Abstract: Methods for vapor depositing high temperature coatings on gas turbine components are provided, as are methods for producing pre-alloyed pucks for usage in vapor deposition processes. In one embodiment, the method includes the step of producing a pre-alloyed puck including a master alloy and a high vaporization temperature refractory metal, which has a vaporization temperature greater than each of the master alloy constituents. The pre-alloyed puck is placed over an ingot and heated to a temperature greater than the melt point of the pre-alloyed puck and less than the vaporization temperature of the high vaporization temperature refractory metal to transform the puck and a portion of the ingot into a molten pool and to produce a vapor stream containing the constituents of the master alloy and the ingot. The vapor stream is exposed to a gas turbine engine component to deposit the high temperature coating over at least one surface thereof.

Abstract: A loading apparatus for use in electroplating processes includes a container designed to sealingly receive a plurality of airfoil blades fitted with gaskets. Each fitted airfoil blade is disposed in contact with a plurality of electrical contact assemblies having a spring-like design which ensures an adequate connection is made and complete plating of the airfoil blades occurs.

Abstract: A gas turbine engine is used for power generation or propulsion and includes vanes. Each vane includes a trailing edge having a curvature and cooling slots that cool the vane. A photochemical edge shield includes an edge and projections that project from the edge. Before coating the vane, the photochemical edge shield is positioned on the vane such that each of the projections is received in one of the cooling slots. A ceramic coating is then applied to the vane. The photochemical edge shield prevents the ceramic coating from entering and clogging the cooling slots of the vane during the ceramic coating process.