Abstract: A method of forming a metal coating on surfaces of internal passages of a turbine part includes applying a nickel aluminum bond coating to an external surface of the turbine part, positioning the turbine part in a VPA chamber, coupling a gas manifold to at least one internal passage inlet, and coating at least a portion of the internal surface and the external of the turbine part by a vapor phase aluminiding (VPA) process using metal coating gases to form a coating on the internal surfaces of the turbine part.

Abstract: A method for at least partially coating a surface of an object with a layer of platinum. The method includes applying a platinum precursor material to the object surface, evaporating the platinum precursor material from the object surface such that a residue comprising platinum remains on the surface, and heating the object such that the residue evaporates and re-deposits on the object surface as a layer comprising platinum.

Abstract: A method of forming a metal coating on surfaces of internal passages of a turbine blade, the turbine blade having an outer surface and comprising at least one internal passage. The method includes injecting a paint into at least one of the internal passages of the turbine blade, and heat treating the turbine blade such that an aluminide coating is deposited on the surface of the at least one internal passage.

Abstract: Methods and apparatus for forming a metal coating on a surface of a workpiece are provided. The method includes positioning the workpiece in a microwavable chamber, positioning a coating material in the microwavable chamber, and heating at least the workpiece and the coating material using microwave range electromagnetic energy such that a diffusion coating of the coating material is formed on the surface of the workpiece.

Abstract: A method of removing an oxide layer from a surface of a metallic component, includes: contacting the surface with an alkaline cleaner, followed by contacting the surface with an acidic solution. The method is especially useful for removing oxide layers from the interior of hollow gas turbine engine components. The cleaned surface may be provided with an oxide-resistant coating by a pack aluminide coating process.

Abstract: A method for repairing a turbine component includes identifying a crack in a surface of the component and applying a fluoride mixture to the surface of the component containing the crack. The method also includes exposing the portion of the component including the fluoride mixture to a controlled atmosphere and returning the repaired surface of the component to predetermined dimensions.

Abstract: A chemically-nonreactive, electrically-nonconductive shield having a recess generally corresponding to the shape of an airfoil portion to be positioned therein. The shield is submerged in an electroplating solution in a plating tank. The recess in the shield is sized to provide a predetermined, closely-spaced apart clearance between walls of the recess and the adjacent airfoil portion sufficient to reduce the flow rate of an electrolyte present in the electroplating solution between walls of the recess and the adjacent airfoil portion. The clearance permits control of the amount of electroplating that is deposited on the portion of the airfoil that is positioned in the recess in relation to portions of the airfoil not positioned in the recess.

Abstract: A coating system for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to fluid containment surfaces. The coating system combines an outermost layer of platinum with an inner ceramic barrier layer of silica and/or tantala. The platinum layer catalyzes the hydrocarbon fluid to form particles of carbonaceous gum substances, and the ceramic barrier layer seals the containment surface from the hydrocarbon fluid to eliminate attachments points for deposits and inhibit interdiffusion between the platinum layer and the containment surface. The invention also encompasses a coating apparatus and process for depositing the coating system.

Abstract: Methods and apparatus of fabricating gas turbine engine components are provided. The method includes positioning a non-consumable shield adjacent to an edge of the component such that a gap is defined between the shield and the component, wherein the shield and gap form a fluid flow restriction adjacent to the edge, and inducing an electrical current from an anode to the component through an electrolyte bath such that a coating is applied to the component.

Abstract: A coating and method for reducing the incidence of cracking in a combustor assembly of a gas turbine engine, and particularly combustor assemblies of at least two components that are welded together to define a weld region that is prone to cracking at combustion temperatures sustained within the combustion chamber of the gas turbine engine. At least the surface of the weld region protected by a coating system comprising a thermal-sprayed metallic bond coat and a ceramic coating deposited on the bond coat. The ceramic coating is deposited by thermal spraying a powder having a particle size of not greater than 10 micrometers, and the outer surface of the coating system is smoother than the outer surface of the bond coat on which the ceramic coating is deposited.

Abstract: A process for refurbishing a worn surface of a shroud support component of a turbomachine, as well as a shroud support component refurbished with the process. The process generally entails removing a surface region of the worn surface so as to define a repair surface on the component. A braze tape formed from a slurry to comprise a braze material and a wear-resistant alloy is then applied to the repair surface, followed by a heat treatment to cause the braze tape to diffusion bond to the repair surface so as to define a built-up surface. The built-up surface is then machined to define a wear-resistant coating on the component.