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.

A method and a fugitive mold for producing a cast-metal part are provided. In some embodiments, the fugitive mold may be formed by three-dimensionally (3D) printing a preceramic resin in the shape of a fugitive mold; curing the preceramic resin to form a preceramic polymer, and pyrolyzing the fugitive mold to convert the preceramic polymer to a metastable ceramic material. The metastable ceramic material may include an amorphous silicon oxycarbide ceramic. A cast-metal part may be formed by filling the fugitive mold with a liquid metal or alloy, and allowing the liquid metal or alloy to solidify over a first length of time. The cast-metal part may then be retrieved by heating the fugitive mold at a temperature lower than the melting point of the cast-metal part for a second length of time longer than the first length of time to disintegrate the metastable ceramic material.

A bonded abrasive article includes elongate shaped abrasive particles. The elongate shaped abrasive particles comprise an elongate shaped ceramic body having opposed first and second ends joined to each other by at least two longitudinal sidewalls. At least one of the at least two longitudinal sidewalls is concave along its length. At least one of the first and second ends is a fractured surface.

A method for the joining of ceramic pieces with a hermetically sealed joint comprising brazing a layer of joining material between the two pieces. The wetting and flow of the joining material is controlled by the selection of the joining material, the joining temperature, the joining atmosphere, and other factors. The ceramic pieces may be on a non-diffusable type, such as aluminum nitride, alumina, beryllium oxide, and zirconia, and the pieces may be brazed with an aluminum alloy under controlled atmosphere. The joint material is adapted to later withstand both the environments within a process chamber during substrate processing, and the oxygenated atmosphere which may be seen within the shaft of a heater or electrostatic chuck.

A method of forming a layered material including arranging a 2DLM on a base material comprising one or more Moiré interferences, and adding material or removing material at a location of the one or more Moiré interferences.

An indenter is made of polycrystalline diamond and has a tip having a spherical surface with a radius of 10 to 2000 μm.

A structure having excellent rectification performance and durability and having a micro flow channel is provided. The structure has a flow channel in the inside, wherein the cross section of the flow channel has a shape in which a region surrounded by a substantially elliptical curve and a line segment is connected to a triangular region with the base being the line segment, the region surrounded by the line segment and the substantially elliptical curve is semielliptical or more, and the base angle of the triangular region is 45 degrees or more.

A rotating member of the present disclosure mainly includes ceramics and includes a first through-hole into which a shaft is inserted and a second through-hole into which a key protruding from an outer peripheral surface of the shaft or a solid lubricant in direct or indirect sliding contact with the outer peripheral surface of the shaft is inserted. The second through-hole is a polygonal shape if viewed in an axial direction of the first through-hole and includes a notch part extending along the axial direction at at least one corner.

The method includes the steps of: a) selecting particles with particular slenderness ratios and diameters from SiC powder to serve as selected SiC material powder; b) coating a PVA coating on particles of the selected SiC material powder so that the PVA coating and the selected SiC material powder are combined into a particulate ceramic material; c) pressing the particulate ceramic material into a ceramic base body; d) sintering the ceramic base body to form a fixed shape and forming completely continuous channels from an inside to a surface thereof by cooling; and e) infiltrating the ceramic base body with molten aluminum. The ceramic composite material made by the method includes a ceramic base body having completely continuous channels from an inside to a surface thereof; an aluminum filler filled in the channels; and an aluminum coating disposed on the ceramic base body and integratedly connecting with the aluminum filler.

A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.