A method of fabricating an impregnated fiber assembly, the method including introducing a first suspension including a first powder of solid particles into an inside volume defined by an inside face of a first fiber texture of hollow shape placed in a mold, an outer face of the first fiber texture being present facing a wall of the mold; using a centrifugal force to impregnate the first fiber texture with the first suspension by rotating the mold; after impregnating the first texture, positioning a second fiber texture on the inside face of the first fiber texture to obtain a fiber assembly; introducing a second suspension including a second powder of solid particles into the inside volume after putting the second fiber texture into position; and using a centrifugal force to impregnate the second fiber texture with the second suspension by rotating the mold to obtain an impregnated fiber assembly.

A method of creating a tackified prepreg includes steps of providing a fiber weave that have unidirectional fibers and woven sections spaced apart from one another to provide unidirectional fiber sections, applying a tackifier to the fiber weave, and separating the unidirectional fiber section from the woven sections.

The present disclosure is directed to a method for forming a passage in a composite component. The method includes forming a cavity in a fiber preform. The cavity forms a portion of the passage. The method also includes inserting a core into the cavity and placing one or more fiber plies onto the fiber preform to form a fiber preform assembly. The method further includes thermally processing the fiber preform assembly and densifying the fiber preform assembly to form the composite component. The method also includes removing the core from the composite component.

Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.

A composite production method includes impregnating a plate-shaped porous inorganic structure and a fibrous inorganic material with a metal while the fibrous inorganic material is arranged to be adjacent to the porous inorganic structure. In the composite structure, first and second phases are adjacent to each other by using a porous inorganic structure having a porous silicon carbide ceramic sintered body and the fibrous inorganic material, the first phase being a phase in which the porous silicon carbide ceramic sintered body is impregnated with the metal, the second phase being a phase in which the fibrous inorganic material is impregnated with the metal, a percentage of the porous silicon carbide ceramic sintered body in the first phase is 50 to 80 volume percent, and a percentage of the fibrous inorganic material in the second phase is 3 to 20 volume percent. A composite is produced by the method.

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 composite material part includes a fiber preform forming fiber reinforcement including a stack of at least two fiber plies, each of the fiber plies being made of an interlock weave three-dimensional fabric and each of the fiber plies having a number of warp yarn layers or a number of weft yarn layers that is greater than or equal to three; and a matrix present in the pores of the fiber preform.

A method of forming a ceramic matrix composite component is provided. The method includes applying a first amount of adhesive across a surface of a release film, providing a first ceramic foam panel including a plurality of channels formed on a first side of the first ceramic foam panel, contacting the first ceramic foam panel and the release film such that adhesive transfers to the first side of the first ceramic foam panel, and coupling the first ceramic foam panel to a second ceramic foam panel.

A ceramic component is formed of at least one stack of two or more layers of one-directional non-woven carbon fiber fabrics embedded in a ceramic matrix containing silicon carbide and elemental silicon. All adjacent layers within the at least one stack directly adjoin each other. The at least one stack has a minimum thickness of 1.5 mm perpendicularly to the plane of the layers. The ceramic matrix permeates substantially the entire component.

A method of providing an end-capped tubular ceramic composite for containing nuclear fuel (34) in a nuclear reactor involves the steps of providing a tubular ceramic composite (40), providing at least one end plug (14, 46, 48), applying (42) the at least one end plug material to the ends of the tubular ceramic composite, applying electrodes to the end plug and tubular ceramic composite and applying current in a plasma sintering means (10, 50) to provide a hermetically sealed tube (52). The invention also provides a sealed tube made by this method.