Abstract: Methods for producing a high temperature oxidation and hot corrosion resistant MCrAlX coating on a superalloy substrate include applying an M-metal, chromium, and aluminum or an aluminum alloy comprising a reactive element to at least one surface of the superalloy component by electroplating at electroplating conditions below 100° C. in a plating bath thereby forming a plated component and heat treating the plated component.

Abstract: A coating for spark plugs and engine parts is resistant to fouling. The coating may be applied to the spark plug or engine part by dipping the part in a sol gel solution, ensuring it wets the part, and extracting it at a slow, controlled rate. As the part is allowed to dry, the sol gel reacts with moisture in the air to form a thin oxide film. Unlike conventional sol gel applications, which apply the oxide directly to the part, the present invention may form an oxide coating, in situ, while drying in place on the part.

Abstract: Exemplary embodiments of the invention provide barrier coated substrates and methods of coating a substrate with a barrier coating derived from sol gels. An example includes a barrier coated aerospace component that is subject to hot salt corrosion during use. The barrier coating is derived from oxidation of a coating composition that includes at least one sol gel. The barrier coating resists hot salt corrosion for an incubation period of such duration that an uncoated superalloy substrate under the same conditions would suffer corrosion to a depth of about 2.0 mils. Methods of applying the barrier coating include the steps of selecting a first liquid sol gel and wetting surfaces of the superalloy substrate with the selected first liquid sol gel. The wetted surfaces of the superalloy substrate are subjected to heat treatment. The heat treatment includes sintering of sol gel to oxide to produce a barrier coating.

Abstract: A coated component is provided comprising a silicon-based substrate and a braze layer overlying the silicon-based substrate. The braze layer comprises silicon, tantalum, and a metal element having substantially the same melt temperature with silicon as tantalum has with silicon. The braze layer further comprises ceramic particles. Protective coatings are also provided.

Abstract: Methods for producing a high temperature oxidation resistant coating on a superalloy component and the coated superalloy component produced thereby are provided. Aluminum or an aluminum alloy is applied to at least one surface of the superalloy component by electroplating in an ionic liquid aluminum plating bath to form a plated component. The plated component is heat treated at a first temperature of about 600° C. to about 650° C. and then further heat treated at a second temperature of about 700° C. to about 1050° C. for about 0.50 hours to about two hours or at a second temperature of about 750° C. to about 900° C. for about 12 to about 20 hours.

Abstract: Methods for producing a high temperature oxidation and hot corrosion resistant MCrAlX coating on a superalloy substrate include applying an M-metal, chromium, and aluminum or an aluminum alloy comprising a reactive element to at least one surface of the superalloy component by electroplating at electroplating conditions below 100° C. in a plating bath thereby forming a plated component and heat treating the plated component.

Abstract: Dispersion strengthened aluminum base alloys are shaped into metal parts by high strain rate forging compacts or extruded billets composed thereof. The number of process steps required to produce the forged part are decreased and strength and toughness of the parts are increased. The dispersion strengthened alloy may have the formula Albal,Fea,SibXc, wherein X is at least one element selected from Mn, V, Cr, Mo, W, Nb, and Ta, “a” ranges from 2.0 to 7.5 weight-%, “b” ranges from 0.5 to 3.0 weight-%, “c” ranges from 0.05 to 3.5 weight-%, and the balance is aluminum plus incidental impurities. Alternatively, the dispersion strengthened alloy may be described by the formula Albal,Fea,SibVdXc, wherein X is at least one element selected from Mn, Mo, W, Cr, Ta, Zr, Ce, Er, Sc, Nd, Yb, and Y, “a” ranges from 2.0 to 7.5 weight-%, “b” ranges from 0.5 to 3.0 weight-%, “d” ranges from 0.05 to 3.5 weight-%, “c” ranges from 0.02 to 1.50 weight-%, and the balance is aluminum plus incidental impurities.

Abstract: Components and methods of forming a protective coating system on the components are provided. In an embodiment, and by way of example only, the component includes a ceramic substrate and a braze layer disposed over the ceramic substrate. The braze layer includes a silicon matrix having a first constituent and a second constituent that is different than the first constituent. The first constituent forms a first intermetallic with a portion of the silicon matrix and the second constituent forms a second intermetallic with another portion of the silicon matrix, wherein the braze layer is formulated to provide a barrier to oxygen diffusion therethrough.

Abstract: A turbine engine component includes an electron beam-physical vapor deposition thermal barrier coating covering at least a portion of a substrate. The thermal barrier coating includes an inner layer having a columnar-grained microstructure with inter-columnar gap porosity. The inner layer includes a stabilized ceramic material. The thermal barrier coating also includes a substantially non-porous outer layer, covering the inner layer and including the stabilized ceramic material. The outer layer is deposited with continuous line-of-sight exposure to the vapor source under oxygen deficient conditions. The outer layer may further comprise a dopant oxide that is more readily reducible than the stabilized ceramic material. During deposition, the outer layer may also have an oxygen deficient stoichiometry with respect to the inner layer. Oxygen stoichiometry in the outer layer may be restored by exposure of the coated component to an oxidizing environment.

