The method includes forming an inner monolithic layer from crystals of beta phase stoichiometric silicon carbide on a carbon substrate in the form of a rod by chemical methylsilane vapor deposition in a sealed tubular hot-wall CVD reactor. The method further includes forming a central composite layer over the inner monolithic layer by twisting continuous beta phase stoichiometric silicon carbide fibers into tows, transporting the tows to a braiding machine, and forming a reinforcing thread framework. A pyrocarbon interface coating is built up by chemical methane vapor deposition in a sealed tubular hot-wall CVD reactor. Then, a matrix is formed by chemical methylsilane vapor deposition in the reactor. A protective outer monolithic layer is formed from crystals of beta phase stoichiometric silicon carbide over the central composite layer by chemical methylsilane vapor deposition in a CVD reactor. And then the carbon substrate is removed from the fabricated semi-finished product.

The method includes forming an inner monolithic layer from crystals of beta phase stoichiometric silicon carbide on a carbon substrate in the form of a rod by chemical methylsilane vapor deposition in a sealed tubular hot-wall CVD reactor. The method further includes forming a central composite layer over the inner monolithic layer by twisting continuous beta phase stoichiometric silicon carbide fibers into tows, transporting the tows to a braiding machine, and forming a reinforcing thread framework. A pyrocarbon interface coating is built up by chemical methane vapor deposition in a sealed tubular hot-wall CVD reactor. Then, a matrix is formed by chemical methylsilane vapor deposition in the reactor. A protective outer monolithic layer is formed from crystals of beta phase stoichiometric silicon carbide over the central composite layer by chemical methylsilane vapor deposition in a CVD reactor. And then the carbon substrate is removed from the fabricated semi-finished product.

Coating systems are provided for use on a CMC substrate, that can include: a bond coat on a surface of the CMC substrate; a first rare earth silicate coating on the bond coat; a sacrificial coating of a reinforced rare earth silicate matrix on the at least one rare earth silicate layer; a second rare earth silicate coating on the sacrificial coating; and an outer layer on the second rare earth silicate coating. The first rare earth silicate coating comprises at least one rare earth silicate layer, and the second rare earth silicate coating comprises at least one rare earth silicate layer. The sacrificial coating has a thickness of about 4 mils to about 40 mils. Methods are also provided for tape deposition of a sacrificial coating on a CMC substrate.

Coating systems are provided for use on a CMC substrate, that can include: a bond coat on a surface of the CMC substrate; a first rare earth silicate coating on the bond coat; a sacrificial coating of a reinforced rare earth silicate matrix on the at least one rare earth silicate layer; a second rare earth silicate coating on the sacrificial coating; and an outer layer on the second rare earth silicate coating. The first rare earth silicate coating comprises at least one rare earth silicate layer, and the second rare earth silicate coating comprises at least one rare earth silicate layer. The sacrificial coating has a thickness of about 4 mils to about 40 mils. Methods are also provided for tape deposition of a sacrificial coating on a CMC substrate.

A coated building article comprising a fiber cement cladding element may be coated with a system designed to achieve a desired appearance. The coating system may comprise a first coating layer and a second coating layer wherein the second coating layer comprises at least one layer of a low gloss coating composition which has a light reflectance of 5% or less when light is shone onto the surface of the coated article at an angle of 60? or 85? to the surface is positioned on at least a portion of the front face of the fiber cement cladding element. Also provided is a method of coating the building article with a low gloss coating composition.

A preparation method includes: pressing and forming a ceramic base material to obtain a green body of a ceramic plate; applying a ground glaze on the surface of the green body to cover the base color and defects of the green body; applying a cover glaze on the surface of the green body after applying the ground glaze, wherein the cover glaze contains 0.2 wt % to 0.7 wt % of coloring metal oxide to make the coloring bright; roller-printing patterns on the surface of the green body after applying the cover glaze to produce a flowing cloud effect; and drying the green body with the roller-printed patterns and firing in a kiln. The present invention uses roller printing to print the patterns of cloud effect on the surface of the cover glaze, which form a sharp contrast with the color of the cover glaze, producing a better visually distinct effect.

A method of repairing a nonconforming article includes applying a machinable coating to an article with a nonconformance. The article includes a preform at least partially infiltrated with a matrix material, to form a repaired article. The method also includes machining the machinable coating and completing infiltration of the repaired article with the matrix material. A method of repairing an article is also disclosed.

A method of repairing a nonconforming article includes applying a machinable coating to an article with a nonconformance. The article includes a preform at least partially infiltrated with a matrix material, to form a repaired article. The method also includes machining the machinable coating and completing infiltration of the repaired article with the matrix material. A method of repairing an article is also disclosed.

A multilayer protective coating system includes a turbine engine component substrate formed of a ceramic matrix composite material, an environmental barrier coating layer including a rare earth disilicate material deposited directly on the substrate, and a plurality of pairs of alternating layers of the rare earth disilicate material and a rare earth monosilicate material deposited and sintered directly on the environmental barrier coating layer. Each layer of the plurality of pairs of alternating layers is relative less thick as compared with the environmental barrier coating layer.

A multilayer protective coating system includes a turbine engine component substrate formed of a ceramic matrix composite material, an environmental barrier coating layer including a rare earth disilicate material deposited directly on the substrate, and a plurality of pairs of alternating layers of the rare earth disilicate material and a rare earth monosilicate material deposited and sintered directly on the environmental barrier coating layer. Each layer of the plurality of pairs of alternating layers is relative less thick as compared with the environmental barrier coating layer.