A heating element is used, a periphery of the heating element is covered with a net-shaped conductor, the conductor and a carbon fiber bundle are electrically connected with a connecting tool at one end of the heating element, a periphery of the conductor is covered with an outer skin having flexibility, thermal conductivity and an insulating property, and the other end of the heating element is provided with a power supply terminal configured to supply power.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

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.

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.

A complex ceramic particle and ceramic composite material may be made of a pretreated coal dust and a polymer derived ceramic that is mixed together and pyrolyzed in a nonoxidizing atmosphere. Constituent portions of the particle mixture chemically react causing particles to increase in density and reduce in size during pyrolyzation, yielding a particle suitable for a plurality of uses including composite articles and proppants.

A complex ceramic particle and ceramic composite material may be made of a pretreated coal dust and a polymer derived ceramic that is mixed together and pyrolyzed in a nonoxidizing atmosphere. Constituent portions of the particle mixture chemically react causing particles to increase in density and reduce in size during pyrolyzation, yielding a particle suitable for a plurality of uses including composite articles and proppants.

A porous ceramic structure intended to form the reinforcement of a ceramic matrix composite component, the structure having a connected porosity delimited by an internal surface which includes a plurality of first points, each first point being associated with a second point aligned with this first point along a normal to the internal surface taken at the first point, the structure being divisible into a plurality of unit volumes of a size less than or equal to 5 mm3 in each of which: a characteristic pore length, corresponding to the maximum of the distance separating each first point from its associated second point, is less than or equal to 0.5 mm; and a porosity ratio is greater than or equal to 50%.

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.

Disclosed herein are systems and methods for synthesis of polymer derived ceramic materials, including silicon oxycarbide comprising silicon metal. In some embodiments, the silicon metal is formed by carbothermal reduction during thermal processing. In some embodiments, the thermal processing comprises microwave plasma processing. In some embodiments, the silicon metal forms nanodomains within a structure of the silicon oxycarbide ceramic material.