Abstract: A composition, a machine component coated with the same, and a method of coating the machine component are provided. The composition includes a CoNiCrAlY alloy, where three or more elements of the CoNiCrAlY alloy are present in equimolar amounts, one of the three or more elements of the CoNiCrAlY alloy being aluminum (Al), and where a molar fraction of Al is between about 0.20 and about 0.25. The composition further includes a transition metal boride including at least one of: cobalt boride (Co2B), titanium boride (TiB2), zirconium boride (ZrB2), tantalum boride (TaB2), niobium boride (NiB2), or molybdenum boride (Mo2B), and a refractory alloy.

Abstract: A coated component includes a component having a surface, and a solid lubricant wear resistant coating on the surface, wherein the solid lubricant wear resistant coating includes a solid lubricant phase with a negative thermal expansion coefficient material dispersed therein. The component may also include a coating having oleophilic or porous properties disposed on portions thereof, and a coating having oleophobic properties disposed on portions thereof.

Abstract: A thermal insulation assembly for a duct through which high temperature fluid, greater than 500 Fahrenheit, passes. The thermal insulation assembly can experience pressures less than 80 kilopascals and can be included in a turbine engine. The thermal insulation assembly includes a first foil layer confronting the duct, a second foil layer spaced from the first foil layer, an insulation layer between the first foil layer and the second foil layer, an opacifier layer provided on the insulation layer, and a reflective layer applied to the opacifier layer.

Abstract: Methods are provided for forming a thermal barrier coating having a non-linear compositional gradient and/or a non-linear porosity gradient, along with coated components formed therefrom. The method includes spraying a deposition mixture of a first composition and a second composition via a solution precursor plasma spray apparatus onto a surface of a substrate; while spraying the deposition mixture, adjusting at least one deposition parameter such that the thermal barrier coating is formed with the non-linear gradient.

Abstract: A coating method is provided. The coating method includes applying, via electrophoretic deposition or slurry deposition, an overcoat composition on an outer surface of a thermal barrier coating system on a substrate. The overcoat composition includes a coating material comprising a plurality of particles having a particle size of less than 1000 nm. The method includes sintering the overcoat composition in the presence of one or more sintering aids to form an overcoat layer having a surface roughness of less than 1 micrometer.

Abstract: A composition comprising an yttria-rare earth-doped zirconium oxide is provided that has a tetragonal structure and a formula: YaLnbCexZr1-a-b-xO2-? where Ln is a mixture of rare earth elements; 0.01?a?0.051; 0.01?b?0.051 such that Y and each rare earth element is included in the composition in substantially equal molar amounts; 0.05?(a+b)?0.07; 0?x?0.051; and 0???0.05. Methods of forming a coating that includes this composition, along with the resulting coated components, are also provided.

Abstract: A composition is provided of a rare earth-doped zirconium oxide having a tetragonal structure and having a formula: YaLnbTaxNbzZr1-a-b-x-zO2-? where Ln is a rare earth element or a mixture of rare earth elements; 0?a?0.06; 0.06?b?0.12; 0?x?0.1; 0?z?0.1; 0.08?(x+z)?0.1; 0.16?(a+b+x+z)?0.22; and 0.01???0.05. Methods of forming a coating with this composition, along with the coated components, are also provided.

Abstract: Layered barrier cans and methods of producing the same are disclosed herein. An example shroud disclosed herein includes an inner shell including a first non-metallic material, an outer shell including the first non-metallic material or a second non-metallic material, and a metal core shell positioned between the inner shell and the outer shell.

Abstract: Coated components, along with methods of their formation, are provided. The coated component may include a substrate having a surface and a thermal barrier coating on the surface of the substrate. The thermal barrier coating includes a plurality of elongated surface-connected voids therein, and wherein the thermal barrier coating comprises a plurality of nonspherical particles within a thermal barrier material.

Abstract: A composition, a machine component coated with the same, and a method of coating the machine component are provided. The composition includes a CoNiCrAlY alloy, where three or more elements of the CoNiCrAlY alloy are present in equimolar amounts, one of the three or more elements of the CoNiCrAlY alloy being aluminum (Al), and where a molar fraction of Al is between about 0.20 and about 0.25. The composition further includes a transition metal boride including at least one of: cobalt boride (Co2B), titanium boride (TiB2), zirconium boride (ZrB2), tantalum boride (TaB2), niobium boride (NiB2), or molybdenum boride (Mo2B), and a refractory alloy.

