The present invention relates to a body (2) provided on air vehicles; at least one transition metal alloy (3) which is located on the body (2) and consists of two-dimensional inorganic compounds by bonding a plurality of carbon atoms (C) and a plurality of nitrogen atoms (N); a plurality of layers (4) containing the transition metal alloy (3); at least one barrier coating (5) consisting of layers (4), which, thanks to the conductivity of the layer (4), prevents and provides protection against plastic and/or elastic deformations that may occur on the body (2) as a result electromagnetic wave that will act on the body (2), thanks to the conductivity of the layer (4).

Disclosed are a multi-layer porcelain block, a preparation method thereof and a denture. The multi-layer porcelain block includes a first zirconia powder layer, a second zirconia powder layer, a third zirconia powder layer, a fourth zirconia powder layer, a fifth zirconia powder layer, a sixth zirconia powder layer, a seventh zirconia powder layer, and an eighth zirconia powder layer laid in sequence. The zirconia powers in the first to eighth zirconia powder layers are doped with yttria. The first zirconia powder layer accounts for 13% to 17% by mass, the second zirconia powder layer accounts for 8% to 12% by mass, the third zirconia powder layer accounts for 10% to 14% by mass, the fourth zirconia powder layer accounts for 10% to 14% by mass, the fifth zirconia powder layer accounts for 10% to 14% by mass, the sixth zirconia powder layer accounts for 10% to 14% by mass.

A method is provided and suggests grading of a CMC (Ceramic Matrix Composite) structure as a function of dielectric constant by altering the solid loading (SL) ratio of the individual composite layers. The slurry is applied either by impregnation into the ceramic fabrics or by coating on ceramic fibers. The final structure is prepared by piling up prepregs or weaving ceramic fibers with specific SL ratio, drying and firing.

A composition includes granules in which zirconia particles are aggregated. The granules have an average circularity of 0.81 or greater based on a projected image.

Composite components and methods for adding a composite material to a composite component are provided. For example, a method comprises positioning a composite material segment against the composite component to form a component layup; applying an insulating material around at least a portion of the component layup to form an insulated layup; and densifying the insulated layup, where the composite component was previously densified before positioning the composite material segment against the composite component. In some embodiments, the composite material is ceramic matrix composite (CMC) and the composite material segment is a plurality of CMC plies. The composite component may be a CMC gas turbine engine component that comprises an original CMC component and a new CMC material segment joined to the original CMC component through the transfer of silicon between the original CMC component and the new CMC material segment during melt infiltration.

The invention relates to a method for the preparation of a blank of a ceramic material, wherein a first ceramic material and then a second ceramic material of different compositions are filled into a die and wherein the materials are pressed and after pressing are sintered. A layer of the first ceramic material is thereby filled into the die and a first cavity formed in the layer, the second ceramic material is then filled into the first open cavity and the materials pressed together and then heat-treated.

A ceramic component is provided that is suitable to be placed in high temperature environment. The component includes a first member that is formed of a first material, and a ceramic layer that is bonded to a surface of the first member, which is a side exposed to the high temperature environment and that is formed of a ceramic material having a higher heat resistance than that of the first member. A bonding portion between the first member and the ceramic layer is formed of a composite material having the first material and the ceramic material, and a gradient composition in which an abundance ratio of the first material gradually decreases and an abundance ratio of the ceramic material gradually increases in a direction from the first member to the ceramic layer.

The invention relates to a transparent composite material for various applications, having crystalline and amorphous inorganic materials with improved material properties.

Provided is a porous plate-shaped filler that can be used as a material for a heat-insulation film having excellent heat insulation performance. In a porous plate-shaped filler 1 having a plate shape, an aspect ratio is 3 or higher, a minimum length is 0.5 to 50 m, and an overall porosity is 20 to 90%, and the porosity is lower in the circumferential part than in the center part. When this porous plate-shaped filler 1 of the present invention is contained in a heat-insulation film, the infiltration of a matrix into the filler is reduced, and thus the thermal conductivity can be lowered. Therefore, even a thin heat-insulation film can have a greater heat-insulation effect than before.

A method of forming a ceramic matrix composite (CMC) component having an engineered surface includes applying a surface slurry comprising first particulate solids in a liquid carrier to an outer surface of a ceramic fiber preform. The surface slurry is dried to remove the liquid carrier, and thus a surface slurry layer comprising the first particulate solids is formed on the outer surface. The surface slurry layer is polished to a predetermined thickness and/or surface finish. After polishing, a ceramic tape comprising second particulate solids is applied to the surface slurry layer, and pressure is applied to attach the ceramic tape to the surface slurry layer and to induce consolidation of the ceramic tape and the surface slurry layer. Thus, a multilayer surface region comprising the surface slurry layer and a ceramic tape layer is formed on the ceramic fiber preform. The ceramic fiber preform and the multilayer surface region are infiltrated with a molten material, and, upon cooling, a CMC component having an engineered surface is formed.