Abstract: An example article according to the present disclosure includes, among other possible things, a metallic substrate, and a bond coat on the metallic substrate. The bond coat includes a matrix phase, gettering particles in the matrix phase, wherein the gettering particles are reactive with oxidants, and a dispersion of matrix modifier particles in the matrix phase. The example article also includes a diffusion barrier between the bond coat and the metallic substrate, wherein the diffusion barrier is configured to inhibit diffusion of components from the bond coat into the metallic substrate. An example composite material and method of applying a barrier to a substrate are also disclosed.

Abstract: A gas turbine engine component having a substrate; a thermal barrier coating on the substrate having a porous microstructure; and a reflective layer conforming to the porous microstructure of the thermal barrier coating, wherein the reflective layer comprises a conforming nanolaminate defined by alternating layers of platinum group metal materials selected from the group consisting of platinum group metal-based alloys, platinum group metal intermetallic compounds, mixtures of platinum group metal with metal oxides and combinations thereof. A capping layer can be added over the reflective layer. A supporting layer can be added between the reflective layer and the thermal barrier coating. A process is also disclosed.

Abstract: A multi-phase radiative and thermal barrier coating system including a substrate having a substrate surface; a first layer deposited on the substrate surface; a second layer deposited on the first layer, the second layer having an outer surface, wherein the second layer comprises radiative barrier materials in a porous thermal conduction and radiant heat transfer resistant microstructure.

Abstract: A method for protecting a coated substrate having a porous ceramic barrier coating includes applying a molten salt to the ceramic barrier coating. The salt is selected from the group consisting of one or more acetates and/or nitrates. The molten salt is infiltrated into porosity of the ceramic barrier coating. The infiltrated molten salt is solidified. The solidified salt is sintered.

Abstract: Disclosed is a coated composite comprising a seal coat disposed on a composite material wherein the seal coat comprises protective particles and a matrix.

Abstract: A method of applying a coating to a substrate includes forming a slurry by mixing elemental precursors of gettering particles, diffusive particles, matrix material, and a carrier fluid; applying the slurry to a substrate; and sintering the slurry to form a composite material. The sintering causes the elemental precursors to react with one another to form gettering particles. An article is also disclosed.

Abstract: An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix phase and gettering particles in the matrix phase. The gettering particles with an aspect ratio greater than one are aligned such that a maximum dimension of the gettering particles extends along an axis that is generally parallel to the substrate. The barrier layer includes a dispersion of diffusive particles in the matrix phase. A composite material and a method of applying a barrier layer to a substrate are also disclosed.

Abstract: A gas turbine engine component having a substrate; a thermal barrier coating on the substrate having a porous microstructure; and a reflective layer conforming to the porous microstructure of the thermal barrier coating, wherein the reflective layer comprises a conforming nanolaminate defined by alternating layers of platinum group metal materials selected from the group consisting of platinum group metal-based alloys, platinum group metal intermetallic compounds, mixtures of platinum group metal with metal oxides and combinations thereof. A capping layer can be added over the reflective layer. A supporting layer can be added between the reflective layer and the thermal barrier coating. A process is also disclosed.

Abstract: A component of an aero-propulsion apparatus, wherein the component includes a material and has a surface, and a thin film on the surface, wherein the thin film is configured to undergo a detectible change in properties when exposed to a temperature exceeding a threshold temperature. Methods are also disclosed.

Abstract: Disclosed is a coated ceramic fiber including a silicon carbide coating layer adjacent to the ceramic fiber and a silicon dioxide coating layer adjacent to the silicon carbide coating layer, wherein the silicon dioxide coating layer forms micro cracks after a crystal structure transformation. The coated ceramic fiber may be included in a composite material having a ceramic matrix.

Abstract: A nanocomposite optical ceramic (NCOC) material includes a plurality of coated (core-shell) nanoparticles having nanoparticles of a first material coated with a coating of a second material. The first material and the second material are mutually insoluble and each have a transmissivity of at least 80% for an intended wavelength. The first material and the second material have a difference in index of refraction of less than 25%. The first material and second material have grins with a diameter of less than 1/20th the intended wavelength. The coating of the second material on the nanoparticles of the first material is up to 50 nm thick. The NCOC contains no more than 0.01% voids per unit volume.

Abstract: An article includes a substrate, a barrier layer disposed on the substrate, and an oxide-based ceramic material topcoat disposed on the barrier layer. The topcoat includes at least one crack. The article also includes a filler layer disposed on the topcoat and in the at least one crack. A method of applying a coating to an article and an article are also disclosed.

Abstract: An article includes a substrate and a barrier layer on the substrate. The barrier layer includes a matrix, diffusive particles dispersed in the matrix, and gettering particles dispersed in the matrix. The gettering particles include at least one alloyed metal silicide. A composite material and a method of fabricating an article are also disclosed.

Abstract: A method for forming an oxidation protection system on a carbon-carbon composite structure can comprise applying a boron slurry to the carbon-carbon composite structure, wherein the boron slurry comprises a boron compound, a first glass mixture, a first glass former, a first glass modifier, and a first carrier fluid, the first glass mixture including a first glass compound and a second glass compound, the first glass compound having a first viscosity-temperature profile that is at least one order of magnitude below a second viscosity-temperature profile of the second glass compound; applying a silicon slurry to the carbon-carbon composite structure, wherein the silicon slurry comprises a silicon compound, a third glass compound, a second glass former, a second glass modifier, and a second carrier fluid; and heating the carbon-carbon composite structure.

Abstract: A method for forming an oxidation protection system on a carbon-carbon composite structure comprises applying a boron slurry to the carbon-carbon composite structure, wherein the boron slurry comprises a boron composition, a first glass compound, a first glass former, a first glass modifier, and a first carrier fluid, the boron composition including a first metal boride, applying a silicon slurry to the carbon-carbon composite structure, wherein the silicon slurry comprises a silicon compound, a glass compound, a second glass former, a second glass modifier, an oxygen inhibitor, and a second carrier fluid; and heating the carbon-carbon composite structure.

Abstract: An article according to an exemplary embodiment of this disclosure includes a substrate and a bond coat disposed on the substrate. The bond coat includes a matrix. The matrix includes regions of ?-cristobalite. The article also includes a plurality of gettering particles disposed in the matrix, a plurality of diffusive particles disposed in the matrix, and an additive operable to stabilize the regions of ?-cristobalite at ambient temperatures dispersed in the matrix. An article and a method of coating an article are also disclosed.

Abstract: A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

Abstract: An environmental barrier coating includes a barrier layer which includes a matrix, diffusive particles, and gettering particles; and a calcium-magnesia alumina-silicate (CMAS)-resistant component. The CMAS-resistant component includes hafnium silicate and a rare earth hafnate. An article and a method of fabricating an article are also disclosed.

Abstract: Disclosed is a coated ceramic fiber including a silicon carbide coating layer adjacent to the ceramic fiber and a silicon dioxide coating layer adjacent to the silicon carbide coating layer, wherein the silicon dioxide coating layer forms micro cracks after a crystal structure transformation. The coated ceramic fiber may be included in a composite material having a ceramic matrix.

Abstract: An environmental barrier coating includes a barrier layer which includes a matrix, diffusive particles, and gettering particles; and a calcium-magnesia alumina-silicate (CMAS)-resistant component. The CMAS-resistant component includes hafnium silicate and a rare earth hafnate. An article and a method of fabricating an article are also disclosed.