Abstract: A fabrication apparatus for fabricating ceramic structures of controlled size and composition is provided. The fabrication apparatus includes an additive manufacturing machine configured to dispense preceramic materials in a printed pattern, the printed pattern corresponding to the ceramic structures of the controlled size and composition, a radiation emitter configured to emit curing radiation toward the printed pattern to cure the preceramic materials and a lamp element configured to shine light on the preceramic materials to convert the preceramic materials to ceramics.

Abstract: A fabrication apparatus for fabricating ceramic structures of controlled size and composition is provided. The fabrication apparatus includes an additive manufacturing machine configured to dispense preceramic materials in a printed pattern, the printed pattern corresponding to the ceramic structures of the controlled size and composition, a radiation emitter configured to emit curing radiation toward the printed pattern to cure the preceramic materials and a lamp element configured to shine light on the preceramic materials to convert the preceramic materials to ceramics.

Abstract: Disclosed is a method of coating a high temperature fiber including depositing a base material on the high temperature fiber using atomic layer deposition, depositing an intermediate material precursor on the base material using molecular layer deposition, depositing a top material on the intermediate material precursor or the intermediate layer using atomic layer deposition, and heat treating the intermediate precursor. The intermediate material in the final coating includes a structural defect, has lower density than the top material or a combination thereof. Also disclosed are the coated high temperature fiber and a composite including the high temperature fiber.

Abstract: A method of fabricating a ceramic component includes hot pressing a composite component with a glass powder / filler cover mixture to form a consolidated glass-based coating on the composite component.

Abstract: A coating system for a turbine engine component is disclosed. The coating system includes a substrate, an optional bond coat, a synthetic oxide layer and a top coat. The synthetic oxide layer is formed by atomic layer deposition and includes two or more oxides.

Abstract: A coating system for a turbine engine component is disclosed. The coating system includes a substrate, an optional bond coat, a synthetic oxide layer and a top coat. The synthetic oxide layer is formed by atomic layer deposition and includes two or more oxides.

Abstract: Disclosed is a method of coating a high temperature fiber including depositing a base material on the high temperature fiber using atomic layer deposition, depositing an intermediate material precursor on the base material using molecular layer deposition, depositing a top material on the intermediate material precursor or the intermediate layer using atomic layer deposition, and heat treating the intermediate precursor. The intermediate material in the final coating includes a structural defect, has lower density than the top material or a combination thereof. Also disclosed are the coated high temperature fiber and a composite including the high temperature fiber.

Abstract: 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.

Abstract: A brake component is disclosed. In various embodiments, the brake component includes a ceramic matrix composite (CMC) structure including a plurality of nominally dense plies, interleaved with a plurality of interlayers, wherein the plurality of nominally dense plies and the plurality of interlayers are bonded by at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a localized heating process. In various embodiments, the brake component is a rotor disk or a stator disk.

Abstract: A method for forming in situ a boron nitride reaction product locally on a reinforcement phase of a ceramic matrix composite material includes the steps of providing a ceramic matrix composite material having a fiber reinforcement material; and forming in situ a layer of boron nitride on the fiber reinforcement material.

Abstract: A fabrication apparatus for fabricating ceramic structures of controlled size and composition is provided. The fabrication apparatus includes an additive manufacturing machine configured to dispense preceramic materials in a printed pattern, the printed pattern corresponding to the ceramic structures of the controlled size and composition, a radiation emitter configured to emit curing radiation toward the printed pattern to cure the preceramic materials and a lamp element configured to shine light on the preceramic materials to convert the preceramic materials to ceramics.

Abstract: Disclosed is a method of making high temperature fiber including chemically bonding high temperature material to a fiber template at a first temperature to form a precursor fiber and processing the precursor fiber at a second temperature to form the high temperature fiber. The first temperature does not equal the second temperature. Also disclosed are high temperature fibers made by the method.

Abstract: Disclosed is a method of making high temperature fiber including incorporating an inorganic atom into a polymer precursor fiber to form a modified polymer precursor fiber and converting the modified polymer precursor fiber to a high temperature fiber having a bonded inorganic atom.

Abstract: Disclosed is a method of coating a high temperature fiber including depositing a base material on the high temperature fiber using atomic layer deposition, depositing an intermediate material precursor on the base material using molecular layer deposition, depositing a top material on the intermediate material precursor or the intermediate layer using atomic layer deposition, and heat treating the intermediate precursor. The intermediate material in the final coating includes a structural defect, has lower density than the top material or a combination thereof. Also disclosed are the coated high temperature fiber and a composite including the high temperature fiber.

Abstract: 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.

Abstract: A method for repairing a printed circuit board (PCB) including the steps of presenting a PCB having an initial coating on a surface thereof, removing the initial coating from the surface of the PCB at least in an area in need of repair, and recoating at least the area of the PCB in need of repair by way of atomic layer deposition.

Abstract: A method of producing a ceramic matrix composite material component is provided. The method includes that steps of: a) producing a preform having one or more ceramic constituents, the preform being porous with internal voids; and b) applying at least one layer of a first material to the preform using an atomic layer deposition (ALD) process to decrease a porosity of the preform.

Abstract: A method of applying a corrosion barrier includes applying a conversion coat onto a component and applying a layer of ceramic material over the conversion coat by atomic layer deposition. The conversion coat and the ceramic material provide corrosion resistance. A component with a corrosion barrier is also disclosed.

Abstract: A method for forming in situ a boron nitride reaction product locally on a reinforcement phase of a ceramic matrix composite material includes the steps of providing a ceramic matrix composite material having a fiber reinforcement material; and forming in situ a layer of boron nitride on the fiber reinforcement material.

Abstract: A coating system for a turbine engine component is disclosed. The coating system includes a substrate, an optional bond coat, a synthetic oxide layer and a top coat. The synthetic oxide layer is formed by atomic layer deposition and includes two or more oxides.