265 results about "Bond coating" patented technology

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 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 directed vapor deposition (DVD) method and system for applying at least one bond coating on at least one substrate for thermal barrier coating systems. The method and system provides for alloy strengthening in high temperature metallic alloys that can be melt or solid state processed to materials that one applies by vapor deposition. The creep strengthened coating contains nanoscopic particles of oxides, nitrides, borides, carbides, and other materials which are formed by reactive codeposition. An approach for reactive codeposition is plasma assisted directed vapor deposition. Accordingly, the resultant structure may be utilized for, but not limited thereto, high temperature coatings, e.g. for protecting rocket or power turbines, or diesel engine components. The resultant structure is has a greatly extended lifetime attributed in part to the elimination of coating spallation by the “rumpling” mechanism.

Undercarriage assembly components of track-type machines having a metallurgically bonded wear-resistant coating and methods for forming such coated undercarriage assembly components is taught herein. The bodies of the undercarriage assembly components, formed of an iron-based alloy, have a hard metal alloy slurry disposed on a surface or into an undercut or channel and then fused to form a metallurgical bond with the iron-based alloy. 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 of the undercarriage assembly components having the wear-resistant coating corresponds to a wear surface of the component during operation of the endless track of the track-type vehicle.

A thermal barrier coating system on a base material includes a bond coat layer with a lower face in direct contact with the base material and an upper face, a first ceramic layer in direct contact with the upper face of the bond coating layer and a second ceramic layer disposed on an outermost surface of the coating system and configured to be exposed to hot gas. The first ceramic layer includes a layer, combination, mixture, alloy, blend or multilayer structure of at least one of yttria-stabilized zirconia with a yttria content in a range of 6-8 wt-%, YTaO4 doped zirconia, and titania doped zirconia. The second ceramic layer includes a layer, combination, mixture, alloy, blend or multilayer structure of at least one of YTaO4 doped zirconia, titania doped zirconia, scandia stabilized zirconia, ceria containing perovskite material, yttrium aluminium garnet material, Monazite material, and spinel material. A material of the second ceramic layer is different from a material of the first ceramic layer.

A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.

The invention relates to a strengthening coating of the surface of an annealing furnace roller and a preparation method thereof. The preparation of the strengthening coating on the surface of a roller base is performed by a selected hot-spray method. The strengthening coating comprises a bonded coating, a working coating and a transition coating between the bonded coating and the working coating. The proportion of alloy and ceramic in every coating is changed according to gradient, which means that the proportion of alloy is decreased gradually from inner to outer in every coating; while the proportion of ceramic is increased gradually and at last a gradient coating is formed. The invention not only ensures the working coating to have good antioxidation, abrasion resisting and anti- nodulation performances, but also improves the binding performance of strengthening coating and the roller base and improves the cohesion binding performance of the coating inner. Under the function of the strengthening coating of the annealing furnace roller surface made by the method of the invention, the service life of the furnace roller can be prolonged and the using cost and repairing cost can be decreased.

A bi-layer bond coating for use on metal alloy components exposed to hostile thermal and chemical environment, such as a gas turbine engine used to generate electricity and the method for applying such coatings. The preferred coatings include a bi-layer bond coat applied to the metal substrate, with both layers being applied using high velocity oxy-fuel (HVOF) thermal spraying. In one embodiment, bond coatings in accordance with the invention can be used in combination with a thermal barrier coating (“TBC”). However, the invention can also take other forms, such as a stand alone overlay coating. 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 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. Together, the layers enhance adherence to the substrate and improve the overall life of the coating system.

An article is disclosed in one embodiment of the invention as including a silicon-based ceramic substrate and a top coat. A bond coat is provided between the silicon-based ceramic substrate and the top coat. The bond coat is derived from a mixture containing preceramic polymer precursors, such as polycarbosilanes, polycarbosilazanes, or other silicocarbon polymers and pyrolyzed preceramic polymer precursors. A filler material may also be included in the mixture to modify the coefficient of thermal expansion (CTE) of the bond coat to more closely match the CTE of the silicon-based ceramic substrate, top coat, or both.

