Patent application number | Description | Published |
20100009092 | ECONOMIC OXIDATION AND FATIGUE RESISTANT METALLIC COATING - The present disclosure relates to an improved low-cost metallic coating to be deposited on gas turbine engine components. The metallic coating consists of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.0 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 0.0 to 9.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 0.0 to 43.0 wt % platinum, and the balance nickel. | 01-14-2010 |
20100047075 | Thermal Barrier Coating Compositions, Processes for Applying Same and Articles Coated with Same - A process of coating an article includes the steps of (1) applying a ceramic compound to at least one surface of an article to form a layer of ceramic compound; (2) applying at least one inert compound upon the ceramic compound layer to form a protective layer, wherein the at least one inert compound is composed of a first inert compound having a cubic crystalline structure of formula (I) A | 02-25-2010 |
20100098865 | DURABLE REACTIVE THERMAL BARRIER COATINGS - A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises at least one layer of a first material selected from the group consisting of a zirconate, a hafnate, a titanate, and mixtures thereof, which first material has been mixed with, and contains, from about 25 to 99 wt % of at least one oxide. The at least one oxide comprises at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, and yttrium. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described. | 04-22-2010 |
20100136241 | SILICATE RESISTANT THERMAL BARRIER COATING WITH ALTERNATING LAYERS - A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner. | 06-03-2010 |
20100154425 | STRAIN TOLERANT THERMAL BARRIER COATING SYSTEM - A method for forming a thermal barrier coating on a combustor panel or a fuel nozzle comprises the steps of: providing a component selected from the group consisting of a combustor panel, a bulkhead heat shield, and a fuel nozzle; optionally depositing a first layer of a metallic alloy onto the component; and depositing a ceramic composition layer using an electron beam physical vapor deposition technique. If the component is formed from a yttrium or other active element doped single crystal superalloy, the first layer may be omitted and the ceramic composition layer may be deposited directly onto a surface of the component. | 06-24-2010 |
20100189911 | Bond Coating and Thermal Barrier Compositions, Processes for Applying Both, and Their Coated Articles - A coated article includes an article having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer is disposed upon the surface. The bond coat layer includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer. A functionally graded material layer is applied upon the bond coat layer. The functionally graded material layer comprising molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer is then applied upon the functionally graded material layer. | 07-29-2010 |
20100189929 | COATING DEVICE AND DEPOSITION APPARATUS - A coating device for use with an electron beam vapor deposition apparatus includes a crucible portion and a nozzle portion. The crucible portion includes a gas inlet port, a heating zone for presenting a source coating material to be heated, and a flow passage exposed to the heating zone and fluidly connected with the inlet port. The nozzle portion of the coating device includes an outlet orifice fluidly connected with the flow passage for jetting a coating stream from the coating device. | 07-29-2010 |
20100196605 | Yttria-Stabilized Zirconia Coating with a Molten Silicate Resistant Outer Layer - A turbine engine component is provided which has a substrate, a yttria-stabilized zirconia coating applied over the substrate, and a molten silicate resistant outer layer. The molten silicate resistant outer layer is formed from gadolinia or gadolinia-stabilized zirconia. A method for forming the coating system of the present invention is described. | 08-05-2010 |
20100304037 | Thermal Barrier Coatings and Application Methods - A gas turbine engine component has a metallic substrate. A coating is on the substrate. A barrier coat is applied while varying a speed of the component rotation so as to provide a corresponding microstructure to the barrier coat. | 12-02-2010 |
20110033284 | STRUCTURALLY DIVERSE THERMAL BARRIER COATINGS - A coated article includes an article having at least one surface and a thermal barrier coating system disposed upon the at least one surface. The thermal barrier coating system has at least two layers, with each layer having a different microstructure. The microstructure of each layer may be any one of the following: columnar, amorphous, randomized, and splat-like. The thermal barrier coating system typically exhibits a thermal conductivity of no more than 16 BTU in/hr ft | 02-10-2011 |
20110086179 | THERMAL BARRIER COATING WITH A PLASMA SPRAY TOP LAYER - A turbine engine component has a substrate, a thermal barrier coating deposited onto the substrate, and a sealing layer of ceramic material on an outer surface of the thermal barrier coating for limiting molten sand penetration. | 04-14-2011 |
