Abstract: A method is disclosed for laser cladding a substrate, comprising providing the substrate; depositing a first determined variable bead width of a material along a toolpath upon the substrate; depositing a second adjacent determined variable bead width of a material along the toolpath which overlaps the first determined variable bead width of deposited material; continuing to deposit a plurality of overlapping predetermined adjacent variable bead widths of a material until a first material layer is complete; forming a second material layer by depositing a plurality of overlapping predetermined variable bead widths of a material on top of the first material layer; and continuing to deposit material layers on top of deposited material layers until the cladding is complete; wherein the variable bead width of the deposited material is controlled by a computer having a plurality of input parameters to maintain an approximately constant percent of bead width overlap.

Abstract: Voids, cracks or other similar defects in substrates of thermal barrier coated superalloy components, such as turbine blades or vanes, are filled with resin, without need to remove substrate material surrounding the void by grinding or other processes. The resin is cured at a temperature under 200° C., eliminating the need for post void-filling heat treatment. The void-filled substrate and resin are then coated with a thermal barrier coating.

Abstract: A process for producing a repair coating on at least one metallic surface that is coated with at least one corrosion protection coating A applied with at least one composition selected from the group of pretreatment compositions, of organic compositions and of silicon compound(s) containing compositions, whereby the at least one corrosion protecting coating A has been at least partially removed in the area Z, whereby a thin corrosion protecting coating B containing at least one silicon compound is applied with a solution or dispersion containing at least one silane, at least one silanol, at least one siloxane, at least one polysiloxane or any mixture of these (=“siloxane composition”) on at least a part of the area Z.

Abstract: A method for treating a bushingless connecting rod, wherein the bushingless connecting rod comprises an elongated rod having a pin end configured to connect with a piston, and a crank end configured to connect with a crankshaft. The pin end includes a bore with an internal diameter. The method includes cleaning the pin end bore, masking and fixturing the pin end bore with elastomeric separators, and providing a high-phosphorous nickel alloy coating on the internal diameter of the pin end bore. The method may be applied to original equipment or to a worn engine undergoing a remanufacturing process.

Abstract: A method for restoring a silver oxide-containing hydrophilic coating includes heating the coating to a temperature between about 260° C. and about 540° C. and maintaining the coating at a temperature between about 260° C. and about 540° C. in an environment containing oxygen and ozone for less than 24 hours.

Abstract: In various embodiments, a sputtering target initially formed by ingot metallurgy or powder metallurgy and comprising a sputtering-target material is provided, the sputtering-target material (i) comprising a metal, (ii) defining a recessed furrow therein, and (iii) having a first grain size and a first crystalline microstructure. A powder is spray-deposited within the furrow to form a layer therein, the layer (i) comprising the metal, (ii) having a second grain size finer than the first grain size, and (iii) having a second crystalline microstructure more random than the first crystalline microstructure. Spray-depositing the powder within the furrow forms a distinct boundary line between the layer and the sputtering-target material.

Abstract: A method of locally repairing an aluminide coating (50) on a gas turbine engine nozzle guide vane (26) or a turbine blade (30,30B) comprises removing a damaged portion of the aluminide coating (50) from a portion (53) of the surface of the article. Any oxidised layer (54) is removed from the portion (53) of the surface of the article. Stoichiometric amounts of nickel and aluminium are placed on the portion (53) of the surface of the article using at least one foil (57). The stoichiometric amounts of nickel and aluminium are heat treated to form an aluminide patch coating (50B) on the portion (53) of the surface of the article and to bond the aluminide patch coating (50B) to the portion (53) of the surface of the article and to the aluminide coating (50) surrounding the aluminide patch coating (50B). The advantage is that the aluminide coating (50) surrounding the aluminide patch coating (50B) is not over aluminised.

