270 results about "Bond coating" patented technology

A plasma spray apparatus in the form of a gun is utilized to apply an antifoulant coating to marine vessels. The apparatus includes a plasma generator, an electrophoresis element, a heating element, a shield gas element, a liquid cooling system, a forced air system, and a vacuum system. The plasma generator ionizes gas to create a plasma stream, which is utilized in part to supply energy to the heating element that heats a powder material. The heated powder material is exposed to the electrophoresis element to create a covalently bonded coating material. The coating material is injected into the plasma stream and is applied to a target surface. The shield gas element injects a gas flow to surround and protect the plasma and coating material stream as the stream is in flight to the target surface. The liquid cooling system cools portions of the plasma generator and heating element. The forced air system cools a portion of the target surface as the coating material is being applied. The vacuum system removes fumes and stray particles during the application process.

A track pin bushing for cooperating with a track pin in an endless track has a tubular body with a metallurgically bonded wear-resistant coating and a method for forming such a coated track pin bushing is taught herein. The tubular body, formed of an iron-based alloy, has an outer surface that is carburized and quenched, i.e., case-hardened, in at least a section thereof. At least a portion of the case hardened section has been removed to a depth sufficient to expose a non-carburized layer of the iron-based alloy. A hard metal alloy slurry is disposed on the non-carburized layer and forms a metallurgical bond between the non-carburized layer and the coated unfused slurry by fusing the hard metal alloy. The thickness of the unfused slurry is adjusted to be from 1.67 to 2.0 times a final thickness of the wear-resistant coating. The wear-resistant coating comprises a fused, metal alloy comprising at least 60% iron, cobalt, nickel, or alloys thereof. The portion of the outer surface with the wear-resistant coating corresponds to a contact surface adapted to engage with a drive sprocket in the endless track of the track-type vehicle.

A strengthened bond coat for improving the adherence of a thermal barrier coating to an underlying metal substrate to resist spallation without degrading oxidation resistance of the bond coat. The bond coat comprises a bond coating material selected from the group consisting of overlay alloy coating materials, aluminide diffusion coating materials and combinations thereof. Particles comprising a substantially insoluble bond coat strengthening compound and having a relatively fine particle size of about 2 microns or less are dispersed within at least the upper portion of the bond coat in an amount sufficient to impart strengthening to the bond coat, and thus limit ratcheting or rumpling thereof.

A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.

A bi-layer bond coating for use on metal alloy components exposed to hostile thermal and chemical environment, such as a gas turbine engine, and the method for applying such coatings. The preferred coatings include a bi-layer bond coat applied to the metal substrate using high velocity oxy-fuel (HVOF) thermal spraying. Bi-layer bond coatings in accordance with the invention consist of a dense first inner layer (such as iron, nickel or cobalt-based alloys) that provides oxidation protection to the metal substrate, and a second outer layer having controlled porosity that tends to promote roughness, mechanical compliance, and promotes adherence of the thermal barrier coating (TBC). Preferably, the outer, less dense layer of the bi-layer bond coat is formed from a mixture of metallic powder and polyester to adjust and control the porosity, but without sacrificing mechanical compliance.

A thermal barrier coating comprises a bond coating 12 made of high temperature corrosion resistance superior to a substrate 11 and a thermal barrier coating 13 made of ZrO2 series ceramics formed on the bond coating. The thermal barrier coating has cracks extending in the direction of the thickness of the barrier coat. Substantially all of the tips of the cracks have a distance between the tips and the boundary at the substrate side.

A self-bonding coating composition for the production of electrical steel sheets cores comprising A) 100 parts per weight of at least one epoxy resin based on bisphenol-A-type and / or bisphenol-F-type, 100% of solids, B) 0.1 to 200 parts per weight of nano particles having an average radius ranging from 2 to 600 nm, C) 0 to 25 parts per weight of at least one curing agent selected from the group consisting of dicyandiamide, blocked isocyanate and Lewis acid or selected from the group consisting of phenolic resin, carboxylic acid, anhydride and Lewis acid, 100% of solids, D) 0.1 to 10 parts per weight of at least one additive, and E) 50 to 200 parts per weight of water or at least one organic solvent, ensuring increased re-softening temperatures as well as excellent bonding strength, corrosion resistance and electrical insulation of the coating.

The invention relates to a method for preventing corrosion and marine creature fouling on a ship propeller. Cathode protection, a ceramic insulating coating and a metallic antifouling coating are organically combined in the method. The method comprises the following steps of: removing scales on the surface of the copper alloy propeller, obtaining a uniform and rough surface, and spraying a metallic adhesive coating by adopting a thermal spraying method; preparing a metallic oxide ceramic insulating coating on the surface of the adhesive coating by adopting the thermal spraying method, wherein the ceramic insulating coating comprises single-component oxides such as Al2O3, Cr2O3 and the like and multi-component composite powder of TiO2 or SiO2 with low melting point; preparing the metallic antifouling coating on the ceramic insulating coating, wherein the metallic antifouling coating is made of pure copper or copper alloy with antifouling function; and meanwhile, performing cathode protection on the propeller. The ceramic and the metallic coating adopted in the method have higher bonding force and longer protection life, the current requirement of the ship cathode protection is reduced, the corrosion and marine creature fouling problems of the ship propeller can be simultaneously solved, and the ceramic and the metallic coating have obvious corrosion resistance and antifouling effect.

A combustion turbine component includes a combustion turbine component substrate and a bond coating on the combustion turbine component substrate. The bond coating may include Mn+1AXn (n=1,2,3) where M is selected from groups IIIB, IVB, VB, VIB, and VII of the periodic table of elements and mixtures thereof, where A is selected from groups IIIA, IVA, VA, and VIA of the periodic table of elements and mixtures thereof, and where X includes at least one of carbon and nitrogen. A thermal barrier coating may be on the bond coating.

A gas turbine engine component and coating system including a superalloy substrate having a coating system disposed thereon. A bond coating may be applied to the substrate. An adherent layer of ceramic material forming a thermal barrier coating is present on the bond coat layer. A topcoat layer overlies the thermal barrier coating. The topcoat layer includes greater than about 20 wt % yttria.

A method is provided for treating anti-corrosive steel surfaces, such an epoxy-coated ship's hull, in an environmentally improved manner, with an epoxy-silicone-adhesive paint, as a tiecoat, to provide for the subsequent application of silicone foul release coatings.

A plasma spray apparatus in the form of a gun is utilized to apply an antifoulant coating to marine vessels. The apparatus includes a plasma generator, an electrophoresis element, a heating element, a shield gas element, a liquid cooling system, a forced air system, and a vacuum system. The plasma generator ionizes gas to create a plasma stream, which is utilized in part to supply energy to the heating element that heats a powder material. The heated powder material is exposed to the electrophoresis element to create a covalently bonded coating material. The coating material is injected into the plasma stream and is applied to a target surface. The shield gas element injects a gas flow to surround and protect the plasma and coating material stream as the stream is in flight to the target surface. The liquid cooling system cools portions of the plasma generator and heating element. The forced air system cools a portion of the target surface as the coating material is being applied. The vacuum system removes fumes and stray particles during the application process.

A thermal barrier coating for a gas turbine component includes a bond coating layer, at least a first segmented columnar ceramic layer on the bond coating layer, and a particulate structure-stabilizing material disposed within a plurality of segmentation gaps within the columnar ceramic layer(s). The thermal barrier coating may further comprise, a second segmented columnar ceramic layer of yttria stabilized hafnia on the first segmented columnar ceramic layer, and an outer, continuous, non-segmented sealant layer covering the yttria stabilized hafnia layer to prevent ingress of extraneous materials into the segmentation gaps. Methods for depositing a thermal barrier coating on a substrate are also disclosed.

A durable protective coating may be formed by applying a thin layer of metastable alumina to a bond coating on a substrate. A thermal barrier coating may then be applied to the metastable alumina and the resulting part may be heat treated to transform the metastable alumina to a mixed alpha alumina having particles of the thermal barrier coating, such as zirconia in the case of an yttria stabilized zirconia thermal barrier coating, dispersed therein. The resulting thermal barrier coating may inhibit microbuckling of the thermally grown oxide scale that grows over time at the thermal barrier coating-bond coating interface.

According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, and improve upon the prior bond coat is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, Δx, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt−Δx, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.