A coating material for a silicon carbide-based honeycomb structure, the coating material including from 20 to 75% by mass of ceramic powder (A), the ceramic powder (A) including from 55 to 95% by mass of silicon carbide and from 5 to 30% by mass of silicon dioxide as chemical components.

A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

The invention relates to a method for preparing a material based on an aluminosilicate selected from barium aluminosilicate BAS, barium-strontium aluminosilicate BSAS, and strontium aluminosilicate SAS, said aluminosilicate consisting of aluminosilicate with a hexagonal structure, characterised in that it includes a single sintering step in which a mixture of powders of precursors of said aluminosilicate, including an aluminium hydroxide Al(OH).sub.3 powder, are sintered by a hot-sintering technique with a pulsed electric field SPS; whereby a material based on an aluminosilicate, said aluminosilicate consisting of an aluminosilicate with a hexagonal structure is obtained. The material based on an aluminosilicate prepared by said method can be used in a method for preparing a composite material consisting of an aluminosilicate matrix reinforced by reinforcements made of metalloid or metal oxide.

Disclosed is a coated ceramic fiber including a silicon carbide coating layer adjacent to the ceramic fiber and a silicon dioxide coating layer adjacent to the silicon carbide coating layer, wherein the silicon dioxide coating layer forms micro cracks after a crystal structure transformation. The coated ceramic fiber may be included in a composite material having a ceramic matrix.

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.

A tow coating reactor system includes a reactor for receiving fiber tow, a wedge situated adjacent the reactor and configured to receive the tow at a tip end, such that as the tow moves across the wedge, the wedge spreads the tow into a plurality of sub-tows.

A method may include fused filament fabricating a fused filament fabricated component by delivering a softened filament to selected locations at or adjacent to a build surface. The softened filament may include a binder and a primary material. The binder is configured to release a secondary material upon heating at or above a conversion temperature. The method also may include heating the fused filament fabricated component to a temperature at or above the conversion temperature to sinter the primary material to form a sintered part and cause the binder to release the secondary material within the sintered part.

A method for the preparation of a composite article containing aerogel particles and ceramic fibers, as well as to a composite article obtained by this method, are described.

Disclosed herein is a chemical vapor infiltration method including flowing ceramic precursors through a preform and depositing a matrix material on the preform at a first gas infiltration pressure, increasing the gas filtration pressure to a second gas infiltration pressure, and lowering the gas infiltration pressure to a third gas infiltration pressure which is intermediate to the first and second gas infiltration pressures.

A method for constructing multiple ceramic layers by winding continuous ceramic filaments of identical composition to prepare multilayer RF-transparent structures is provided. In the method, identical continuous ceramic filaments are wound to construct a layer with specific dielectric constant according to patterns, characterized by the winding angle, winding density/inter-fiber aperture and winding count/layer thickness. Layers with same or different dielectric characteristics forms a sandwich design to fulfill the desired mechanical, thermal and electrical requirements.