A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a polymeric precursor with a spinneret biased at a first DC voltage; forming a plurality of nanofibers from the polymeric precursor; receiving the plurality of nanofibers with a collector biased at a second DC voltage different than the first DC voltage; and changing a direction of movement of the plurality of nanofibers between the spinneret and the collector with a plurality of magnets having a magnetic field by adjusting the magnetic field.

Processing reinforcing fiber products to recover reinforcing fibers by removing other material, such fiber sizing material and/or matrix material from the reinforcing fibers. The processing includes cosolvent treating the reinforcing fiber product with a cosolvent composition including a normally-liquid first solvent portion and a normally-gaseous second solvent portion under conditions of temperature and pressure at which the cosolvent composition is in the form of a single fluid phase that is a liquid or a supercritical fluid. The processing may be performed in a continuous manner to recover the continuous reinforcing fibers in a continuous form.

A method for making a turbine engine blade includes three-dimensionally weaving elongate fibers of a material selected from the group consisting of carbon, glass, silica, silicon carbide, silicon nitride, aluminum, aramid, aromatic polyamide, and combinations thereof to create a woven preform including a single piece of woven material. The woven preform includes continuous warp fibers extending along a first direction, continuous weft fibers extending along a second direction substantially normal to the first direction, and continuous fibers extending in a third direction substantially normal to the first and the second directions. The woven preform includes an airfoil region extending along the first direction and an arrangement of flaps extending along the second direction. The flaps are folded into a plane substantially normal to a plane of the airfoil region to form a shaped woven preform. The shaped woven preform is densified with a ceramic matrix.

The method of the present invention for making a BNNT fabric comprises dispersing Boron-Nitride nanotubes at loading greater than 5 weight % in an electrospinning delivery solution; electrospinning the delivery solution onto a collector thereby forming a mat comprised of BNNT-PAN nano fibers; and, finally removing any electrospinning delivery solution from the mat leaving a fabric of intertwined Boron-Nitride nanotubes.

Equipment for manufacturing ceramic wires is disclosed. The manufacturing equipment can comprise a deposition unit for depositing the ceramic wire on a wire substrate, a loading/unloading unit having a release reel for providing the wire substrate to the deposition unit and a coiling reel for discharging the wire substrate from the deposition unit, and at least one buffer unit arranged between the loading/unloading unit and the deposition unit. The buffer unit may continuously be providing the wire substrate to the deposition unit or continuously winding the wire substrate from the deposition unit when the release reel or the coiling reel is replaced.

Ceramic matrix composite components and methods for fabricating ceramic matrix composite components are provided. In one example, a ceramic matrix composite component includes a ceramic matrix composite body. The ceramic matrix composite body includes a layer-to-layer weave of ceramic fibers and a layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers disposed adjacent to the layer-to-layer weave. When stressed, the ceramic matrix composite body forms a relatively high through-thickness stress region and a relatively high in-plane bending stress region. The layer-to-layer weave is disposed through the relatively high through-thickness stress region and the layer of 1D/2D fabric is disposed through the relatively high in-plane bending stress region.

The present invention relates Inorganic fibres having a composition comprising: 61.0 to 70.8 wt % SiO.sub.2; 27.0 to 38.9 wt % CaO; 0.10 to 2.0 wt % MgO; and optionally, an amount of other components providing a balance up to 100 wt %. A sum of SiO.sub.2 and CaO is greater than or equal to 97.8 wt % and wherein the amount of the other components, when present, comprise no more than 0.80 wt % Al.sub.2O.sub.3.

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

A microstructure comprises a plurality of interconnected units wherein the units are formed of graphene tubes. The graphene tubes may be formed by photo-initiating the polymerization of a monomer in a pattern of units to form a polymer microlattice, removing unpolymerized monomer, coating the polymer microlattice with a metal, removing the polymer microlattice to leave a metal microlattice, depositing graphitic carbon on the metal microlattice, converting the graphitic carbon to graphene, and removing the metal microlattice. A ceramic may be deposited on the graphene and another graphene layer may be deposited on top of the ceramic to create a multi-layered sp.sup.2-bonded carbon tube.

A method for fabricating a ceramic material includes impregnating a porous structure with a mixture that includes a preceramic polymer and a filler. The filler includes at least one free metal. The preceramic polymer material is then rigidized to form a green body. The green body is then thermally treated to convert the rigidized preceramic polymer material into a ceramic matrix located within pores of the porous structure. The same thermal treatment or a second, further thermal treatment is used to cause the at least one free metal to move to internal porosity defined by the ceramic matrix or pores of the porous structure.