20110135895 | ARTICLE HAVING THERMAL BARRIER COATING - An article includes a metallic substrate and a tri-layer thermal barrier coating that is deposited on the metallic substrate. The tri-layer thermal barrier coating includes an inner ceramic layer, an outermost ceramic layer relative to the metallic substrate, and an intermediate ceramic layer between the inner ceramic layer and the outermost ceramic layer. The inner ceramic layer and the outermost ceramic layer are composed of respective first and second ceramic materials and the intermediate ceramic layers composed of a third, different ceramic material. The inner ceramic layer has a first thickness, the outermost ceramic layer has a second thickness, and the intermediate ceramic layer has a third thickness that is greater than the first thickness and the second thickness. | 06-09-2011 |
20110167634 | COATED GAS TURBINE ENGINE COMPONENT REPAIR - A method of repairing a component of a gas turbine engine that includes a metallic substrate, an existing aluminide coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer to the metallic substrate, and applying a new aluminide coating over the new metallic layer to form a new diffusion layer in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer forms a structural layer having a thickness selected to provide a specified contour to the component. | 07-14-2011 |
20110217464 | METHOD FOR APPLYING A THERMAL BARRIER COATING - A method and apparatus for forming thermally grown alpha alumina oxide scale on a substrate is provided. The method includes the steps of: a) providing a heating chamber having a heat source and an oxidizing gas source selectively operable to provide a stream of oxidizing gas; b) providing at least one substrate disposed in the heating chamber, which substrate has a composition sufficient to permit formation of an alpha alumina scale on one or more surfaces; c) maintaining a vacuum in the heating chamber at a level that inhibits formation of one or more low temperature oxides on the one or more surfaces of the substrate; d) heating at least one of the one or more surfaces of the substrate to a predetermined temperature at or above 1800 degrees Fahrenheit; and e) directing the stream of oxidizing gas at a controlled rate toward one or more heated surfaces of the substrate. | 09-08-2011 |
20110256421 | METALLIC COATING FOR SINGLE CRYSTAL ALLOYS - A metallic coating for use in a high temperature application is created from a nickel base alloy containing from 5.0 to 10.5 wt % aluminum, from 4.0 to 15 wt % chromium, from 2.0 to 8.0 wt % tungsten, from 3.0 to 10 wt % tantalum, and the balance nickel. The metallic coating has particular utility in protecting single crystal superalloys used in high temperature applications such as turbine engine components. | 10-20-2011 |
20130224453 | Spallation-Resistant Thermal Barrier Coating - In a method for coating a substrate, a ceramic first layer is suspension plasma sprayed and is at least about as tough as 7YSZ. A ceramic second layer is applied over the first layer and is less tough than the first layer. | 08-29-2013 |
20130260119 | Multi-Material Thermal Barrier Coating System - The thermal barrier coating system comprises a matrix of a first chemistry with multiple embedded second phases of a second chemistry. The matrix comprises a stabilized zirconia. The second regions comprise at least 40 mole percent of oxides having the formula Ln | 10-03-2013 |
20130260132 | HYBRID THERMAL BARRIER COATING - A tubine engine component has a substrate, a thermal barrier layer deposited onto the substrate, and a sealing layer of ceramic material deposited on an outer surface of the thermal barrier layer for limiting molten sand penetration. The thermal barrier layer and sealing layer are formed by suspension plasma spraying. A preferred sealing layer is gadolinium zirconate. | 10-03-2013 |
20140030497 | LOCALIZED TRANSITIONAL COATING OF TURBINE COMPONENTS - Different thermal barrier coatings are deposited on different regions of the surface of a component. A first thermal barrier coating comprising an erosion resistant yttria stabilized zirconia material is deposited on a first region of the surface of the component. A second thermal barrier coating comprising an oxidation and corrosion resistant gadolinia stabilized zirconia is deposited on a second region of the surface of the component. | 01-30-2014 |
20140065408 | THERMAL BARRIER COATING FOR GAS TURBINE ENGINE COMPONENTS - A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer. | 03-06-2014 |
20140127416 | ECONOMIC OXIDATION AND FATIGUE RESISTANT METALLIC COATING - The present disclosure relates to an improved low-cost metallic coating to be deposited on gas turbine engine components. The metallic coating consists of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to 1.0 wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.0 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 0.0 to 9.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 0.0 to 43.0 wt % platinum, and the balance nickel. | 05-08-2014 |
20140220324 | THERMAL BARRIER COATING HAVING OUTER LAYER - A component according to an exemplary aspect of the present disclosure includes, among other things, a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer includes a material that absorbs energy in response to an impact event along at least a portion of the outer layer. | 08-07-2014 |