Abstract: Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Abstract: Coated components, along with methods of their formation, are provided. The coated component includes a ceramic substrate having a surface; an intermediate layer on the surface of the ceramic substrate; and an environmental barrier coating on the intermediate layer. The intermediate layer includes a carbon-sink material that inhibits accumulation of free carbon from a carbon-containing species within the intermediate layer, the ceramic substrate, or both.

Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Abstract: A control system includes one or more processors configured to determine when to extend a life span of an engine by applying an additional restorative coating to the engine based on one or more monitored parameters of the engine. The monitored parameters include a condition of a previously applied restorative coating. The one or more processors are configured to determine the condition of the previously applied restorative coating based on an optical response of the previously applied restorative coating. The one or more processors also are configured to direct application of the additional restorative coating based on the one or more monitored parameters of the engine.

Abstract: Coated components, along with methods of their formation, are provided. The coated component includes a ceramic substrate having a surface; an intermediate layer on the surface of the ceramic substrate; and an environmental barrier coating on the intermediate layer. The intermediate layer includes a carbon-sink material that inhibits accumulation of free carbon from a carbon-containing species within the intermediate layer, the ceramic substrate, or both.

Abstract: Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Abstract: Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Abstract: Various embodiments include a gas turbine seal and methods of forming such seal. The method of forming the seal includes forming a freestanding ceramic seal for sealing in a gas turbine by applying a ceramic material on a substrate to form a ceramic layer, removing the substrate from the ceramic layer and finishing the ceramic layer to define the freestanding ceramic seal. The method includes depositing particles of the ceramic material in one of a molten or vapor state on a surface of the substrate and quenching the ceramic material to form the ceramic layer. The ceramic material comprises yttria-stabilized zirconia having a t? tetragonal structure. A gas turbine including the freestanding ceramic seal is additionally disclosed.

Abstract: The present application provides Calcia-Magnesia-Alumina-Silica (CMAS) (or molten silicate) resistant thermal barrier coatings (IBC). The coatings include elongate growth domains of non-equiaxed, randomly arranged overlapping grains or splats. The elongate growth domains include overlapping individual, randomly distributed splats of tough and soft phases. In some embodiments, the elongate growth domains are formed via air plasma spray. In some embodiments, the tough phases are at least partially stabilized zirconia and/or hafnia compositions, and the soft phases are CMAS (or molten silicate) reactive or resistant compositions. Within each elongate growth domain, the mixture of the tough and soft phases act together to limit penetration of CMAS and also provide sufficient domain toughness to minimize cracking forces produced during crystallization of infiltrated CMAS.

Abstract: A control system includes one or more processors configured to determine when to extend a life span of an engine by applying an additional restorative coating to the engine based on one or more monitored parameters of the engine. The monitored parameters include a condition of a previously applied restorative coating. The one or more processors are configured to determine the condition of the previously applied restorative coating based on an optical response of the previously applied restorative coating. The one or more processors also are configured to direct application of the additional restorative coating based on the one or more monitored parameters of the engine.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.

Abstract: A coated component, along with methods of its formation, restoration, and use, is provided. The coated component may include a substrate defining a surface; a thermal barrier coating on the surface of the substrate; a layer of environmental contaminant compositions (e.g., CMAS) on the thermal barrier coating; and a chemical barrier coating on the layer of environmental contaminant compositions.

Abstract: An article having a damage-tolerant thermal barrier coating includes a plurality of coating layers disposed over a substrate. The plurality of coatings comprises an inner layer and an outer layer. The outer layer is more resistant to infiltration by nominal CMAS relative to 8 weight percent yttria-stabilized zirconia at a temperature of 1300 degrees Celsius. The inner layer has, in a temperature range from about 1000 degrees Celsius to about 1200 degrees Celsius, a thermal resistance in a range from about 9×10?5 degree Kelvin per watt to about 23×10?5 degree Kelvin per watt.

Abstract: The present application provides Calcia-Magnesia-Alumina-Silica (CMAS) (or molten silicate) resistant thermal barrier coatings (TBC). The coatings include elongate growth domains of non-equiaxed, randomly arranged overlapping grains or splats. The elongate growth domains include overlapping individual, randomly distributed splats of tough and soft phases. In some embodiments, the elongate growth domains are formed via air plasma spray. In some embodiments, the tough phases are at least partially stabilized zirconia and/or hafnia compositions, and the soft phases are CMAS (or molten silicate) reactive or resistant compositions. Within each elongate growth domain, the mixture of the tough and soft phases act together to limit penetration of CMAS and also provide sufficient domain toughness to minimize cracking forces produced during crystallization of infiltrated CMAS.

Abstract: Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Abstract: A coated component, along with methods of its formation, restoration, and use, is provided. The coated component may include a substrate defining a surface; a thermal barrier coating on the surface of the substrate; a layer of environmental contaminant compositions (e.g., CMAS) on the thermal barrier coating; and a chemical barrier coating on the layer of environmental contaminant compositions.

Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.

Abstract: Articles suitable for use as high-temperature machine components include a substrate and an environmental barrier coating disposed over the substrate, where the environmental barrier coating includes at least one hermetic self-sealing layer formed from a mixture including an alkaline earth metal aluminosilicate and a rare-earth silicate, and where the at least one hermetic self-sealing layer exhibits substantially no net remnant or residual expansion when subjected to high temperature heat treatment. The environmental barrier coating can further include a bondcoat disposed between the substrate and the hermetic self-sealing layer, a topcoat disposed over the hermetic self-sealing layer, and/or an intermediate layer disposed between the hermetic self-sealing layer and the bondcoat. The intermediate layer can include a barrier material that is substantially inert with respect to silica.

Abstract: Coating systems for a turbine blade tip, such as a metal turbine blade tip, are provided. The coating system can include a thermal barrier coating on the surface of the turbine blade tip as well as one or more bond coats and/or metallic coatings. The coated blade tip can be used with a ceramic matrix composite shroud coated with an environmental barrier coating to reduce blade tip wear. Methods are also provided for applying the coating system onto a turbine blade tip.