Method for pressure coating of surface of hot gas path component of gas turbine system in aircraft industry, involves continuously coating surface to allow coating material to be bridged over groove length in exit region direction

摘要

The method involves connecting a pressure masking device with coolant supply holes formed on an inner surface of an industry article. Pressure masking fluid i.e. water, is routed from the inner surface to an outer surface of the article, where the outer surface includes an objective surface through grooves. The print masking fluid is routed through the set of coolant supply holes and the grooves at pressure. The objective surface is continuously coated to allow the coating material to be bridged over length of the groove in a direction of an exit region and to form microchannels. An independent claim is also included for a pressure masking system.