Abstract: A rotary knife includes a handle, a rotatable annular blade, an expandle blade housing, and a housing support. The blade housing is movable relative to the handle between a blade-securing condition, in which the blade housing securely supports the blade for rotational operation, and a relatively expanded blade-releasing condition, in which the blade housing permits removal and installation of the blade relative to the blade housing. The housing support is coupled to the handle and supports the housing in the blade-securing and blade-releasing conditions. The support and housing include interengaging surfaces that contact one another in the blade-securing condition, with at least one of the interengaging surfaces including an applied high-friction coating.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: A process for producing a repair coating on at least one metallic surface that is coated with at least one corrosion protecting coating A applied with at least one composition selected from the group of pretreatment compositions, of organic compositions and of silicon compound(s) containing compositions, whereby the at least one corrosion protecting coating A has been at least partially removed in the area Z, whereby a thin corrosion protecting coating B containing at least one silicon compound is applied with a solution or dispersion containing at least one silane, at least one silanol, at least one siloxane, at least one polysiloxane or any mixture of these (=“siloxane composition”) on at least a part of the area Z.

Abstract: A method for controlled removal of a portion of a diffusion coating from a coated superalloy component and a method for rejuvenating a coated superalloy component are provided. The methods include providing the component having an oxide layer, an additive layer between the oxide layer and a diffusion zone, the diffusion zone being between the additive layer and a superalloy substrate of the superalloy component. The methods include selectively removing the oxide layer and a portion of the additive layer by grit blasting, wherein removing creates an exposed portion. Rejuvenating includes applying an aluminide coating to the exposed portion and heat treating at a preselected elevated temperature to form a rejuvenated protective aluminide coating on the superalloy component.

Abstract: A method for coating of a metallic article is provided. According to the method, the metal surface is coated with a composition which comprises a polymer or comprises a two-component system that reacts to form a polymer following application to the metal surface. The composition comprises 70-2700 meq/kg olefinic double bonds which leads to stronger adhesion and to increased corrosion resistance.

Abstract: A method of repairing a damaged abradable coating (48) on a surface (46) of a shroud (44) in an assembled gas turbine engine (10) comprises inserting a boroscope (60) through an aperture (52) in the casing (50) of the compressor (26) of the gas turbine engine (10). The boroscope (60) is arranged to carry a conduit (62). The boroscope (60) and hence the conduit (62) are directed to the damaged abradable coating (48) on the surface (46) of the shroud (44). A liquid abradable glue (64) is supplied through the conduit (62) and the liquid abradable glue (64) is directed onto the surface (46) of the shroud (44) in the compressor (26) of the gas turbine engine (10) to repair the damaged abradable coating (48).

Abstract: This disclosure relates to phosphate coatings that inhibit corrosion of metals, specifically coatings comprising acidic phosphate and alkaline metal oxide/hydroxide components. In one particular embodiment, phosphate-based coating formulations that reduce or eliminate corrosion of steel and other metals are disclosed. In other embodiments, methods for coating steel surfaces with acidic phosphate and alkaline metal oxide/hydroxide components to reduce or eliminate corrosion of the metal surfaces are disclosed.

Abstract: A method of locally repairing a coating (50) on a gas turbine engine nozzle guide vane (26) or a turbine blade (30,30B) comprises removing a damaged portion of the coating (50) from a portion (53) of the article. Any oxidized layer (54) is removed from the portion (53) of the surface of the article. Material is placed on the portion (53) of the article (26,30,30B) to form a patch coating (50B). The material is heated to form a patch coating (50B) on the portion (53) of the article (26,30,30B) and to bond the patch coating (50B) to the portion (53) of the article (26,30,30B) and to the coating surrounding the patch coating (50B). A high energy beam is impinged on the coating (50) and the high energy beam is moved from the periphery (60) of the patch coating (50B) to the periphery (62) of the coating (50) in a pattern (P) to uniformly heat the periphery (60) of the patch coating (50B) and the periphery (62) of the coating (50). The advantage is that a halo effect around the patch coating (50B) is obviated.

Abstract: In various embodiments, a sputtering target initially formed by ingot metallurgy or powder metallurgy and comprising a sputtering-target material is provided, the sputtering-target material (i) comprising a refractory metal, (ii) defining a recessed furrow therein, and (iii) having a first grain size and a first crystalline microstructure. A powder is spray-deposited within the furrow to form a layer therein, the layer (i) comprising the metal, (ii) having a second grain size finer than the first grain size, and (iii) having a second crystalline microstructure more random than the first crystalline microstructure. Spray-depositing the powder within the furrow forms a distinct boundary line between the layer and the sputtering-target material.

