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 component includes a substrate at least a portion of which adjacent to a surface of the substrate is made of a material including silicon; a bond coat located on the surface of the substrate and including silicon, an environmental barrier which includes an outer layer of ceramic material covering the bond coat, wherein the environmental barrier further includes a self-healing inner layer located between the bond coat and the outer layer, the inner layer including a matrix in which silico-forming particles are dispersed, these particles being capable of generating a matrix crack healing phase in the presence of oxygen.

A component includes a substrate at least a portion of which adjacent to a surface of the substrate is made of a material including silicon; a bond coat located on the surface of the substrate and including silicon, an environmental barrier which includes an outer layer of ceramic material covering the bond coat, wherein the environmental barrier further includes a self-healing inner layer located between the bond coat and the outer layer, the inner layer including a matrix in which silico-forming particles are dispersed, these particles being capable of generating a matrix crack healing phase in the presence of oxygen.

A method of redefining an opening in a composite component comprises filling the opening with a filling material, where the opening is defined in a body of the composite component and opens onto a surface defined by the composite component, and redefining the opening such that the opening extends into the body. Some methods comprise removing an existing coating from the surface of the composite component prior to filling the opening with the filling material and applying a new coating to the surface prior to redefining the opening such that the opening extends through the new coating and into the body. An exemplary composite component comprises a body, a surface with a coating thereon, an original opening defined through the body and filled with a filling material, and a new opening defined through the coating into the body, which may be defined at a new location from the original opening.

A method of redefining an opening in a composite component comprises filling the opening with a filling material, where the opening is defined in a body of the composite component and opens onto a surface defined by the composite component, and redefining the opening such that the opening extends into the body. Some methods comprise removing an existing coating from the surface of the composite component prior to filling the opening with the filling material and applying a new coating to the surface prior to redefining the opening such that the opening extends through the new coating and into the body. An exemplary composite component comprises a body, a surface with a coating thereon, an original opening defined through the body and filled with a filling material, and a new opening defined through the coating into the body, which may be defined at a new location from the original opening.

An article includes a substrate, an intermediate coating on the substrate, and an environmental barrier coating (EBC) on the intermediate coating. The substrate includes a ceramic, ceramic matrix composite (CMC), or superalloy. The EBC includes a rare earth disilicate. When the intermediate coating is at an initial state, such as prior to exposure to an oxidating environment, the intermediate coating includes a bond coat on the substrate and a reactive layer on the bond coat. The bond coat includes silicon, while the reactive layer includes a rare earth monosilicate or rare earth oxide. In response to oxidation of a portion of the silicon of the bond coat to form silicon dioxide, a portion of the rare earth monosilicate or rare earth oxide of the reactive layer is configured to react with at least a portion of the silicon dioxide to form a converted layer that includes a rare earth disilicate.

In one example, a method for forming a coating system including a bond coat and an environmental barrier coating on a ceramic or CMC substrate, e.g., with an abradable coating on the environmental barrier coating. The method may include depositing a bond coat on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited bond coat; heat treating the as-deposited bond coat following the deposition of the as-deposited bond coat on the substrate to form a heat treated bond coat; depositing an environment barrier coating (EBC) layer on the heat treated bond coat to form as deposited EBC layer; and heat treating the as-deposited EBC layer to form a heat treated EBC layer.

In one example, a method for forming a coating system including a bond coat and an environmental barrier coating on a ceramic or CMC substrate, e.g., with an abradable coating on the environmental barrier coating. The method may include depositing a bond coat on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited bond coat; heat treating the as-deposited bond coat following the deposition of the as-deposited bond coat on the substrate to form a heat treated bond coat; depositing an environment barrier coating (EBC) layer on the heat treated bond coat to form as deposited EBC layer; and heat treating the as-deposited EBC layer to form a heat treated EBC layer.

Systems for and methods for improving mechanical properties of ceramic material are provided. The system comprises a heat source for heating the ceramic material to a temperature greater than a brittle-to-ductile transition temperature of the ceramic material; a probe for mounting the ceramic material and configured to extend the ceramic material into the heat source; a plasma-confining medium and a sacrificial layer disposed between the ceramic material and the plasma-confining medium; and an energy pulse generator such as a laser pulse generator. The sacrificial layer is utilized to form plasma between the ceramic material and the plasma-confining medium. The method comprises heating ceramic material to a temperature greater than a brittle-to-ductile transition temperature of the ceramic material and subjecting the ceramic material to energy pulses via a sacrificial layer and a plasma-confining medium whereby a plasma of the sacrificial coating forms between the ceramic material and a plasma-confining medium.

An automated preparation method of a SiC.sub.f/SiC composite flame tube, comprising the following steps: preparing an interface layer for a SiC fiber by a chemical vapor infiltration process, and obtaining the SiC fiber with a continuous interface layer; laying a unidirectional tape on the SiC fiber with the continuous interface layer and winding the SiC fiber with the continuous interface layer to form and obtaining a preform of a net size molding according to a fiber volume and a fiber orientation obtained in a simulation calculation; and adopting a reactive melt infiltration process and the chemical vapor infiltration process successively for a densification and obtaining a high-density SiC.sub.f/SiC composite flame tube in a full intelligent way. The SiC.sub.f/SiC composite flame tube prepared by the present disclosure not only has a high temperature resistance, but also has a low thermal expansion coefficient, high thermal conductivity and high thermal shock resistance.