Abstract: A composite article includes a substrate, a ceramic member on the substrate and a ceramic bond coat for securing the substrate and the ceramic member together. A method of securing the ceramic member and the substrate together includes pyrolyzing a ceramic precursor, such as a ceramic powder, between the substrate and the ceramic member to form the ceramic bond coat.

Abstract: A method of coating a turbine engine component involves providing the turbine engine component with a first area and a second area. The first area neighbors the second area. A cover is disposed over the first area of the turbine engine component. The second area of the turbine engine component is coated with a first coating curable from exposure to a light. The second area of the turbine engine component is exposed to light resulting in the curing of the first coating. The cover is removed from the first area. The first area of the turbine engine component is then sprayed with a second coating different from the first coating.

Abstract: A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase.

Abstract: The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.

Abstract: Methods for repairing gas turbines are provided. A representative method includes: identifying an affected area of a surface of a component of the gas turbine, the surface of the component defining a portion of a gas flow path through the gas turbine; applying an epoxy-based filler to the affected area; curing the epoxy-based filler; and blending the epoxy-based filler with the surface of the component.

Abstract: A tool for assembling and disassembling a plasma spray gun comprises a first removal and installation head, including a body, a drive socket and first and second prongs, which are spaced to mate with corresponding sockets disposed in a first plasma spray gun component, such as a cathode holder. In addition, the tool may comprise a second removal and installation head, including a body and first and second prongs, which are spaced to mate with corresponding sockets disposed in a second plasma spray gun component, such as a locking ring. The second removal and installation head is configured to attach to the first removal and installation head. The tool is ergonomically designed and easily allows the removal and/or installation of plasma spray gun components.

Abstract: A bond coat is applied to a substrate of a gas turbine engine component the component. A barrier coat is applied atop the bond coat. The applying of the bond coat includes: applying a first layer having an as-applied first roughness; and applying a second layer atop the first layer, the second layer having an as-applied second roughness, greater than the first roughness. In the resulting coating system, the first and second layers may have different properties (e.g., greater porosity, pore size, and/or splat size for the second layer).

Abstract: A method of cleaning a carbon work piece includes the step of applying an acetone cleaning agent to the carbon work piece to remove debris therefrom. The removal of debris promotes adhesion between the carbon work piece and a subsequently applied coating. For example, other steps may precede the acetone cleaning step, such as submersing the carbon work piece in deionized water. In one example, a subsequent coating process deposits an alumina coating on the carbon work piece.

Abstract: This invention is a fiber-reinforced ceramic matrix composite and a method for their fabrication. The precursors of the ceramic matrix phase are impregnated into the fibrous preform or-applied to the surface of the fiber as fluids. The preform or fibers are then thermally processed to convert the precursor compounds to the desired refractory materials, e.g., carbides, borides, or nitrides. The density and other properties of the composites may be enhanced further by using a hybrid process that combines fluid infiltration and thermal treatment with chemical vapor infiltration.

Abstract: Ceramic metal oxide fibers are made by intercalating graphitic graphite fibers with a mixture of metal chlorides and then heating the intercalated fibers to oxidize or burn off the carbon leaving a metal oxide fiber having generally the shape and structure of the graphite fiber precursors to make composite fibers, such as binary fibers of aluminum oxide-zirconium oxide and aluminum oxide-ferric oxide.

Abstract: Lanthanum sulfide is maintained in the stable cubic phase form over a temperature range of from 500.degree. C. to 1500.degree. C. by adding to it small amounts of calcium, barium, or strontium. This novel compound is an excellent thermoelectric material.

Abstract: Coated nuclear fuel particles are made by first pyrolytically depositing low density carbon onto fuel cores and thereafter depositing a fission-product retentive, higher density exterior coating. In the improvement, cores of uranium, thorium or plutonium oxides are coated by co-depositing silicon carbide or zirconium carbide along with the low density pyrocarbon to create a uniform dispersion. Silicon or zirconium is deposited in an amount equal to at least about one atom for each fission anticipated during the fuel lifetime.

Abstract: Carbon-graphite fibers are coated with a protective metal oxide coating by intercalating the fibers with a metal chloride and then deintercalating the chlorine by hydrolysis to form a metal oxide over the fibers. An example using aluminum chloride to form an aluminum oxide coating is described.