A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.

A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.

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.

A method of producing or repairing a fiber-reinforced ceramic matrix composite comprises delivering a powder composition comprising SiC particles and chopped coated SiC fibers into or onto a powder receptacle configured for composite fabrication or repair. After delivering the powder composition into or onto the powder receptacle, the SiC particles are densified to form a SiC matrix reinforced with the chopped coated SiC fibers, thereby producing or repairing a fiber-reinforced ceramic matrix composite.

Vessels such as crucibles, pans, open cups and saggars, containing a monolithic ceramic material, and a ceramic matrix composite, wherein the monolithic ceramic material is an inner tart. A method for making oxide materials that can be utilized in the contact with corrosive materials and that allows for higher conversions in a given heating process.

Vessels such as crucibles, pans, open cups and saggars, containing a monolithic ceramic material, and a ceramic matrix composite, wherein the monolithic ceramic material is an inner tart. A method for making oxide materials that can be utilized in the contact with corrosive materials and that allows for higher conversions in a given heating process.

Provided are a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic matrix composite. The coating structure is layered on the surface of the base portion, and includes a bond coat layer formed of a rare-earth silicate and a top coat layer layered on the bond coat layer. The residual stress present in the bond coat layer is compressive residual stress. The oxygen permeability coefficient of the bond coat layer is no greater than 10.sup.9 kg.Math.m.sup.1.Math.s.sup.1 at a temperature of not lower than 1200 C. and a higher oxygen partial pressure of not less than 0.02 MPa. The bond coat layer may contain carbonitride particles or carbonitride whiskers.

A new and innovative hard ceramic coating having refractory properties is provided. The ceramic coating may be used as a replacement for refractory materials. As opposed to polymer-based coatings that are sacrificial when exposed to extreme temperatures, the ceramic coating is a non-sacrificial, fully inorganic (e.g., free of organic components) coating that resists many thermal cycles. The ceramic coating is also thinner and lighter than conventional refractory materials the ceramic coating can replace. The ceramic coating demonstrates advantageous thermal insulation properties (e.g., low thermal conductivity) over a wide range of temperatures and when applied with minimal thickness. The ceramic coating also demonstrates high emissivity, low thermal conductivity, and high resistance mechanical properties, which are all desirable properties for use as a thermally insulating replacement coating for refractory materials.

A new and innovative hard ceramic coating having refractory properties is provided. The ceramic coating may be used as a replacement for refractory materials. As opposed to polymer-based coatings that are sacrificial when exposed to extreme temperatures, the ceramic coating is a non-sacrificial, fully inorganic (e.g., free of organic components) coating that resists many thermal cycles. The ceramic coating is also thinner and lighter than conventional refractory materials the ceramic coating can replace. The ceramic coating demonstrates advantageous thermal insulation properties (e.g., low thermal conductivity) over a wide range of temperatures and when applied with minimal thickness. The ceramic coating also demonstrates high emissivity, low thermal conductivity, and high resistance mechanical properties, which are all desirable properties for use as a thermally insulating replacement coating for refractory materials.