Abstract: A remote temperature measurement system for a gas turbine engine includes an optical emitter/receiver in communication with the control system and a probe system embedded within a component of the gas turbine engine, the probe system within a line-of-sight of the optical emitter/receiver, the control system operable to determine a local temperature of the component in response to optical communication with the probe system.

Abstract: A method of making a particulate for an additive manufacturing technique includes receiving particulate at a chemical vapor deposition (CVD) reactor, flowing a hydrocarbon gas into the CVD reactor, decomposing the hydrocarbon gas in the CVD reactor, and depositing a carbonaceous coating on the particulate using a product of the decomposed hydrocarbon gas. The coating deposited over the particulate has a reflectivity that is lower than the reflectivity the underlying particulate body to reduce an energy input requirement for purposes of fusing the particulate into a layer of an article using an additive manufacturing technique. In embodiments, the coated particulate can be received at an additive manufacturing apparatus and fused into a layer of an article as a metallic-carbon composite using a high-density energy source.

Abstract: An electrical device includes an electromagnetic component configured to generate a magnetic flux. The electromagnetic component includes a soft magnetically-conductive material configured to pass magnetic flux therethrough along a flux path. The soft magnetically-conductive material includes at least one grain oriented portion having metal grains that are oriented parallel with respect to the magnetic flux.

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 refractory metal alloy includes at least three metal components. At least one of the metal components is a refractory metal selected from the group of Mo, Nb, W, Ti, V, Cr, Mn, Y, Zr, Hf, Ta, Fe, Co, Al, Mn. The refractory metal alloy also includes two nonmetal components. The refractory metal alloy comprises non-trace amounts of each of the metal components and each of the nonmetal components. A component is also disclosed.

Abstract: An embodiment of a method includes fabricating a first single crystal boule having a uniform composition and grain orientation. The first uniform single crystal boule is divided into a first plurality of layered shapes. The shapes of the first plurality are stacked with at least a second plurality of layered shapes along a first axis. The second plurality of layered shapes have at least one physical aspect differing from at least one corresponding physical aspect of the first plurality of layered shapes. The first plurality of layered shapes and at least the second plurality of layered shapes are joined via a field assisted sintering technique (FAST) to form a bulk component.

Abstract: A system for treatment of atomized powder including a fluidized bed operable to treat feedstock alloy powders. A method of treating atomized powder including communicating an inert gas into a fluidized bed; communicating an atomized powder into the fluidized bed; and heating the atomized powder in the fluidized bed, eject the treated powders out of the fluidized bed to quench the powders.

Abstract: A system for treatment of atomized powder including a fluidized bed operable to treat feedstock alloy powders. A method of treating atomized powder including communicating an inert gas into a fluidized bed; communicating an atomized powder into the fluidized bed; and heating the atomized powder in the fluidized bed, eject the treated powders out of the fluidized bed to quench the powders.

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 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 solid oxide fuel cell or solid oxide electrolyzer includes a plurality of fuel cell layers stacked along a stacking axis. Each fuel cell layer including a stacked arrangement of elements including a cathode, an anode, an electrolyte located between the anode and the cathode, a support layer positioned at the anode opposite the electrolyte, and a separator plate located at the support layer opposite the anode. The separator plate is configured to contact the cathode of an adjacent fuel cell layer of the plurality of fuel cell layers. The separator plate defines a plurality of anode flow channels configured to deliver a fuel therethrough and a plurality of cathode flow channels configured to deliver an air flow therethrough. The separator plate is formed from a bulk metallic glass material.

Abstract: In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

Abstract: A system for forming a coating having a plurality of nanosized oxide particles on a work surface is disclosed. In various embodiments, the system includes a laser configured to direct a laser beam at a focal region on the work surface; and an applicator configured to direct a nanoparticle coated feedstock powder at the focal region of the work surface.

Abstract: A method is provided for additively manufacturing an object. This method includes: depositing a layer of material on a build surface; consolidating at least a portion of the layer of material together to form a portion of the object, the consolidating comprising directing an energy beam onto the material to form a melt pool; directing a beam of light onto the melt pool; detecting a response from the beam of light interacting with the melt pool; and determining a parameter of the melt pool based on the detected response.

Abstract: A remote temperature measurement system for a gas turbine engine includes an optical emitter/receiver in communication with the control system and a probe system embedded within a component of the gas turbine engine, the probe system within a line-of-sight of the optical emitter/receiver, the control system operable to determine a local temperature of the component in response to optical communication with the probe system.

Abstract: A method includes accessing a first model defining a shape of a part. The shape of the part is segregated into a plurality of predefined shapes selected from a library of predefined shapes. The predefined models for each of plurality of predefined shapes are assembled into a second model defining the shape of the part. The part is additively manufactured according to the second model.

Abstract: An additive manufactured multi-portion article includes a first portion of an article manufactured by a first additive manufacturing process; and a second portion of the article manufactured by a second additive manufacturing process different than the first additive manufacturing process, the second portion attached to the first portion.

Abstract: A process of forming an oxide dispersion strengthened alloy, comprises distributing an alloy powder on a platform; applying a uniform nanometer-scale metal oxide onto the alloy powder; applying an energy beam onto the alloy powder and the uniform nanometer-scale metal oxide; and forming an oxide dispersion strengthened alloy.

Abstract: A structural panel includes a first skin, a second skin and a core. The core is connected to the first skin and the second skin. The core includes a corrugated sheet of wire mesh that includes a plurality of corrugations. Each of the corrugations extends vertically between and engages the first skin and the second skin.

Abstract: Disclosed is a stator having: a first member having a first plurality of axially opposing ends including a first front end and a first back end mutually spaced along a first stator center axis, a first outer diameter (OD) side and a first inner diameter (ID) side, wherein first member comprises laminated steel; a plurality of cooling features disposed directly against the first member, wherein the plurality of fins spans between the first plurality of axially opposing ends of the first member, and wherein: the stator comprises a base layer disposed directly against the first member, between the first member and the cooling features, thereby reducing an interface contact resistance between the first member and the plurality of cooling features.