Sized molds for metal casting are obtained from molding material mixtures on the basis of inorganic bonding agents containing at least one phosphatic compound and at least one oxidic boron compound, especially sized, water glass-bound forms and cores, having at least one refractory base molding material, water glass as inorganic bonding agent and amorphous particulate silicon dioxide and one or more powdery oxidic boron compounds and one or more phosphatic compounds. The invention furthermore relates to a method for producing sized foundry mold bodies and use thereof, in particular for producing cast parts from iron alloys. The sizing is a water-based sizing.

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1′.sub.b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1′ is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2′.sub.d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2′ is any one of Sc, Yb, and Lu).

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1′.sub.b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1′ is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2′.sub.d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2′ is any one of Sc, Yb, and Lu).

A coated component, along with methods of its formation and use, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a mullite bondcoat on its surface. The mullite bondcoat includes an oxygen getter phase contained within a mullite phase. For example, the mullite bondcoat may include 60% to 98% by volume of the mullite phase. An environmental barrier coating is on the mullite bondcoat.

A coated component, along with methods of its formation and use, is provided. The coated component includes a ceramic matrix composite (CMC) substrate comprising silicon carbide and having a mullite bondcoat on its surface. The mullite bondcoat includes an oxygen getter phase contained within a mullite phase. For example, the mullite bondcoat may include 60% to 98% by volume of the mullite phase. An environmental barrier coating is on the mullite bondcoat.

Methods of forming oxidation barriers are provided. An illustrative method comprises applying a clay mineral coating composition comprising a solvent and exfoliated clay mineral sheets, e.g., exfoliated vermiculite sheets, to a surface of a substrate; and removing solvent from the clay mineral coating composition as-applied to the surface, thereby forming a coating comprising the exfoliated clay mineral sheets on the surface. The oxidation barriers are also provided.

A gas turbine engine article includes a substrate and a silicate-resistant barrier coating disposed on the substrate. The silicate-resistant barrier coating has an engineered microstructure that includes a refractory matrix formed of grains and calcium aluminosilicate additive (CAS additive) dispersed in grain boundaries between the grains.

A gas turbine engine article includes a substrate and a silicate-resistant barrier coating disposed on the substrate. The silicate-resistant barrier coating has an engineered microstructure that includes a refractory matrix formed of grains and calcium aluminosilicate additive (CAS additive) dispersed in grain boundaries between the grains.

An article may include a substrate including a ceramic or a ceramic matrix composite. The substrate defines a hot side surface configured to face a heated gas environment and a cool side surface opposite the hot side surface. The article also includes a cool side coating on the cool side surface. The cool side coating comprises at least one material having a flow temperature equal to or slightly less than a temperature of the heated gas environment.

An article may include a substrate including a ceramic or a ceramic matrix composite. The substrate defines a hot side surface configured to face a heated gas environment and a cool side surface opposite the hot side surface. The article also includes a cool side coating on the cool side surface. The cool side coating comprises at least one material having a flow temperature equal to or slightly less than a temperature of the heated gas environment.