Abstract: A method for repairing an aluminum part having a worn portion is provided. In one embodiment, the method includes the steps of: (i) producing a first substantially non-porous coating over the worn portion utilizing a cold spray process wherein a powder mixture is propelled against the worn portion of the aluminum part, and (ii) anodizing the aluminum part to grow an aluminum oxide layer overlaying the first substantially non-porous coating. The powder mixture includes aluminum and an alloy media.

Abstract: Structural repair of cracks and other defects in superalloy components, such as steam or gas turbine blades in stationary or aero gas turbines, are performed by heating the blade substrate to an isothermal hold temperature below the substrate's incipient melting point and filling the crack with molten superalloy filler material. The molten filler solidifies into a casting and bonds with the component substrate at the isothermal hold temperature. Heat treatment processes are completed, so that the former crack is filled with cast superalloy material having identical or similar structural properties as the adjoining substrate superalloy material. The casting repair method may be utilized universally for all types of superalloy component defects, including those previously repaired by cosmetic, lower strength welding or brazing methods.

Abstract: A mating structure is provided and includes a first article having a first mating surface formed of a metallic material, a second article having a second mating surface, the second article being disposed such that the first and second mating surfaces mate with one another and a coating disposed on the first mating surface, which is formed of a material having a hardness that is higher than that of the metallic material of the first article. The coating has dimensions exceeded by corresponding dimensions of the first article.

Abstract: A process for producing a repair coating on at least one metallic surface that is coated with at least one corrosion protecting coating A applied with at least one composition selected from the group of pretreatment compositions, of organic compositions and of silicon compound(s) containing compositions, whereby the at least one corrosion protecting coating A has been at least partially removed in the area Z, whereby a thin corrosion protecting coating B containing at least one silicon compound is applied with a solution or dispersion containing a silane, a silanol, a siloxane, or a polysiloxane on at least a part of the area Z. A further corrosion protecting coating C may be applied.

Abstract: A method and system for depositing multiple materials onto a substrate is described. The method broadly comprises the steps of providing a source of a first powder material to be deposited, providing a source of a second powder material to be deposited, and sequentially depositing the first powder material and the second powder material onto the substrate at a velocity sufficient to deposit the materials by plastically deforming the materials without metallurgically transforming the particles of powder forming the materials.

Abstract: A first material with a known maximum temperature of operation is coated with a second material on at least one surface of the first material. The coating has a melting temperature that is greater than the maximum temperature of operation of the first material. The coating is heated to its melting temperature until the coating flows into any cracks in the first material's surface.

Abstract: A method for repairing a component such as a turbine blade is provided. At the end of its operating time, the component has, for example, a depletion of aluminium in a region near the surface. The application of a repair layer is provided including particles with an increased proportion of aluminium. A subsequent heat treatment may achieve the effect of equalizing the concentration of aluminium between the repair layer and the region near the surface, and so the aluminium content required for new components is achieved again.

Abstract: A method for regenerating oxide coatings on selected gas turbine engine components in situ, comprising the steps of defining an exhaust gas recirculation (EGR) loop for the gas turbine engine, identifying one or more target locations within the EGR loop for purposes of monitoring the level of metal oxide degradation occurring in key gas turbine engine components over time, collecting and analyzing data corresponding to the level of metal oxide degradation with a fixed time period at each of the target locations, determining which ones of the target locations within the EGR loop require oxide regeneration using injected oxygen, and controlling the amount of oxygen injection at the target locations sufficient to regenerate the metal oxide coatings to desired levels.

Abstract: A process for producing a metal member that enables both the fatigue properties and the corrosion resistance of the member to be improved, a structural member that includes a thus produced metal member, and a method of repairing a metal member. The process for producing a metal member comprises a projecting particles having an average particle size of not more than 200 ?m onto the surface of a metal material comprising an aluminum alloy using compressed air or a compressed gas, and a chemical conversion treatment including forming a film on the surface of the metal material by performing a chemical conversion treatment following projecting the particles.

Abstract: The present inventions relate to methods and apparatus for detecting and mechanically removing defects and a surrounding portion of the photovoltaic layer and the substrate in a thin film solar cell such as a Group IBIIIAVIA compound thin film solar cell to improve its efficiency.

