United Technologies Corporation

International Fuel Cells, LLC

United States of America As Represented by the Secretary of the Air Force

Sudhangshu Bose

Richard D Breault

James Thompson Beals

David A Litton

Michael J Maloney

Dinesh K Gupta

Daniel A Bales

Nicholas E Ulion

Michael E Gorman

Steven M Burns

Alan David Cetel

Mark T Ucasz

Tyrus E Royal

Merritt W Wight

Jeanine T Marcin

Dilip M Shah

Carl R Verner

Peter J Draghi

David A Rutz

Keith A Santeler

Norman Pietruska

James J Moor

Daniel F Paulonis

Stephen Douglas Murray

John J Marcin

Joshua E Persky

Glenn A Cotnoir

Jacob A Snyder

John D Wiedemer

Raymond P Ristau

John Donahue

John H Hughes

Nicole Sullivan

Jeanine D Marcin

Venkat Seetharaman

Shiela R Woodward

Stephen D Murray

Keith Santeler

Repair methods involving conductive heat resistance welding includes repairing a crack of a gas turbine engine component using a conductive heat resistance welding technique and a welding technique other than conductive heat resistance welding.

Repair methods involving conductive heat resistance welding

A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.

Refractory metal core coatings

The present invention relates to an overlay coating which has improved strength properties. The overlay coating comprises a deposited layer of MCrAlY material containing discrete nitride particles therein. The nitride particles are present in a volume fraction in the range of 0.1% to 15.0% and have a particle size in the range of from 0.1 microns to 10.0 microns. The coating may also have oxide particles dispersed therein.

Thermal barrier coating utilizing a dispersion strengthened metallic bond coat

A method and apparatus are provided for inspecting a coated substrate such as a multi-layer coating on a substrate of a turbine airfoil. At each of a number of locations along the airfoil a number of frequencies of alternating current are passed through the airfoil. At least one impedance parameter is measured. The measured impedance parameters are utilized to determine a condition of the coating.

Nondestructive, electrical impedance-based, thermal barrier coating inspection

A method of surface cleaning and controlled oxidation of superalloys is described. The method provides a thin homogeneous layer of relatively pure alpha alumina which is suited to receive and adhere to a subsequent vapor deposited coating.

Surface preparation process for deposition of ceramic coating

The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.

Method for repairing turbine engine components

The present invention relates to high temperature composite materials formed from nano-sized powders suitable for use in the manufacture of jet engine components. The composite materials consist essentially of a matrix formed from a powdered material having a particle size in the range of from about 1 to about 100 nanometers and a plurality of reinforcing fibers embedded within the matrix and comprising from about 20% to about 40% by volume of the composite material. The method of manufacturing the composite materials broadly comprises the steps of mixing the powdered material with the reinforcing fibers and consolidating the mixture to form the composite material.

High temperature composite material formed from nanostructured powders

A thermal barrier coating system for a superalloy substrate is disclosed. The superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate, so that a portion of the substrate remains exposed. The localized area is defined to be the area(s) at which a TBC typically fails first, e.g., the leading and trailing edges of an airfoil, or other area. An alumina layer is formed on the remaining portion of the substrate, and also on the bond coat. A ceramic layer is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate at which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.

Thermal barrier coating system utilizing localized bond coat and article having the same

An uncooled turbine outer air is comprised of a combination of monolithic ceramics with high temperature capability and oxidation and creep resistance, and a fiber reinforced ceramic composite with high fracture toughness. In a preferred embodiment of the invention, a fiber reinforced ceramic composite of silicon carbide and aluminum borosilicate is infiltrated by chemically vapor deposited silicon carbide. The infiltration process is continued until the composite develops a monolithic layer of silicon carbide. An additional layer is deposited on the monolithic ceramic to provide additional thermal protection.

Outer air seal for a gas turbine engine

A porous substrate of a fuel cell electrode assembly is formed by producing a fibrous carbon precursor web by means of a conventional wet paper-making process. The precursor web is then dried and saturated with a wet resinous binder which will carbonize when heated. Substantially the entirety of all of the carbon fibers in the web are thus coated with the binder, and substantially all of the inter-fiber junctures in the web will also be coated with the binder. The saturated web is then dried, and heat treated to convert the binder to a glassy carbon which exhibits superior resistance to corrosion.

Method of making a final cell electrode assembly substrate

Corrosion resistant fuel cell substrates

A method for making a carbon-graphite component, such as a fuel cell substrate, suited for use in an electrochemical cell includes forming a precursor sheet structure comprising a resin, fibers that are graphitizable, and an inorganic compound containing boron and oxygen. Various details of the method are developed that effect the carbon yield of cellulose fibers used for the precursor sheet and the thermal and the electrical conductivity of the component. In one embodiment, the inorganic compound of boron and oxygen is boric acid.

Carbon graphite component for an electrochemical cell and method for

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Manchester, CT, United States of America

Sudhangshu Bose