428325

Abstract:

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.