A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.

A CMC ply assembly is disclosed including at least one matrix ply interspersed amongst a plurality of CMC plies. Each of the plurality of CMC plies includes a first matrix and a plurality of ceramic fibers. The at least one matrix ply includes a second matrix and is essentially free of ceramic fibers. The plurality of CMC plies and the at least one matrix ply are arranged in an undensified ply stack having an article conformation. A CMC article is disclosed including a plurality of densified CMC plies and at least one densified matrix ply interspersed amongst the plurality of densified CMC plies. A method for forming the CMC article is disclosed including forming, carburizing, infusing a melt infiltration agent into, and densifying the CMC ply assembly. The melt infiltration agent infuses more completely through the at least one matrix ply than through the plurality of CMC plies.

Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.

A fuel rod for a nuclear fission reactor is disclosed and claimed. The fuel rod includes an elongate hollow cladding configured to retain a nuclear fuel therein. The cladding includes an elongate hollow tube. Fiber layers are positioned around the outside surface of the tube or within the tube forming an integral part thereof. Both the tube and the fibers are formed of a ceramic material. A fuel assembly including a plurality of such fuel rods is also disclosed and claimed.

The present disclosure relates to a method for producing an acoustic attenuation panel having two outer skins made from a composite material with a ceramic matrix containing a fibrous reinforcement. The skins are assembled on each side of a central honeycomb core having walls forming acoustic cavities produced by at least partial electrochemical conversion of aluminum into aluminum oxide. The method includes inserting a fugitive filler material into the acoustic cavities, leaving an annular space free in each cavity, on each side against the skin, extending around the cavity, and a step of sintering the composite material, in which the fugitive material is removed and the spaces around the cavities are filled with the composite material.

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 method of fabricating a composite material part comprises fiber reinforcement densified by a matrix. The method comprises the following steps: making a fiber fabric by weaving yarns having an initial mean fiber percentage; and densifying the fiber fabric with a matrix. The fiber fabric is subjected, prior to densification, to one or more jets of water under pressure so as to reduce the mean fiber percentage in the fabric to a value lying in the range 20% to 45%.

A pre-form CMC cavity and method of forming pre-form CMC cavity for a ceramic matrix component includes providing a mandrel, applying a base ply to the mandrel, laying-up at least one CMC ply on the base ply, removing the mandrel, and densifying the base ply and the at least one CMC ply. The remaining densified base ply and at least one CMC ply form a ceramic matrix component having a desired geometry and a cavity formed therein. Also provided is a method of forming a CMC component.

The invention relates to a multilayer cladding including a combination of ceramic and metallic components. The multilayer coating includes an inner layer, an intermediate layer and an outer layer. The inner layer can form the cladding structure, the intermediate layer can include a ceramic composite or ceramic-containing composite composed of interlocking woven or braided fibers, e.g., fiber tows wrapped on the inner layer to form a woven structure, and a matrix material, and the outer can be composed of metal or metal alloy, such as, in the form of a coating. The multilayer cladding is effective to protect contents of the cladding structure from exposure to high temperature environments.

The present invention relates to a gastight multilayer composite tube having a heat transfer coefficient of >500 W/m.sup.2/K and comprising at least two layers, namely a layer of nonporous monolithic oxide ceramic and a layer of oxidic fiber composite ceramic, a connecting piece comprising at least one metallic gas-conducting conduit which in the longitudinal direction of the composite tube overlaps in a region at least two ceramic layers, where the one ceramic layer comprises a nonporous monolithic ceramic and the other ceramic layer comprises a fiber composite ceramic, and also the use of the multilayer composite tube as reaction tube for endothermic reactions, radiation tubes, flame tubes or rotary tubes.