The disclosure describes articles having coating systems configured to inhibit or prevent crystallization of TGO at the operating temperature of the article. An article includes a substrate defining a surface; a bond coat on the surface of the substrate; a coating layer that includes a boron dopant configured to inhibit crystallization of amorphous silicon dioxide thermally grown oxide on the bond coat at an operating temperature of the article. By inhibiting or preventing TGO crystallization, the described coating systems may increase a useable life of the component.

Composite materials and methods of manufacturing composite materials, such as for use in aerospace parts, are described herein. A representative method for manufacturing a coated composite material structure includes applying a plurality of material layers to a preform structure. The plurality of material layers can include at least one first material layer (including a first matrix precursor), and at least one second material layer (including a second matrix precursor and a coating precursor). The method can also include infusing the preform structure with the first and second matrix precursors and the coating precursor from the plurality of material layers. The method can further include heating the infused preform structure to concurrently form a composite material structure and a coating on at least a portion of the composite material structure.

Composite materials and methods of manufacturing composite materials, such as for use in aerospace parts, are described herein. A representative method for manufacturing a coated composite material structure includes applying a plurality of material layers to a preform structure. The plurality of material layers can include at least one first material layer (including a first matrix precursor), and at least one second material layer (including a second matrix precursor and a coating precursor). The method can also include infusing the preform structure with the first and second matrix precursors and the coating precursor from the plurality of material layers. The method can further include heating the infused preform structure to concurrently form a composite material structure and a coating on at least a portion of the composite material structure.

A process for manufacturing a part made of a ceramic matrix composite material, includes coating an outer surface of a porous preform with a layer of a fugitive material to form a model of the part to be obtained, the fugitive material being wax or resin, the fugitive material layer in the model not exceeding the highest peak of surface undulations of the preform, and ceramic and/or carbon particles being present in the porosity of the preform, coating the model formed with a ceramic powder composition, heat treating the coated model to remove the fugitive material and form a ceramic shell mold by sintering of the ceramic powder composition, introducing a molten composition including silicon into the shell mold to obtain the part in the shell mold, the molten composition infiltrating the porosity of the preform to form the ceramic matrix, and separating the shell mold from the part obtained.

A process for manufacturing a part made of a ceramic matrix composite material, includes coating an outer surface of a porous preform with a layer of a fugitive material to form a model of the part to be obtained, the fugitive material being wax or resin, the fugitive material layer in the model not exceeding the highest peak of surface undulations of the preform, and ceramic and/or carbon particles being present in the porosity of the preform, coating the model formed with a ceramic powder composition, heat treating the coated model to remove the fugitive material and form a ceramic shell mold by sintering of the ceramic powder composition, introducing a molten composition including silicon into the shell mold to obtain the part in the shell mold, the molten composition infiltrating the porosity of the preform to form the ceramic matrix, and separating the shell mold from the part obtained.

The present disclosure relates to a composition that includes a scaffold having an internal space and a mixture positioned within the space, where the mixture includes a first phase having a metal halide perovskite and a second phase including at least one of a perovskite precursor and/or a switching molecule, the composition is capable of reversibly switching between a first state having at least one of a first transparency and/or a first color and a second state having at least one of a second transparency and/or a second color.

Disclosed is a method for preparing a carbon-reinforced metal-ceramic composite material, including: mixing raw materials of carbon, copper, zinc, titanium, copper oxide, calcium oxide and titanium dioxide, ball-milling the raw materials with a medium of ethanol to obtain a mixture, drying and milling the mixture to obtain a powder, sintering the powder with a laser having an irradiation power ranging from 100 to 600 W and an irradiation period of 3 min to 10 min to obtain a product, and rapidly cooling the product to allow a temperature of the product to be decreased to the room temperature within 5 min to obtain the carbon-reinforced metal-ceramic composite material.

Disclosed is a method for preparing a carbon-reinforced metal-ceramic composite material, including: mixing raw materials of carbon, copper, zinc, titanium, copper oxide, calcium oxide and titanium dioxide, ball-milling the raw materials with a medium of ethanol to obtain a mixture, drying and milling the mixture to obtain a powder, sintering the powder with a laser having an irradiation power ranging from 100 to 600 W and an irradiation period of 3 min to 10 min to obtain a product, and rapidly cooling the product to allow a temperature of the product to be decreased to the room temperature within 5 min to obtain the carbon-reinforced metal-ceramic composite material.

A method of forming a barrier layer on a ceramic matrix composite (CMC) is described. The method includes forming a particulate surface layer comprising silicon particles on an outer surface of a fiber preform. The particulate surface layer is nitrided to convert the silicon particles to silicon nitride particles. After the nitriding, the fiber preform and the particulate surface layer are infiltrated with a molten material comprising silicon. Following infiltration, the molten material is cooled, thereby forming a ceramic matrix composite with a barrier layer thereon, where the barrier layer comprises silicon nitride and less than 5 vol. % free silicon. The barrier layer may also include silicon carbide and/or one or more refractory metal silicides.

A method of forming a barrier layer on a ceramic matrix composite (CMC) is described. The method includes forming a particulate surface layer comprising silicon particles on an outer surface of a fiber preform. The particulate surface layer is nitrided to convert the silicon particles to silicon nitride particles. After the nitriding, the fiber preform and the particulate surface layer are infiltrated with a molten material comprising silicon. Following infiltration, the molten material is cooled, thereby forming a ceramic matrix composite with a barrier layer thereon, where the barrier layer comprises silicon nitride and less than 5 vol. % free silicon. The barrier layer may also include silicon carbide and/or one or more refractory metal silicides.