Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Thermally-conductive ceramic and ceramic composite components suitable for high temperature applications, systems having such components, and methods of manufacturing such components. The thermally-conductive components are formed by a displacive compensation of porosity (DCP) process and are suitable for use at operating temperatures above 600° C. without a significant reduction in thermal and mechanical properties.

A fibrous preform for forming the fibrous reinforcement of a friction part made of composite material, includes a woven helical fibrous texture defining a superposition of fibrous layers, the texture being needled and having ceramic particles selectively at areas intended to define the rubbing faces of the friction part.

The present invention relates to surface-treated prepreg composites and corresponding methods of surface treating an inorganic fabric to form a surface-treated fabric reinforced prepreg composite. The method comprises infiltrating an inorganic fabric with a first slurry mixture to form an infiltrated fabric; optionally drying the infiltrated fabric; infiltrating an inorganic paper with a second slurry mixture to form an infiltrated paper; optionally drying the infiltrated paper; and applying the infiltrated paper to at least one surface of the infiltrated fabric to form a surface-treated prepreg composite.

An AC-electrospinning system and a method are provided for fabricating inorganic fiber tubular structures. The AC-electrospinning system preferably uses an electrode system that comprises an electrical charging component electrode and at least one of an AC field attenuating component and a precursor liquid attenuating component. Use of the AC-electrospinning process to fabricate the inorganic fiber tubular structures allows the structures to be made with high porosities that are not achievable using the conventional approach.

A mandrel for a molding process that includes a first portion that has a first portion outer surface, a first portion inner surface, a first portion first end, and a first portion second end. A thickness of the first portion first end is greater than the first portion second end. A second portion has a second portion outer surface, a second portion inner surface, a second portion first end, and a second portion second end. A thickness of the second portion first end is smaller than the second portion second end. The first portion inner surface engages the second portion inner surface to form a mandrel that has a constant cross-section.

A turbine engine component may comprise a Ceramic Matrix Composite (CMC) structure including a plurality of nominally dense plies, wherein each of the plurality of the nominally dense plies are bonded by at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS), or a localized heating at a bonding interface. The turbine engine component may include an airfoil extending between a first platform and a second platform, wherein the airfoil, the first platform, and the second platform define the CMC structure.

A method for forming a ceramic matrix composite (CMC) component with an internal cooling channel includes forming a first fiber member, forming a first depression in a surface of the first fiber member, covering the first depression with a second fiber member to form a near-net shape fiber preform of a component with an internal channel defined in part by the first depression, and densifying the fiber preform.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis. The vanes include a first vane that is integral with the first rotor disk and projects axially to the second rotor disk.

A composite material manufacturing method includes: laminating a first sheet (210) including a first slurry (214) and a third sheet (230) including a third slurry (234); and heating the first sheet (210) and the third sheet (230) that are laminated to a temperature of transforming to ceramics by pyrolysis to form an intermediate body (300). The manufacturing method further includes impregnating the intermediate body (300) with a slurry and heating at a temperature lower than a temperature of transforming to ceramics by pyrolysis.