An embodiment of a line-of-sight coating fixture includes a support structure, a spindle, and a shadow structure. The support structure includes a plurality of compartments disposed below a platter, each compartment having an opening on a periphery of the support structure. Each compartment is adapted to receive and secure a base of a workpiece such that a body of each workpiece to be coated is disposed about a periphery of the support structure and extends above the platter. The spindle is disposed through a center of the platter or support structure for rotating the workpieces thereabout. The shadow structure is disposed about the spindle, inside of the periphery, the shadow structure sized and adapted to shield a portion of each workpiece from line-of-sight coating material.

An embodiment of a line-of-sight coating fixture includes a support structure, a spindle, and a shadow structure. The support structure includes a plurality of compartments disposed below a platter, each compartment having an opening on a periphery of the support structure. Each compartment is adapted to receive and secure a base of a workpiece such that a body of each workpiece to be coated is disposed about a periphery of the support structure and extends above the platter. The spindle is disposed through a center of the platter or support structure for rotating the workpieces thereabout. The shadow structure is disposed about the spindle, inside of the periphery, the shadow structure sized and adapted to shield a portion of each workpiece from line-of-sight coating material.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

A coating process for applying a bifurcated coating to an article is disclosed including applying an aluminizing slurry to a first portion of the article, applying a chromizing slurry to a second portion of the article, and simultaneously heat treating the article, the aluminizing slurry, and the chromizing slurry. Heat treating the aluminizing slurry forms an aluminide coating on the first portion of the article and an aluminide diffusion zone between the article and the aluminide coating. Heat treating the chromizing slurry forms a chromide coating on the second portion of the article and a chromide diffusion zone between the article and the chromide coating. The first portion and the second portion are both maintained in an unmasked state while applying the aluminizing slurry and the chromizing slurry and during the heat treating.

A method for forming a coating on a surface of an airfoil is provided, where the airfoil has a leading edge, a trailing edge, a pressure side, and a suction side. The method can include forming a platinum-group metal layer on the surface of the airfoil along at least a portion of the trailing edge, and forming an aluminide coating over the surface of the airfoil of the leading edge, the trailing edge, the pressure side, and the suction side. The leading edge may be substantially free from any platinum-group metal. The method may further include, prior to forming the aluminide coating, forming a bond coating on the surface of the airfoil along the leading edge, and after forming the aluminide coating, forming a thermal barrier coating over the bond coating. A method is also generally provided for repairing a coating on a surface of an airfoil.

Disclosed is a method for improving the high-temperature stability of a component, in particular a blade of a turbomachine, formed at least partially from a molybdenum alloy that, besides molybdenum, silicon, boron and titanium, comprises iron and/or yttrium. The method comprises depositing a diffusion barrier layer formed from technically pure molybdenum or tungsten or being an alloy based on molybdenum and/or tungsten at least on an outer surface, which comprises the molybdenum alloy, of the component, and depositing silicon on the diffusion barrier layer to form molybdenum silicides and/or tungsten silicides.

The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine. The method includes uninstalling the damaged coated component from the gas turbine engine. The method also includes isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component. In addition, the method includes simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine.

The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine. The method includes uninstalling the damaged coated component from the gas turbine engine. The method also includes isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component. In addition, the method includes simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine.

The present disclosure is directed to a method for coating a component of a gas turbine engine. The method includes isolating a first portion of the component of the gas turbine engine from a second portion of the component. The method also includes simultaneously depositing a first coating material on the first portion of the component and a second coating material on the second portion of the component, wherein the first and second coating materials are different.