Abstract: The invention relates to an aqueous composition of bis-amino-functional silicon compounds which is essentially free of organic solvents and releases essentially no further alcohol in the course of crosslinking, and to processes for preparing it and to the use thereof, for example for hydrophobization of metal or glass surfaces.

Abstract: A fast hardening clear coating composition for repairing a clear coat/color coat finish or a pigmented mono-coat of a vehicle comprising a film forming binder and an organic liquid carrier, where the binder contains a hydroxyl polymer component comprising (A) hydroxyl-containing acrylic polymer, (B) at least one hydroxyl-terminated component selected from the group consisting of (1) an organic diol having the formula where R1 and R2 are individually selected from the group of hydrogen and an alkyl group having 1, 3-5 carbon atoms and (2) a hydroxyl terminated reaction product of trimethylol propane and a lactone; (C) an organic polyisocyanate crosslinking component, at least portion of which comprises a trimer of isophorone diisocyanate or hexamethylene diisocyanate and the composition further contains, a curing catalyst, of a dialkyl tin aliphatic carboxylate, a tertiary aliphatic mono or diamine, an aliphatic carboxylic acid, and optionally, a zinc or calcium organic acid salt in an effective amount suc

Abstract: Methods of reducing corrosion between magnesium and another metal are disclosed herein. In one method, a corrosion protection material is cold sprayed at an interface formed between the magnesium and the other metal, the corrosion protection material including magnesium. In another method, a cladding layer is applied to heat affected areas of the magnesium and/or the other metal, at a welded joint, or combinations thereof.

Abstract: An internal combustion piston comprises a modified layer produced by a surface treatment including injecting injection powders having a diameter of 20 ?m to 400 ?m and containing a reinforcing element to be collided with a surface of the internal combustion piston obtained by casting and forging by injecting at an injection speed of 80 m/s or more or at an injection pressure of 0.3 MPa or more, the reinforcing element improving a strength of an alloy comprising the piston when being diffused and penetrated in the alloy, wherein by the surface treatment, oxides generated on the surface of the piston by the casting and forging are removed, and surface flaws generated on the surface are repaired, whereby the modified layer is formed to have a uniformly fine-grained metal microstructure which contains the reinforcing element in the injection powders diffused and penetrated in the vicinity of the surface of the piston and an alloy element of the alloy comprising the piston.

Abstract: A method for the local initial application of a thermal barrier coating layer (3), or for the local repair of coating defects and/or deteriorations of components (1) in the hot gas path of a gas turbine engine, which components are coated with a thermal barrier coating layer, includes at least the following steps: (I) in the case of repair, normally overall inspection of the whole component (1) for the determination of the location of defect/deterioration, as well as of corresponding type of defect/deterioration of each place for a multitude of locations of the component (1); (II) if needed, preparation of the surface in at least one location; (III) local application of a ceramic tissue together with a wet chemical thermal barrier coating layer deposition material for the formation of a patch (5) of ceramic matrix composite; (IV)a intermediate inspection of the patch and/or the surface; (IV)b in the case of a repetitive and/or multi-step repair method, subsequent layer application of a ceramic tissue togethe

Abstract: A restoration process for restoring surface porosity defects on a component surface. The areas of a component surface having surface porosity defects are identified for restoration. The restoration surface is subsequently sprayed with a restoration spray to restore the surface porosity defects. The component surface is then finished to create a final component substantially free of surface porosity.

Abstract: A process for forming a coated substrate comprises providing a nickel base alloy substrate, depositing a chromium coating onto the nickel base alloy substrate and diffusing chromium from said coating into the substrate, applying a MCrAlY coating onto the nickel base alloy substrate and heat treating the substrate with the deposited chromium and the MCrAlY coating so that chromium diffuses into an outer region of the substrate. Further, in accordance with the present invention, a strip process for removing a coating from a substrate broadly comprises the steps of providing a nickel base alloy substrate having chromium diffused into an outer region and a MCrAlY coating deposited over the substrate with the diffused chromium and removing the MCrAlY coating by immersing the nickel base alloy substrate in an acid solution containing a sulfuric acid—hydrochloric acid mixture in water.

