A method of making a ceramic composite component includes providing a fibrous preform or a plurality of fibers, providing a first plurality of particles, coating the first plurality of particles with a coating to produce a first plurality of coated particles, delivering the first plurality of coated particles to the fibrous preform or to an outer surface of the plurality of fibers, and converting the first plurality of coated particles into refractory compounds. The first plurality of particles or the coating comprises a refractory metal.

A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine includes an airfoil assembly. The airfoil assembly includes an airfoil and at least one reinforcement inset coupled to the airfoil assembly. The reinforcement inset is configured to resist damage to the airfoil assembly due to objects impacting the airfoil assembly.

A method is provided in which multiple layers are formed. Each of the layers includes at least a first set of ceramic fibers and a second set of ceramic fibers. The first set is arranged at an angle with respect to the second set. The first set and the second set define a plurality of pores therebetween. The layers are arranged on top of each other to form a porous preform. The pores of the layers arranged on top of each other are aligned. The pores define a plurality of channels extending continuously through the porous preform from a first side of the porous preform to a second side of the porous preform. Each channel comprises one inlet at the first side of the porous preform and one outlet at the second side of the porous preform. The porous preform is infiltrated with a matrix material.

Powder particles for forming a homogeneous green body having a sufficient strength and a process for producing a green body by using the powder particles. A green body is shaped by using powder particles of composite particles in which thermoplastic resin particles are scattered on surfaces of large particles in an amount within a predetermined volume ratio range with respect to the large particles, and loaded to form resin pools in contact point peripheral areas of adjoining ones of the large particles and form voids in areas other than the contact point peripheral areas when the thermoplastic resin particles are melted. A green body packed with the powder particles each having a small amount of the thermoplastic resin particles attached thereon is placed under a melting condition of the thermoplastic resin particles, the thermoplastic resin is melted and gathers around contact points (or proximal points) of the adjoining powder particles.

Provided herein is a method of making a conductive network by combining uncoated carbon nanotubes and carbon nanotubes coated with an electroactive substance to create an electrically conductive network; and redistributing at least a portion of the electroactive substance. Also provided herein is an electrically conductive network with an active material coating; first carbon nanotubes coated with the active material coating; and second carbon nanotubes partially coated with the active material coating, wherein at least a portion of the surfaces of the second carbon nanotubes directly contact surfaces of other second carbon nanotubes without the active material coating between these second carbon nanotubes, and wherein the first carbon nanotubes and the second carbon nanotubes are entangled to form an electrically conductive network.

Methods for fabricating high-temperature composite structures (e.g., structures comprising carbon-carbon composite materials or ceramic composite matrix (CMC) materials and configured for use at temperature at or exceeding about 2000 F. (1093 C.)) include forming precursor structures by additive manufacturing (AM) (e.g., 3D printing). The precursor structures are exposed to high temperatures to pyrolyze a precursor matric material of the initial 3D printed structure. A liquid resin is used to impregnate the pyrolyzed structure, to densify the structure into a near-net final shape. Use of expensive and time-consuming molds and post-processing machining may be avoided. Large, unitary, integrally formed parts conducive for use in high-temperature environments may be formed using the methods of the disclosure.

A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a first polymeric precursor with a spinneret; forming a first plurality of nanofibers from the first polymeric precursor; depositing the first plurality of nanofibers with a collector; and applying a fluid, with a nozzle, onto the first plurality of nanofibers disposed on the collector. The fluid includes a second polymeric precursor.

A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine includes an airfoil assembly. The airfoil assembly includes an airfoil and at least one reinforcement inset coupled to the airfoil assembly. The reinforcement inset is configured to resist damage to the airfoil assembly due to objects impacting the airfoil assembly.

A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.

Composite material units (CMU) of the structure (SE1-ML-LinkerL-Ligand2-SE2), are provided, wherein ML is a Mechanical Ligand, LinkerL is a chemical bond or entity that covalently links ML and Ligand2, Ligand2 is a chemical entity that is covalently linked to the structural entity SE2, or forms a mechanical bond with the structural entity SE2, and SE1 and SE2 are structural entities.