The heat resistant structure of the flying body is provided with a tip part and a body part. The tip part is arranged in a front end of the flying body with respect to a direction of travel of the flying body. The body part is arranged in a back direction from the tip part with respect to the direction of travel of the flying body. The tip part is provided with a surface member, a base part, and an insulation member. The surface member is arranged on an outer surface of the tip part and has a melting point higher than a desired temperature. The base part couples the surface member to the body part. The insulation member is arranged between the surface member and the base part., and thermally insulates the base part from the surface member.

The heat resistant structure of the flying body is provided with a tip part and a body part. The tip part is arranged in a front end of the flying body with respect to a direction of travel of the flying body. The body part is arranged in a back direction from the tip part with respect to the direction of travel of the flying body. The tip part is provided with a surface member, a base part, and an insulation member. The surface member is arranged on an outer surface of the tip part and has a melting point higher than a desired temperature. The base part couples the surface member to the body part. The insulation member is arranged between the surface member and the base part., and thermally insulates the base part from the surface member.

A surface-coated boron nitride sintered body tool is provided, in which at least a cutting edge portion includes a cubic boron nitride sintered body and a coating film formed on a surface of the cubic boron nitride sintered body. The coating film includes an A layer and a B layer. The A layer is formed of columnar crystals each having a particle size of 10 nm or more and 400 nm or less. The B layer is formed of columnar crystals each having a particle size of 5 nm or more and 70 nm or less. The B layer is formed by alternately stacking two or more compound layers having different compositions. The compound layers each have a thickness of 0.5 nm or more and 300 nm or less.

A surface-coated boron nitride sintered body tool is provided, in which at least a cutting edge portion includes a cubic boron nitride sintered body and a coating film formed on a surface of the cubic boron nitride sintered body. The coating film includes an A layer and a B layer. The A layer is formed of columnar crystals each having a particle size of 10 nm or more and 400 nm or less. The B layer is formed of columnar crystals each having a particle size of 5 nm or more and 70 nm or less. The B layer is formed by alternately stacking two or more compound layers having different compositions. The compound layers each have a thickness of 0.5 nm or more and 300 nm or less.

A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

A coated article, comprising an article having at least one surface having disposed thereupon an oxidation resistant coating comprising at least two constituents to form a composition, a first constituent comprising at least one thermal expansion component comprising at least about 10% by volume to up to about 99% by volume of the composition, a second constituent comprising at least one oxygen scavenger comprising at least about 1% by volume to up to about 90% by volume of the composition.

A coated article, comprising an article having at least one surface having disposed thereupon an oxidation resistant coating comprising at least two constituents to form a composition, a first constituent comprising at least one thermal expansion component comprising at least about 10% by volume to up to about 99% by volume of the composition, a second constituent comprising at least one oxygen scavenger comprising at least about 1% by volume to up to about 90% by volume of the composition.

A composite article includes a substrate and a powder-derived composite coating on the substrate. The composite coating includes discrete regions of a first material and discrete regions of a second material. At least one of the first material or the second material is a chemical precursor.

A composite article includes a substrate and a powder-derived composite coating on the substrate. The composite coating includes discrete regions of a first material and discrete regions of a second material. At least one of the first material or the second material is a chemical precursor.

Provided is a silicon carbide-tantalum carbide composite having excellent durability. A silicon carbide-tantalum carbide composite (1) includes: a body (10) whose surface layer is at least partly formed of a first silicon carbide layer (12); a tantalum carbide layer (20); and a second silicon carbide layer (13). The tantalum carbide layer (20) is disposed over the first silicon carbide layer (12). The second silicon carbide layer (13) is interposed between the tantalum carbide layer (20) and the first silicon carbide layer (12). The second silicon carbide layer (13) has a C/Si composition ratio of not less than 1.2 as measured by X-ray photoelectron spectroscopy. The second silicon carbide layer (13) has a peak intensity ratio G/D of not less than 1.0 between the G-band and D-band of carbon as measured by Raman spectroscopy.