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.

A protective fabric which includes at least one structural layer and a ceramic composite material layer fixed to the at least one structural layer, is provided. The structural layer can include a non-woven material made from or containing synthetic fibers. The ceramic composite material layer is formed of ceramic composite material powder which includes a ceramic carrier, and iron-silver crystals containing zero-valent iron and zero-valent silver supported on the ceramic carrier. The protective fabric is effective for removing VOCs, suppressing bacterial growth, and filtering or inactivating virus, such as SARS-CoV-2 virus. Protective products or articles incorporating the protective fabric are also provided.

An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.

A protective fabric which includes at least one structural layer and a ceramic composite material layer fixed to the at least one structural layer, is provided. The structural layer can include a non-woven material made from or containing synthetic fibers. The ceramic composite material layer is formed of ceramic composite material powder which includes a ceramic carrier, and iron-silver crystals containing zero-valent iron and zero-valent silver supported on the ceramic carrier. The protective fabric is effective for removing VOCs, suppressing bacterial growth, and filtering or inactivating virus, such as SARS-CoV-2 virus. Protective products or articles incorporating the protective fabric are also provided.

This disclosure provides a method of pressure sintering an environmental barrier coating on a surface of a ceramic substrate to form an article. The method includes the steps of etching the surface of the ceramic substrate to texture the surface, disposing an environmental barrier coating on the etched surface of the ceramic substrate wherein the environmental barrier coating includes a rare earth silicate, and pressure sintering the environmental barrier coating on the etched surface of the ceramic substrate in an inert or nitrogen atmosphere at a pressure of greater than atmospheric pressure such that at least a portion of the environmental barrier coating is disposed in the texture of the surface of the ceramic substrate thereby forming the article.

A method for manufacturing a composite panel is described. The method includes producing a first wall, a second wall, a third wall and a fourth wall from composite materials including an oxide matrix and long oxide fibres; from the first and second walls, producing a cellular core including a plurality of cells, each cell including a first end and an opposing second end, covering the first and second ends of the cells of the cellular core with the third wall and the fourth wall, respectively, so as to close the ends of said cells.

The present invention provides a silicon carbide fiber reinforced silicon carbide composite material, which is a composite material of SiC fibers and SiC ceramics with improved toughness and can be produced with high yield by relatively simple steps without complex steps such as a step of oxidation-resistant coating or an advanced interface control step. The silicon carbide composite material comprises a multiphase matrix and silicon carbide fibers disposed in the matrix, the matrix containing a silicon carbide phase and a phase that includes a substance of low reactivity with respect to silicon carbide. It can be obtained by steps suitable for mass production and ensures greatly improved fracture toughness while maintaining the excellent properties of SiC ceramics.

A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.

Adhesive compositions and methods for bonding materials with different thermal expansion coefficients is provided. The adhesive is formulated using a flux material, a low flux material, and a filler material, where the filler material comprises particulate from at least one of the two components being bonded together. A thickening agent can also be used as part of the adhesive composition to aid in applying the adhesive and establishing a desired bond thickness. The method of forming a high strength bond using the disclosed adhesive does not require the use of intermediary layer or the use of high cure temperatures that could damage one or both of the components being bonded together.

A honeycomb body made of a composite material for fire-resistant lightweight structures including honeycomb cells having a cross section is provided. The cell walls of the honeycomb cells are produced from a composite material. The composite material has at least one carrier, for example a woven fabric or a laid fabric made of fibers, and a matrix into which the carrier is embedded. The matrix includes a silicon-based ceramic material, of which the proportion by mass in the matrix along the cell walls is at least 30 wt. %. A method for producing such a ceramic honeycomb body and a honeycomb tube as an intermediate product for the same are also provided. A flat semi-finished product as a curable intermediate product for the production of fire-resistant fiber composite lightweight structures, which has a matrix mixture including dispersed silicon particles, is also provided.