Abstract: A gas turbine component, such as a turbine disk or a turbine seal element, is protected by depositing an oxide coating on the gas turbine component. The deposition is performed by a vapor deposition process such as metal-organic chemical vapor deposition (MOCVD) to a coating thickness of from about 0.2 to about 50 micrometers, preferably from about 0.5 to about 3 micrometers. The deposited oxide may be an oxide of aluminum, silicon, tantalum, titanium, and chromium.

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.

Abstract: A gas turbine engine wash process that facilitates reducing a formation of particulate matter within a gas turbine engine is described. The engine wash process includes injecting a first liquid into the engine to remove particulate matter formed within the engine and adversely affecting engine operation and performance. A second liquid is then injected into the engine to facilitate reducing a rate of formation of particulate matter within the gas turbine engine as the engine is operated in the future. More specifically, the second liquid is an anti-static liquid that coats compressor blades within the gas turbine engine.

Abstract: A protective coating system and method for protecting a thermal barrier coating from CMAS infiltration. The coating system comprises inner and outer alumina layers and a platinum-group metal layer therebetween. The outer alumina layer is intended as a sacrificial layer that reacts with molten CMAS, forming a compound with a melting temperature significantly higher than CMAS. As a result, the reaction product of the outer alumina layer and CMAS resolidifies before it can infiltrate the TBC. The platinum-group metal layer is believed to serve as a barrier to infiltration of CMAS into the TBC, while the inner alumina layer appears to enhance the ability of the platinum-group metal layer to prevent CMAS infiltration.

Abstract: A protective coating system and method for protecting a thermal barrier coating from CMAS infiltration. The coating system comprises inner and outer alumina layers and a platinum-group metal layer therebetween. The outer alumina layer is intended as a sacrificial layer that reacts with molten CMAS, forming a compound with a melting temperature significantly higher than CMAS. As a result, the reaction product of the outer alumina layer and CMAS resolidifies before it can infiltrate the TBC. The platinum-group metal layer is believed to serve as a barrier to infiltration of CMAS into the TBC, while the inner alumina layer appears to enhance the ability of the platinum-group metal layer to prevent CMAS infiltration.

Abstract: An article protected by a thermal barrier coating system includes a substrate having a substrate surface, and a thermal barrier coating system overlying the substrate. The thermal barrier coating system has a thermal barrier coating formed of a thermal barrier coating material arranged as a plurality of columnar grains extending generally perpendicular to the substrate surface and having grain surfaces. A sintering inhibitor is within the columnar grains, either uniformly distributed or concentrated at the grain surfaces. The sintering inhibitor is lanthanum oxide, chromium oxide, and/or yttrium chromate, mixtures thereof, or mixtures thereof with aluminum oxide.

Abstract: A system for determining a maintenance schedule for a jet engine using at least remotely-gathered environmental data is provided. The system includes a remote monitor having a sensor for collecting the remotely-gathered environmental data. A data pathway is connected to the remote monitor. A processor is connected to the data pathway and processes the remotely-gathered environmental data collected by the remote monitor. An environmental database is connected to the data pathway and compiles and stores the remotely-gathered environmental data. A flight database is connected to the data pathway and compiles and stores flight data for the jet engine. The flight data includes at least thermal cycle data and time on wing data. The processor is adapted to generate the maintenance schedule for the jet engine based on the remotely-gathered environmental data and the flight data.

Abstract: A gas turbine engine wash process that facilitates reducing a formation of particulate matter within a gas turbine engine is described. The engine wash process includes injecting a first liquid into the engine to remove particulate matter formed within the engine and adversely affecting engine operation and performance. A second liquid is then injected into the engine to facilitate reducing a rate of formation of particulate matter within the gas turbine engine as the engine is operated in the future. More specifically, the second liquid is an anti-static liquid that coats compressor blades within the gas turbine engine.

Abstract: An engine, according to an exemplary embodiment of the invention, comprises a compressor which compresses inlet air; a combustor in which a mixture of fuel and air is combusted; a turbine which is driven by gases from the combustor; and a dielectric coating applied to a surface of at least one of: the compressor and the turbine, the dielectric coating having a dielectric constant of at least 3.0 and a loss tangent of at most 0.1, wherein the dielectric coating reduces the magnitude of an electrostatic force which attracts particles flowing through the engine to the surface of the engine. In operation, only a thin layer of particles typically accumulates on the dielectric coating. While the dielectric coating reduces the magnitude of the electric field which attracts particles, the repulsive force produced by the accumulated particles repels additional particles of the same charge.

Abstract: Cooking speed and efficiency are increased in radiant ovens by reducing the intensity of energy emitted by the oven's radiant energy source that does not deeply penetrate food. Undesired photochemical reactions in the cooked food are also reduced or eliminated. In one embodiment, the radiant energy source includes at least one lamp having a coating that reflects at least some of the radiant energy that does not deeply penetrate food. In another embodiment, a plate that reflects or absorbs at least some of the radiant energy that does not deeply penetrate food is disposed between the radiant energy source and a location within the oven where food to be cooked is placed.

Abstract: A sensor for sensing conditions on an object. The sensor comprises a first at least partially reflective surface layer disposed adjacent the object in close conforming relationship with a surface of the object, an intermediate layer, and a second at least partially reflective surface layer. The intermediate layer is disposed between the first at least partially reflective surface layer and the second at least partially reflective surface layer. The intermediate layer can be formed as a solid element, a combination of solid areas and spaces, and as an aerogel.

Abstract: A hermetically packaged radiation imager includes a moisture barrier cover disposed over the imaging array and a hermetic seal structure disposed around the periphery of the moisture barrier cover to seal the cover to the underlying substrate. The hermetic seal structure comprises a solder seal disposed in contact with the moisture barrier cover and a dielectric material layer disposed between the solder seal and conductive lines extending from the imager array across the substrate surface. The hermetic seal structure further includes a primer layer that is disposed between the dielectric material layer and the solder seal to provide a foundation to which the solder seal adheres. The dielectric material layer is deposited in an atomic layer epitaxy technique, thus providing a thin layer having high structural integrity.

Abstract: A method is disclosed to deposit aluminum coatings on high temperature superalloys for corrosion, oxidation, and erosion protection using low temperature chemical vapor deposition and an organometallic halide precursor, specifically an aluminum alkyl halide. The process is adapted to protective coatings for turbine parts having internal passages. Due to the lower temperatures used during chemical vapor deposition, a broad range of substrate materials can be utilized. The precursor vapors clean the substrate surfaces by removing native oxides while simultaneously depositing aluminum.

Abstract: A hermetically packaged radiation imager includes a moisture barrier cover disposed over the imaging array and a hermetic seal structure disposed around the periphery of the moisture barder cover to seal the cover to the underlying substrate. The hermetic seal structure comprises a solder seal disposed in contact with the moisture barrier cover and a dielectric material layer disposed between the solder seal and conductive lines extending from the imager army across the substrate surface. The hermetic seal structure further includes a primer layer that is disposed between the dielectric material layer and the solder seal to provide a foundation to which the solder seal adheres. The dielectric material layer is deposited in an atomic layer epitaxy technique, thus providing a thin layer having high structural integrity.