The present invention relates to a thermal barrier coating material having the chemical composition of (1−n)CeO₂-nZrO₂-0.5R₂O₃, where n is in the range of 0.9≧n≧0 and R is selected from a group consisting of Nd, Sm, Eu, Gd, Tb and combinations of at least two among them. It possesses a thermal expansion coefficient higher than 12×10⁻⁶ K⁻¹ from ambient temperature up to 1200° C. and superior to those of the presently widely-used thermal barrier coating materials. Even if it is subjected to long time calcinations at 1400° C. or is quenched to room temperature, it can still maintain the stable crystal structure. In addition, its thermal expansion trend matches quite well with that of the bond coating alloy. This is beneficial to the elimination of thermal stress generated between the substrate and the ceramic top coating during the thermal cycle and can significantly improve the thermal shock resistance of the coating. The present invention further relates to a method for producing a thermal barrier coating material and a method for preparing a thermal barrier coating.

A method for repairing a component is provided, where the component has a substrate comprising an outer surface and an inner surface and defining one or more grooves. Each groove extends at least partially along the outer surface of the substrate. The component further includes a structural coating, a bond coating, and a thermal bather coating. The groove(s) and the structural coating define one or more channels for cooling the component. The repair method includes removing the thermal barrier and bond coatings, removing at least a portion of the structural coating in a vicinity of a damaged portion of the component, performing a repair operation on the damaged portion of the component, applying a structural coating at least in a vicinity of the repaired portion of the component, and applying a bond coating and a thermal barrier coating. Additional repair methods are also provided.

A layer of a powdered material (4) is heated with an energy beam (10) such that at least one gas-generating agent (8) reacts to form at least one gaseous substance (14) to produce a void-containing coating (16) adhered to the surface of a substrate (2).

The powdered material may contain a metallic material, a ceramic material, or both, and may also contain at least one of a flux material (32) containing the gas-generating agent and an exothermic agent (64). The heating may occur using a laser beam and may induce a melting or sintering of the powdered material to produce the void-containing coating. A gas turbine engine component exhibiting improved thermal and mechanical properties may be formed to include the void-containing coating, which may take the form of a bond coating, a thermal barrier coating, or both.

A bond is created during gypsum board cure between a gypsum matrix and a tacky coating applied onto a glass fiber. The tacky coating is comprised of a polymer composed of methacrylic acid and dimethyldiallyammonium chloride. The polymer is dissolved in an acidic aqueous solution and is roller coated onto the glass fibers. The chopped glass fibers may also be placed in such an acidic solution, which is made alkaline by the addition of alkali, thereby precipitating the polymer out of solution as a tacky composition that produces a tacky coating on the glass fibers. The glass fibers with the tacky bond coating are incorporated in an alkaline gypsum slurry to form a gypsum board having a first and second facer sheet. The tacky coating on the glass fibers bonded to the gypsum matrix result in compliant load transfer between the gypsum matrix and the glass fibers, yielding improved flexure strength and nail pullout resistance.

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 M_n+1AX_n (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.

The invention relates to a method for performing supersonic atmospheric plasma spraying of zirconium oxide on the surface of a crystallizer copper plate. The method comprises the following steps: 1) performing surface pretreatment to a crystallizer copper plate matrix; 2) spraying a bonded coating on the surface of the pretreated matrix; 3) spraying a zirconium oxide base surface layer on the bonded coating; and 4) performing heat treatment to the product obtained in the step 3) and controlling the temperatures of the matrix and the coating below the matrix recrystallization temperature. By adopting the method, the bonding strength of the crystallizer copper plate matrix and the coating is high, the coating has high micro-hardness, low surface roughness and porosity and good high-temperature wear performance and thermal shock resistance. By applying the coating, the service life of the crystallizer can be effectively increased; and the coating can also be applied in the surface strengthening and repair of other copper or copper alloy elements.