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.

Methods for fabricating protective coating systems for gas turbine engine applications are provided. An exemplary method of applying a protective coating to a substrate includes the steps of providing a substrate formed of a ceramic matrix composite material, forming a first coating layer directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and forming a second coating layer directly on to the first coating layer and comprising a thermal barrier material. The method optionally includes forming a third coating layer partially directly on to the second coating layer and partially within at least some of the plurality of pores of the second coating layer.

Methods for fabricating protective coating systems for gas turbine engine applications are provided. An exemplary method of applying a protective coating to a substrate includes the steps of providing a substrate formed of a ceramic matrix composite material, forming a first coating layer directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and forming a second coating layer directly on to the first coating layer and comprising a thermal barrier material. The method optionally includes forming a third coating layer partially directly on to the second coating layer and partially within at least some of the plurality of pores of the second coating layer.

A gas turbine engine article includes a substrate and an environmental barrier coating (EBC) system disposed on the substrate. The EBC system includes, from the substrate, a dense bond coat layer, a porous bond coat layer, and a topcoat layer in contact with the porous bond coat layer at an interface. The porous bond coat layer includes a matrix, oxygen-scavenging gas-evolution particles dispersed through the matrix, and engineered buffer pores. The oxygen-scavenging gas-evolution particles react with oxygen and generate a gaseous byproduct that diffuses through the interface to escape the EBC system. The engineered buffer pores buffer diffusion of gaseous byproduct to the interface by retaining at least a portion of the gaseous byproduct.

A gas turbine engine article includes a substrate and an environmental barrier coating (EBC) system disposed on the substrate. The EBC system includes, from the substrate, a dense bond coat layer, a porous bond coat layer, and a topcoat layer in contact with the porous bond coat layer at an interface. The porous bond coat layer includes a matrix, oxygen-scavenging gas-evolution particles dispersed through the matrix, and engineered buffer pores. The oxygen-scavenging gas-evolution particles react with oxygen and generate a gaseous byproduct that diffuses through the interface to escape the EBC system. The engineered buffer pores buffer diffusion of gaseous byproduct to the interface by retaining at least a portion of the gaseous byproduct.

Provided is a cutting tool that can have a long tool life even when used to cut soft metals in particular. The cutting tool comprises a base body and a hard carbon film arranged on the base body, the hard carbon film includes an amorphous phase and a graphite phase, the density of the hard carbon film is no less than 2.5 g/cm.sup.3 and no more than 3.5 g/cm.sup.3, the degree of crystallinity of the hard carbon film is no more than 6.5%, and the average coordination number of the amorphous phase is no less than 2.5 and no more than 4.

Provided is a cutting tool that can have a long tool life even when used to cut soft metals in particular. The cutting tool comprises a base body and a hard carbon film arranged on the base body, the hard carbon film includes an amorphous phase and a graphite phase, the density of the hard carbon film is no less than 2.5 g/cm.sup.3 and no more than 3.5 g/cm.sup.3, the degree of crystallinity of the hard carbon film is no more than 6.5%, and the average coordination number of the amorphous phase is no less than 2.5 and no more than 4.

An object of the present invention is to provide a porous ceramic laminate that can reduce pressure loss of a fluid. The present invention is a porous ceramic laminate comprising a first porous layer and a second porous layer, wherein the second porous layer is laminated on the first porous layer, the second porous layer has a portion being laminated on, in contact with, the first porous layer and a portion being laminated over the first porous layer via air, and a coefficient of variance CV (t.sub.b) of the second porous layer thickness is not larger than 0.35.