Abstract: Provided is a highly versatile conductive metallic coating material which is free from the limitation related to a facility without handling complication, and which can maintain its anticorrosive action for a long period. Specifically provided is a conductive metallic coating material which has an organic resin component and a metal component containing aluminum and magnesium and which exhibits a sacrificial anticorrosive reaction on iron. A content ratio of the metal component and the organic resin component is desirably 98:2 to 80:20 in terms of weight ratio. The conductive metallic coating material according to the present invention is usable for preventing corrosion of a building structure or a civil engineering structure and for repairing a corrosion proof treated surface of an existing building structure or a civil engineering structure.

Abstract: Methods for repairing barrier coatings involving providing a component having a barrier coating including at least one damaged portion, removing the damaged portion of the barrier coating leaving a void, applying a replacement tape cast barrier coating to the void of the component, and sintering the component having the replacement tape cast barrier coating layer.

Abstract: A method of reducing the amount of particulates generated from the surface of a processing component used during plasma enhanced chemical vapor deposition of thin films. The body of the processing component comprises an aluminum alloy, and an exterior surface of said processing component is texturized to increase the amount of surface area present on the exterior surface. The texturizing process includes at least one step in which the surface to be texturized is bead blasted or chemically grained, so that the surface roughness of the texturized surface ranges from about 50 ?-inch Ra to about 1,000 ?-inch Ra.

Abstract: A process for producing a repair coating on a metallic surface coated with a corrosion protecting coating A applied with a pretreatment composition, an organic composition or a silicon compound containing composition. Corrosion protecting coating A has been at least partially removed in the area Z, and a thin corrosion protecting coating B containing a silicon compound is applied with a solution or dispersion containing a silane, a silanol, a siloxane, a polysiloxane or a mixture thereof on at least a part of the area Z. A further corrosion protecting coating C which is generated with an organic composition like a primer, a wet-primer, an e-coat, a powder coat, a base-coat or a clear-coat or a composition which is the same or another siloxane composition as for the thin film B may also be applied to coating B.

Abstract: A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.

Abstract: This invention relates to the repair and removal of erosion or impact damage using hand sandable elastomeric coatings on a curved substrate, particularly such surfaces as the leading edge of the airfoil. Specialized applicators and methods of use are also disclosed.

Abstract: A method for repairing a scratch in the clear top coat overlying a pigmented base coat on a metallic substrate, without damaging the pigmented base coat, involves the steps of applying an amount of a repair composition to the scratch at least sufficient to fill the scratch, spreading the composition into and over the scratch until the composition at least fills the scratch, removing excess composition, allowing the composition to air dry, sanding the dried composition to create a smooth, continuous surface at the site of the scratch and buffing the sanded surface with a fine polishing compound to establish a high gloss, clear coat surface at the site of the scratch. A desirable resin composition consists essentially of, in percent by weight of the composition, toluene 10-18%, n-butyl acetate 10-15%, ethyl acetate 0-5%, acetone 20-25%, acrylic resins 30-50%, surface tension reducer 0-0.5% and plasticizer/coalescent 0-3%.

Abstract: Compositions useful as coatings, wherein the compositions comprise a coating material and a material selected from the group consisting of: mortars and grouts in admixture with the coating material. The coatings may be water-based or solvent-based, and may be epoxies, polyurethanes, polyaspartic ester polymers and polyureas in some embodiments. Compositions according to the disclosure exhibit enhanced physical properties compared with the same compositions made in the absence of a mortar or a grout as an ingredient. Compositions according to some embodiments have at least one of a mortar or grout, and optionally both, evenly dispersed within the bulk of a coating material prior to its application to a substrate sufficiently that the particles of the mortar or grout, or both when both are selected to be present, are substantially completely surrounded by a curable reactive mixture that cures to form a polymeric material useful as a coating.

Abstract: Systems and methods for providing localized heat treatment of metal components are provided. In this regard, a representative method includes: identifying a portion of a metal component to which localized heat treatment is to be performed; shielding an area in a vicinity of the portion of the metal component; and directing electromagnetic energy in the infrared (IR) spectrum toward the portion of the metal component such that the portion is heated to a desired temperature and such that the area in the vicinity of the portion that is subjected to shielding does not heat to the temperature desired for the heat treatment.

