General Electric Company

Other

Raymond Grant Rowe

Melvin Robert Jackson

Donald George LaChapelle

David William Skelly

Paul Stuart Wilson

Andrew Jay Skoog

William Randolph Stowell

Jane Ann Murphy

Tara Easter McGovern

Bruce Alan Knudsen

Robert John Zabala

Peter Joel Meschter

Alan Michael Iversen

Scott Andrew Weaver

Thomas Walter Rentz

Fernando Jorge Casanova

Paul Thomas Marks

Daniel Peter Ivkovich, Jr

San-Dar Gau

Timothy Lance Manning

Gary T Martini

Rebecca Louise Casey

Lisa DeBellis

James Hayward Clare

Francis X Gigliotti, Jr

Lawrence J Galaske, Jr

Mathew Curtis Roling

Richard Michael Robinson

Alan M Iverson

Gerald E Wasielewski, Deceased

Mark A Robinson

Douglas J White

A coating system on a superalloy or silicon-containing substrate of an article exposed to high temperatures. The coating system includes a coating layer that overlies the substrate and is susceptible to hot corrosion promoted by molten salt impurities. A corrosion barrier coating overlies the coating layer and contains at least one rare-earth oxide-containing compound that reacts with the molten salt impurities to form a dense, protective byproduct barrier layer.

Hot corrosion-resistant coatings and components protected therewith

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

A method for metallurgically bonding a stator bar to a coupling to reduce the incidence of leak paths resulting from corrosion. The stator bar comprises strands through which a liquid coolant can flow. Adjacent ends of the strands are received in an interior cavity of the coupling through an opening in the coupling. A joining material is provided on a first portion of the stator bar within the coupling opening and adjacent the ends of the strands. The first portion is heated to melt the joining material. At essentially the same time, a second portion of the stator bar outside the coupling is also heated. Once the joining material is suitably molten, the first portion is allowed to cool while the second portion remains heated, thereby causing the joining material nearest the ends of the strands to solidify first.

Method of metallurgically bonding a stator bar

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 method includes blasting the interior surfaces of the fitting to stator bar strand joint with COpellets to remove loose copper oxide which otherwise would interfere with proper sealing between an epoxy and the copper surfaces of the joint. After cleaning the surfaces and applying air under pressure to remove particulate material, epoxy is applied to the brazed joints followed by an evacuation of the fitting to strand joint. Subsequent release of the vacuum ensures that the epoxy fills in all crevices or cracks at the joint surfaces and minimizes or eliminates any tendency of the epoxy to delaminate.

Methods and systems for sealing liquid cooled stator bar end connections for a generator

A compressor forward stub shaft comprising a plurality of axially spaced, annular rows of dovetail grooves, at least a first and a second of the plurality of rows having dovetail slots coated in part with an anti-wear coating.

Coated forward stub shaft dovetail slot

Method of brazing a liquid-cooled stator bar

A method is disclosed to dissolve cupric oxide (CuO) deposits on a strainer in a stator water cooling system (SWCS) of an industrial electrical power generator. The method injects carbon dioxide (CO ) into the coolant to increase the CuO solubility of the coolant. By increasing the solubility, the CuO level in the coolant is less than saturated. The unsaturated coolant dissolves the CuO deposits on the strainer.

Method for treating stator cooling water to prevent clogging of strainer in the cooling system of an industrial electrical generator

The present invention provides a method of removing copper oxide deposits from stator water cooling system piping material surfaces. The present invention disconnects the generator from the stator water cooling system, connects bridging piping to the stator water cooling system at the points from which the generator was disconnected to allow the stator water cooling system to operate without the generator, provides a sufficient amount of an aqueous solution of an agent which dissolves or removes copper oxide deposits from piping material surfaces for a time sufficient to dissolve or remove substantially all copper oxide deposits, and rinses the piping material surfaces with sufficient water until the output water from the rinsing of the piping material surfaces is essentially neutral.

Piping deposit removal from stator water cooling systems

An introduction system for introducing an atmosphere into an interior of an autoclave alters an existing atmosphere. The introduction system comprises at least one source of actuating gas; an actuating mechanism, a pressure barrier that separates an interior of the autoclave from ambient exterior atmosphere; and a containment vessel that is located at least partially in the interior of the autoclave. The containment vessel comprises a plurality of walls, at least one of the walls comprising a release wall structure of the containment vessel, a vapor producing material cavity, where the walls define the vapor producing material cavity; and an opening element. The opening element is movable by the opening actuator device. The release wall structure of the containment vessel is rapidly opened by the opening element to effect a rapid release of vapor producing material in the vapor producing material cavity into the interior of the autoclave. The autoclave is provided with at least an increased pressure, so a rapid release of vapor producing material in the vapor producing material cavity into the interior of the autoclave causes the vapor producing material to vaporize into a vapor, thus altering an atmosphere in the autoclave. The actuating mechanism comprises an opening actuator device. The at least one source of actuating gas in communication with the opening actuator device and flow from the at least one source of actuating gas is controlled by a control device.

Device to alter an atmosphere in an autoclave

A double wall hot gas path part for turbines, such as an airfoil, combustor, duct or shroud, comprises an outer skin and an inner support wall that are metallurgically bonded to one another. The double wall contains integral channels for passage of cooling air adjacent to the skin. The skin may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures. Microlaminate composites typically have a lower density than that of the material used for the support wall, and a simplified internal geometry, which promote weight reductions in the parts and increases in engine operating efficiency.

Double wall turbine parts

A method for making double-wall airfoil for applications such as the blades and vanes of gas turbine engines by depositing an airfoil skin over an inner support wall which is separately formed and contains channels filled by a channel filling means. The channel filling means is removed thereby forming integral channels within the double-wall for circulating a cooling gas adjacent to the airfoil skin. The airfoil skin deposited may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures.

Method for making a double-wall airfoil

A double-wall airfoil for applications such as the blades and vanes of gas turbine engines. The double-wall comprises an outer airfoil skin and an inner support wall that are metallurgically bonded to one another. The double-wall contains integral channels for passage of cooling air adjacent to the airfoil skin. Airfoil skin may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures. Microlaminate composites typically have a lower density than that of the material used for the airfoil support wall, and a simplified internal geometry which promote weight reductions in the airfoils and increases in engine operating efficiency.

Double-wall airfoil

An improved method for forming fluid inflatable metal structures is taught. The improvement concerns the patterning of the portion of the structure to be inflated. Patterning is accomplished by first applying a strippable flexible mask coating and then scoring this coating so that a patterned portion may be removed therefrom. The parent portion is the portion of the sheet article to be inflated by subsequent processing. After the patterned portion has been removed, a stop-off is applied to the exposed surface of the first sheet. After the stop-off material has been applied, the remainder of the strippable mask is removed and washed with a detergent to remove the residue from the mask. The sheet having stop-off applied in the pattern to the first sheet is then superposed over a second sheet, and heat and pressure are applied to cause diffusion bonding between the exposed surfaces of the two sheets. Following this bonding, the portion of the sheet carrying the stop-off is inflated to give the article its final configuration.

Strippable mask patterning of stop-off for diffusion bond processing

An improved method for superplastic forming diffusion bonding includes application of a protective encapsulating coating over the stop-off coating to prevent migration of yttria into regions to be diffusion bond.

Growing community of inventors

Niskayuna, NY, United States of America

Raymond Grant Rowe