The present invention relates to a method for producing a metal nitride, which is a method for synthesizing a metal nitride by igniting a raw material powder containing a metal powder housed in a reaction vessel (2) under a nitrogen atmosphere and propagating nitriding combustion heat of the metal powder to the whole of the housed raw material powder, characterized in that the raw material powder is housed in the reaction vessel (2) as a molded body (1B) having a void ratio of 40 to 70%. According to the present invention, it is possible to provide a method for producing a metal nitride capable of suppressing the occurrence of powder scattering and improving the recovery rate of the metal nitride.

Disclosed is a method of fabricating an anode for a lithium-ion battery, including milling a mixture of nano-silicon, one or more carbonaceous materials and one or more solvents, wherein the mixture is retained as a wet slurry during milling. The mixture is carbonised to produce a silicon thinly coated with carbon (Si@C) material. Further milling occurs of a second mixture of the Si@C material, one or more graphite, one or more second carbonaceous materials and one or more second solvents, wherein the second mixture is retained as a second wet slurry during milling. The second mixture is carbonised to produce a Si@C/graphite/carbon material. The anode is formed from the Si@C/graphite/carbon material.

An article comprises a body and a conformal protective layer on at least one surface of the body. The conformal protective layer is a plasma resistant rare earth oxide film having a thickness of less than 1000 μm, wherein the plasma resistant rare earth oxide film consists essentially of 40 mol % to less than 100 mol % of Y.sub.2O.sub.3, over 0 mol % to 60 mol % of ZrO.sub.2, and 0 mol % to 9 mol % of Al.sub.2O.sub.3.

Provided is a refractory product which is not impregnated with pitch or the like, wherein it has higher corrosion-erosion resistance and thermal shock resistance as compared to a refractory product subjected to pitch or the like-impregnation treatment. The refractory product which is not impregnated with tar or pitch is characterized in that, in terms of values of physical properties of a sample of the refractory product as measured after heat-treating the sample in a non-oxidizing atmosphere at 1200° C.: an apparent porosity is 7% or less; a total void volume of pores having a pore diameter of 1 μm or less is 80% or more of an integrated void volume of pores of the entire sample of the refractory product; and a gas permeability is 50×10.sup.−17 m.sup.2 or less.

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.

A method for coating fibers, includes desizing sized short fibers having an average length less than or equal to 5 mm, the short fibers being made of ceramic material or carbon, sieving the desized short fibers in order to separate them from any agglomerates of sized short fibers still present, introducing the desized and sieved short fibers into a reactor, and coating the short fibers in the reactor by chemical vapor deposition in a fluidized bed.

A method for manufacturing ceramic matrix composites (CMC) and CMCs made by the method are disclosed. The method can be a manual process or an automated process, such as using a robotic system, that is used for controlled delivery of ceramic particles in a CMC fabric. The method includes identifying voids present between adjacent tows of the CMC fabric and dispensing ceramic particles into the voids. Applying the ceramic particles in the center of the voids reduces the size and volume fraction of the voids/defects, improving the homogeneity of surface texture of the preform, homogeneity of microstructure, and part model shape conformity. The method for manufacturing CMCs creates CMCs having a homogenous distribution of small pores after matrix formation that improves the interlaminar mechanical and thermal properties of the CMCs.

An example technique includes extruding, by a tow deposition device, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material on a major surface of a substrate. Each respective impregnated tow includes at least one ceramic fiber and a curable resin coating the at least one ceramic fiber. The example technique includes curing the curable resin to form a cured composite component. An example system includes a tow deposition device, an energy source, and a computing device. The computing device is configured to control the tow deposition device to extrude, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material, and is configured to control the energy source to cure the curable resin to form a cured composite component.

Systems, devices, and methods are provided for manufacturing a carbon ceramic brake disc. Generally, a plurality of uncured or partially-cured bulk molding compound preforms or molding compound layers and ventilation cores are placed in a mold cavity and warm-pressed at a first temperature. The ventilation cores are removed from the resulting cured green body. The cured green body is then removed from the mold, and treated through a polymer infiltration and pyrolysis or reactive melt infiltration process. Certain steps can be repeated until a desired target density or weight is attained.

Provided is a member for optical glass manufacturing apparatus. The member is used for optical glass manufacturing apparatus and exposed to a gas containing a halogen element in a high temperature environment of 1100° C. or higher. The member includes dense ceramics containing silicon nitride as a main component, and a porosity of a surface layer of the member is smaller than a porosity of the inside of the member.