Abstract: A composition comprising a rare earth-doped zirconium/hafnium oxide is provided that has a defect-fluorite structure or a pyrochlore structure. The rare earth-doped zirconium/hafnium oxide has a formula: (Ln1aLn2aLn3aLn4aLn5b)2M2O7 where each of Ln1, Ln2, Ln3, Ln4, and Ln5 is a different rare earth element such that Ln1 and M have a first atomic radius ratio that is 1.35 to 1.45, Ln2 and M have a second atomic radius ratio that is 1.35 to 1.45, Ln3 and M have a third atomic radius ratio that is 1.46 to 1.78, and Ln4 and M have a fourth radius ratio that is 1.46 to 1.78; a is 0.2 or 0.25; b is 0.2 when a is 0.2, and b is 0 when a is 0.25; and M is Zr, Hf, or a mixture thereof. Methods of forming a coating that includes this composition, along with the resulting coated components, are also provided.

Abstract: A composition comprising a rare earth solid solution, at least one of HfO2 and CaZrO3/MgZrO3; and balance ZrO2. The rare earth solid solution may include Gd2O3 and Lu2O3. In another example, the rare earth solid solution may include Gd2O3, Lu2O3, and at least one of Yb2O3 and Sm2O3.

Abstract: An coated component is provided. The coated component includes a component substrate and bond coat layer comprising silicon deposited on the component substrate. A composite layer is deposited on the bond coat layer. The composite layer includes a rare earth disilicate and a second phase material. The composite layer has a thickness (T) from about 0.05 mm to about 2.25 mm, and a coefficient of thermal expansion that is different by a value of about 0 to about 2.25 from a coefficient of thermal expansion of the component substrate upon which the bond coat layer is deposited. Coated gas turbine engine components are also provided.

Abstract: A thermal insulation system for an aerospace duct through which high temperature fluid, greater than 500 F, passes. The thermal insulation system can experience pressures less than 80 kilopascals and can be included in a turbine engine. The thermal insulation system includes at least a first foil layer confronting the duct, an insulation layer confronting the first foil layer, a second foil layer confronting the insulation layer, and at least one coating applied to any one of the layers.

Abstract: A high entropy ceramic (HEC) composition includes at least three different rare earth (RE) oxides and at least one of hafnium dioxide (HfO2) and zirconia oxide (ZrO2). The at least three different rare earth oxides being equimolar fractions. In one aspect, the high entropy ceramic (HEC) composition can be used in a thermal barrier coating.

Abstract: An anti-fretting coating composition that is operationally stable at temperatures of 800° F. to 2650° F. is provided. The anti-fretting coating composition primarily includes cobalt and aluminum oxide and may also include other modifying phases that enhance the overall tribological performance. A component coated with the anti-fretting coating composition is also provided. The component includes a substrate having a first contact surface shaped to cooperate with a second contact surface of an abutting member in a manner which can develop wear between the first contact surface and the second contact surface. The first contact surface includes an anti-fretting coating thereon formed from the disclosed anti-fretting coating composition.

Abstract: A method of forming a coating on a component of an electrical machine is presented. The method includes coating a surface of the component with a ceramic material, via an electrophoretic process, to form a first coating. The method further includes contacting the first coating deposited by the electrophoretic process with a polymeric material to form a second coating. The method furthermore includes curing or melting the polymeric material in the second coating to form the coating including the ceramic material dispersed in a polymer matrix.

Abstract: A filled abradable seal component, an associated method of manufacturing, and a turbomachine including the filled abradable seal component are disclosed. The method includes positioning the abradable seal component including a plurality of honeycomb cells, applying a filler material on the abradable seal component to fill the plurality of honeycomb cells, and curing the filler material at a temperature below 250 degrees Celsius to produce the filled abradable seal component. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate.

Abstract: A method of forming a coating on a component of an electrical machine is presented. The method includes coating a surface of the component with a ceramic material, via an electrophoretic process, to form a first coating. The method further includes contacting the first coating deposited by the electrophoretic process with a polymeric material to form a second coating. The method furthermore includes curing or melting the polymeric material in the second coating to form the coating including the ceramic material dispersed in a polymer matrix.

Abstract: A filled abradable seal component, an associated method of manufacturing, and a turbomachine including the filled abradable seal component are disclosed. The method includes positioning the abradable seal component including a plurality of honeycomb cells, applying a filler material on the abradable seal component to fill the plurality of honeycomb cells, and curing the filler material at a temperature below 250 degrees Celsius to produce the filled abradable seal component. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate.