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253results about How to "Reduce coating" patented technology

Method for repairing coated components

ActiveUS20050106316A1Increase ceramic spallation lifeReduce coatingMolten spray coatingLayered productsTurbine bladeAlloy
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, 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 reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, 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.
Owner:GENERAL ELECTRIC CO

Method for repairing coated components

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, 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 reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, 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.
Owner:GENERAL ELECTRIC CO

Nitrogen-doped carbon-coated molybdenum selenide/graphene core-shell array sandwich structure composite material, preparation method and application thereof

The invention discloses a nitrogen-doped carbon-coated molybdenum selenide/graphene core-shell array sandwich structure composite material, a preparation method and application thereof. The method includes: dissolving selenium powder in hydrazine hydrate to form a solution A; dissolving a sodium molybdate dehydrate solution in water to form a solution B; mixing the solutions to form a reaction solution, placing a vertical grapheme collector electrode material growing on a carbon cloth in the reaction solution to carry out hydrothermal reaction, and then conducting washing and drying to obtain a VG-MoSe2 core-shell array structure; dissolving dopamine hydrochloride in water, then soaking the VG-MoSe2 core-shell array structure in the dopamine hydrochloride aqueous solution, carrying out water bath polymerization, and performing washing drying; and carbonizing the dopamine polymerized core-shell array structure under high temperature condition in protective atmosphere, thus obtaining the nitrogen-doped carbon-coated molybdenum selenide/graphene core-shell array sandwich structure composite material. When used as a sodium ion negative electrode material, the constructed composite material has high reversible charge-discharge capacity, long cycle life and excellent rate performance.
Owner:ZHEJIANG UNIV

Method for repairing coated components using NiAl bond coats

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.
Owner:GENERAL ELECTRIC CO
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