Abstract: A coated component is provided comprising a silicon-based substrate and a braze layer overlying the silicon-based substrate. The braze layer comprises silicon, tantalum, and a metal element having substantially the same melt temperature with silicon as tantalum has with silicon. The braze layer further comprises ceramic particles. Protective coatings are also provided.

Abstract: An armor material, body armor articles, and methods of manufacturing the armor material are provided. In an embodiment, by way of example only, the armor material includes a first plate, a second plate, and a powder material. The first plate includes a layer comprising a metallic material. The second plate is spaced apart from the first plate and includes a layer comprising a ceramic material. The powder material is disposed between the first and the second plates, and comprises loose powder including at least one of a plurality of ceramic particles and a plurality of metallic particles.

Abstract: A coating for spark plugs and engine parts is resistant to fouling. The coating may be applied to the spark plug or engine part by dipping the part in a sol gel solution, ensuring it wets the part, and extracting it at a slow, controlled rate. As the part is allowed to dry, the sol gel reacts with moisture in the air to form a thin oxide film. Unlike conventional sol gel applications, which apply the oxide directly to the part, the present invention may form an oxide coating, in situ, while drying in place on the part.

Abstract: Methods for producing a high temperature oxidation resistant coating on a superalloy component and the coated superalloy component produced thereby are provided. Aluminum or an aluminum alloy is applied to at least one surface of the superalloy component by electroplating in an ionic liquid aluminum plating bath to form a plated component. The plated component is heat treated at a first temperature of about 600° C. to about 650° C. and then further heat treated at a second temperature of about 700° C. to about 1050° C. for about 0.50 hours to about two hours or at a second temperature of about 750° C. to about 900° C. for about 12 to about 20 hours.

Abstract: Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system comprises an aluminide-comprising bond coating disposed on a substrate, a thermal barrier coating overlying the aluminide-comprising bond coating, and a silicate layer interposed between the thermal barrier coating and the aluminide-comprising bond coating.

Abstract: Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary method of fabricating a protective coating system on a substrate comprises forming a bond coating on the substrate, forming a silicate layer on the bond coating, forming a thermal barrier coating overlying the silicate layer, and heating the thermal barrier coating.

Abstract: According to a method for forming a coating system on a turbine engine component substrate that comprises a nickel-based superalloy substrate having at least one refractory metal included therein, a nickel-based layer is formed on the substrate, the nickel-based layer comprising at least one active material selected from the group consisting of elemental silicon and a silicon compound. The at least one active material is then diffused into the substrate. An yttrium-modified platinum aluminide bond coating, or a MCrAlX bond coating, may be then formed over the active material-modified nickel-based layer.

Abstract: Methods are provided for forming coatings on substrates. In an embodiment, a method includes forming a first metal layer on the substrate, the first metal layer comprising a first precious metal, electrodepositing an active element over the first metal layer to form an active element layer, the active element selected from the group consisting of yttrium, scandium, and a lanthanide series element, applying a second metal layer over the active element layer, the second metal layer consisting essentially of a metal selected from a group consisting of a second precious metal, nickel, and cobalt, heating the substrate including the first metal layer, the active element layer, and the second metal layer to form a diffusion-alloyed layer over the substrate, adding aluminum to the diffusion-alloyed layer, and heating the substrate to diffuse and react the aluminum with the diffusion-alloyed layer to form a modified precious metal aluminide coating on the substrate.

Abstract: A catalyst system for removing one or more components from a fluid stream includes a binder layer and a plurality of catalyst structures affixed to, and protruding from, the binder layer such that the catalyst structure surface is directly exposed to the fluid stream. Methods for preparing a catalyst system, and for selectively removing components from a fluid stream via a catalyst system are also disclosed.

Abstract: A method for coating a polymeric or composite component surface with a wear and erosion resistance metal layer includes the step of cold gas-dynamic spraying a powder mixture onto the polymeric or composite component surface to form the wear and erosion resistance metal layer. The mixture may include at least one metal powder and at least one hard particle powder.

Abstract: An article having a thermal barrier coating includes a superalloy substrate having a columnar grained ceramic coat formed thereon. The ceramic coat includes a nanolaminate region comprising repeating layers of ceramic material with each layer being less than 500 nm in thickness, with dispersions of metal oxide doping material situated between each of the layers. The ceramic coat further includes a non-doped region having a thickness greater than 500 nm adjacent to the nanolaminate region, the non-doped region including one layer or a plurality of adjacent layers of ceramic material without dispersions of metal oxide doping material situated between each of the layers. In one embodiment, and by way of example only, a bond coat is formed between the substrate and the columnar grained ceramic coat. According to another embodiment, the superalloy substrate forms an adherent alumina scale, and no bond coat is necessary.