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 coated component, along with method of forming the same, is provided. The coated component may include a substrate having a surface, a silicon-based bond coating on the surface of the substrate, and an EBC on the silicon-based bond coating. The silicon-based bond coating may include a silicon-phase contained within a refractory phase. The silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating. Such a coated component may be, in particular embodiments, a turbine component.

A coated component, along with method of forming the same, is provided. The coated component may include a substrate having a surface, a silicon-based bond coating on the surface of the substrate, and an EBC on the silicon-based bond coating. The silicon-based bond coating may include a silicon-phase contained within a refractory phase. The silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating. Such a coated component may be, in particular embodiments, a turbine component.

An airfoil includes a ceramic matrix composite airfoil core that defines an airfoil portion and a root portion. The ceramic matrix composite airfoil core is subject to core thermal growth. A platform includes a ceramic matrix composite that wraps around the root portion. The platform is subject to platform thermal growth. A buffer layer is located between the root portion and the platform. The buffer layer absorbs a mismatch between the core thermal growth and the platform thermal growth.

An airfoil includes a ceramic matrix composite airfoil core that defines an airfoil portion and a root portion. The ceramic matrix composite airfoil core is subject to core thermal growth. A platform includes a ceramic matrix composite that wraps around the root portion. The platform is subject to platform thermal growth. A buffer layer is located between the root portion and the platform. The buffer layer absorbs a mismatch between the core thermal growth and the platform thermal growth.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

A plate-shaped heat dissipation member includes a metal-silicon carbide composite containing aluminum or magnesium, in which at least one of two main surfaces of the heat dissipation member is curved to be convex in an outward direction of the heat dissipation member, and when a flatness of the one main surface defined by JIS B 0621 is represented by f.sub.1 and a flatness of the other main surface different from the one main surface defined by JIS B 0621 is represented by f.sub.2, f.sub.2 is less than f.sub.1 by 10 μm or more.

A plate-shaped heat dissipation member includes a metal-silicon carbide composite containing aluminum or magnesium, in which at least one of two main surfaces of the heat dissipation member is curved to be convex in an outward direction of the heat dissipation member, and when a flatness of the one main surface defined by JIS B 0621 is represented by f.sub.1 and a flatness of the other main surface different from the one main surface defined by JIS B 0621 is represented by f.sub.2, f.sub.2 is less than f.sub.1 by 10 μm or more.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.