Abstract: A machine having a fixed part including a portion with a smooth surface is provided. The machine also includes a rotating part configured to rotate relative to the fixed part, the rotating part directly facing the portion of the fixed part, and plural ridges formed on the portion of the fixed part directly facing the rotating part, the plural ridges comprising an abradable material, wherein the abradable material is configured to be inoperable at temperatures above about 1000° C.

Abstract: A target assembly for generating x-rays includes a target substrate, and an emissive coating attached to the target substrate, the emissive coating including a textured material including a plurality of granular protrusions arranged to increase gray body emissive characteristics of the target assembly above that of the target substrate.

Abstract: A target assembly for generating x-rays includes a target substrate, and an emissive coating applied to a portion of the target substrate, the emissive coating comprising one or more of a carbide and a carbonitride.

Abstract: A target assembly for generating x-rays includes a target substrate, and an emissive coating attached to the target substrate, the emissive coating including a textured material including a plurality of granular protrusions arranged to increase gray body emissive characteristics of the target assembly above that of the target substrate.

Abstract: A target assembly for generating x-rays includes a target substrate, and an emissive coating applied to a portion of the target substrate, the emissive coating comprising one or more of a carbide and a carbonitride.

Abstract: A bearing assembly for an x-ray tube is disclosed that includes a bearing race, a bearing ball positioned adjacent to the bearing race, and a combination coating deposited on one of the bearing race and the bearing ball. The combination coating includes titanium carbide and a solid lubricant.

Abstract: An environmental coating is applied to the surface of a titanium-base alloy substrate to protect the surface from oxidation, corrosion, erosion, and other damage. The coating is a mixture of a metal and a ceramic, each selected to contribute to the protective function. The proportions of the metal and the ceramic in the coating are selected such that the coefficient of thermal expansion of the coating is about the same as the coefficient of thermal expansion of the substrate.

Abstract: An abradable coating composition for use on shrouds in gas turbine engines (or other hot gas path metal components exposed to high temperatures) containing an initial porous coating phase created by adding a “fugitive polymer” (such as polyester or polyimide) to the base metal alloy, together with a brittle intermetallic phase such as &bgr;-NiAl that serves to increase the brittle nature of the metal matrix, thereby increasing the abradability of the coating at elevated temperatures, and to improve the oxidation resistance of the coating at elevated temperatures. Coatings having about 12 wt % polyester has been found to exhibit excellent abradability for applications involving turbine shroud coatings. An abradable coating thickness in the range of between 40 and 60 ml provides the best performance for turbine shrouds exposed to gas temperatures between 1380° F. and 1850° F.

Abstract: An abradable coating composition for use on shrouds in gas turbine engines (or other hot gas path metal components exposed to high temperatures) containing an initial porous coating phase created by adding a “fugitive polymer” (such as polyester or polyimide) to the base metal alloy, together with a brittle intermetallic phase such as &bgr;-NiAl that serves to increase the brittle nature of the metal matrix, thereby increasing the abradability of the coating at elevated temperatures, and to improve the oxidation resistance of the coating at elevated temperatures. Coatings having about 12 wt % polyester has been found to exhibit excellent abradability for applications involving turbine shroud coatings. An abradable coating thickness in the range of between 40 and 60 ml provides the best performance for turbine shrouds exposed to gas temperatures between 1380° F. and 1850° F.

Abstract: An improved thermal barrier coating is disclosed. The coating is formed on a metal part to be exposed to high temperature gases. The metal part is first coated with an adherent sublayer of MCrAlY alloy. In this case, the M of the MCrAlY is nickel, cobalt, iron, or some combination of these metals. A diffused layer of MCrAlY combined with a low concentration of mullite is formed over the MCrAlY subcoating and the mullite is increased in concentration as the thickness of the layer increases. The outer surface of the layer is all mullite. Improved life expectancy and decreased thermal conductivity is achieved.