Abstract: Disclosed herein is a method for inhibiting corrosion of a high strength steel turbine component subject to rotary stress. The method comprises applying a sacrificial overlay coating material to at least a portion of a surface of the component to form a protected component, and applying a seal material to at least a portion of the protected component to form a seal coat having a temperature resistance of greater than about 500° F. Also disclosed herein is a turbine component and corresponding engine protected by the method. Further provided is a method for repairing a high strength steel component of a turbofan engine. These methods are capable of inhibiting at least one of stress corrosion cracking or surface pitting of the turbine component after exposure to corrosive water.

Abstract: A method of repairing an abradable, nickel single crystal material having an abraded surface area by applying a diffusion layer to the abraded surface area comprising a nickel-based alloy having a quantity of an additional element selected from silicon and boron; and also applying an abradable layer to the material comprising a cobalt-based alloy to restore the abraded surface area.

Abstract: Providing a metal mold repair method and a metal mold repair paste agent which are capable of repairing cracks with simple work. A repair paste agent containing components that become an alloy is directly applied to a surface of a metal mold having a crack so as to cover the crack part, subsequently a surface of the repair paste agent is coated with an oxidation inhibitor and the repair paste agent is made to penetrate the inside of the crack by heating and becomes an alloy, thereby filling up the crack.

Abstract: A method of coating a metal substrate such as the components in second and third stages of gas turbine engines in order to increase the oxidation and corrosion resistance of the metal substrate under high temperature operating conditions, the method including the steps of forming a powdered mixture of a high-melt superalloy or MCrAlY component, where M comprises Fe, Ni and/or Co, and a low-melt component containing about 2-5 wt. % silicon, boron or hafnium, applying the powdered mixture to the surface of the metal substrate at room temperature using an atomized spray to form a uniform surface coating, and then heating the coated substrate surface under vacuum conditions to a temperature in the range of about 1900° F. to 2275° F. to obtain a uniform coating composition providing oxidation resistance to the underlying substrate.

Abstract: Microencapsulated chemical(s), as water-soluble solid particles, are embedded in at least one the paint layers on the surface of a magnesium article used in an automobile. If the protective paint film is scratched or otherwise mechanically disturbed to expose the surface of the magnesium article the capsules will be ruptured. This will expose the encapsulated chemical(s) to ambient water enabling them to dissolve and form an aqueous solution capable of reacting with the exposed magnesium to form a protective passivating layer on the exposed magnesium to resist corrosion. In a second embodiment the encapsulated chemicals include a deliquescing compound for extraction of moisture from the atmosphere sufficient to induce dissolution of the passivating layer-forming chemical(s) and trigger the formation of the passivating layer in the absence of ambient water.

Abstract: A first material with a known maximum temperature of operation is coated with a second material on at least one surface of the first material. The coating has a melting temperature that is greater than the maximum temperature of operation of the first material. The coating is heated to its melting temperature until the coating flows into any cracks in the first material's surface.

Abstract: A method and composition are disclosed that provide protection of refractory materials used, e.g., in kiln and slagging coal-gasifier operations. Inert high-temperature melting crystalline compounds and glasses are used to fill defects on the surface and/or interior of the refractory material. At the operation temperatures, the inert crystalline compound mixes with slag and increases the viscosity and melting point temperature, reducing the ability of the slag to penetrate into the refractory, which minimizes breakdown of the refractory material. The same scheme can potentially be applied to sealing of geological formations, e.g., for CO2 sequestration, and repairing of engineering materials currently in service while continuing to operate in aggressive environments.

Abstract: Methods for making an environmental barrier coating using a sintering aid involving applying a bond coat layer to the ceramic component; combining at least an organic solvent, a primary transition material selected from a rare earth disilicate, or a doped rare earth disilicate, and at least one slurry sintering aid to produce a transition layer slurry; combining at least an organic solvent, and a primary outer material selected from a rare earth monosilicate or a doped rare earth monosilicate to produce an outer layer slurry; combining at least an organic solvent, and a primary compliant material comprising BSAS or a rare earth doped BSAS to produce a compliant layer slurry; applying at least the transition layer slurry, and any one or more of the outer layer slurry, and the compliant layer slurry to the component; and sintering the component to produce the environmental barrier coating having at least the bond coat layer, a transition layer and any of an outer layer or a compliant layer whereby a reaction be