Abstract:
A method for additively manufacturing a ceramic containing article includes selecting a ceramic precursor (110) and a curable resin (120), determining a ratio of the ceramic precursor (110) to the curable resin (120) required to achieve a desired ceramic microstructure, mixing the ceramic precursor (110) and the curable resin (120) according to the determined ratio, and iteratively building an article by sequentially applying a layer of the mixture and curing the layer using an additive manufacturing machine (10).
Abstract:
A nozzle (26) for additive manufacturing includes a plasma gas tube (31) operable to provide plasma gas (29) to a plasma flame (28), and a source material tube (36) arranged concentrically inside the plasma gas tube (31) such that source material (38) passes through the plasma flame (28). An apparatus and method for additive manufacturing are also disclosed.
Abstract:
A method of forming a protective shield (76) to protect an aircraft component (74) from EMI or energy bursts includes the steps of combining a carbon-based or silicon-based preceramic polymer precursor and a metallic precursor to form a dope, processing the dope to provide a deposit that includes nano-structures, post-processing the deposit to provide a nano-structure material with a uniformly distributed base metal or metal compound, and forming a protective shield (76) using the nano-structure material.
Abstract:
An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix of barium-magnesium alumino-silicate or SiO 2 , a dispersion of silicon oxycarbide particles in the matrix, and a dispersion of particles, of the other of barium-magnesium alumino-silicate or SiO 2 , in the matrix.
Abstract:
A method of fabricating a ceramic article includes providing a porous body that includes a plurality of fiber bundles that has an intra-bundle porosity and an inter-bundle porosity, infiltrating the intra-bundle porosity and the inter-bundle porosity with a mixture of particles in a liquid carrier, the particles having an average size selected with respect to at least the intra-bundle porosity, removing the liquid carrier from the porous body to deposit the particles in the intra-bundle porosity and in the inter-bundle porosity, infiltrating a preceramic polymer into a remaining intra-bundle porosity and a remaining inter-bundle porosity, and thermally converting the preceramic polymer to a ceramic material.
Abstract:
A method of preparing a composite preform includes applying a tacky preceramic-polymer-based adhesive on a first fiber array arranging a second fiber array on the first fiber array, the adhesive holding the first and second fiber arrays together. A composite component is also disclosed.
Abstract:
A heating circuit assembly (20) and method of manufacture includes an electrically conductive heating element (26) having a pattern (30). An electrically non-conductive substrate (22) is additive manufactured and secured to the element (26) for structural support. The substrate (22) has a topology (37) that generally aligns with the pattern (30) of the element (26) thereby reducing the assembly weight and minimizing substrate (22) material waste.
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 (206) extending between a first platform (204) and a second platform (202), wherein the airfoil, the first platform, and the second platform define the CMC structure. Nominally dense means 90-100% dense.
Abstract:
A method of making a ceramic composite component includes providing a fibrous preform (10) or a plurality of fibers (11), providing a first plurality of particles (20, 24), coating the first plurality of particles (20, 24) with a coating (22, 26) to produce a first plurality of coated particles (12, 14), delivering the first plurality of coated particles (12, 14) to the fibrous preform (10) or to an outer surface of the plurality of fibers (11), and converting the first plurality of coated particles (12, 14) into refractory compounds. The first plurality of particles (24) or the coating (22) comprises a refractory metal.