Method of protecting a surface
AssigneePratt & Whitney Canada Corp.
InventorPhillippe SAINT-JACQUES
Life of this patent
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Abstract
A method of masking part of a surface of a wall of a gas turbine component including at least one area having cooling holes defined therein, the method including applying a viscous curable masking compound to the part of the surface over an entirety of each of the at least one area, including blocking access to the cooling holes from the surface by applying the masking compound over the cooling holes without completely filling the cooling holes with the masking compound, and forming a respective solid masking element completely covering each of the at least one area and the cooling holes defined therein by curing the masking compound.
Claims20
A method of masking part of a surface of a wall of a gas turbine component, the surface including at least one area having cooling holes defined therein, the method comprising:
- applying a viscous curable masking compound to the part of the surface over an entirety of each of the at least one area, including blocking access to the cooling holes from the surface by applying the masking compound over the cooling holes without completely filling the cooling holes with the masking compound;
- and
- forming a respective solid masking element completely covering each of the at least one area and the cooling holes defined therein by curing the masking compound.
The method as defined in claim 4, wherein applying the viscous material continuously over the cooling holes is performed such that the masking compound penetrates in each hole along a distance corresponding to less than a diameter of the hole.
A method of applying a surface treatment to at least one selected portion of a surface of a component, the method comprising:
- protecting at least one area of the surface adjacent the at least one selected portion by applying a viscous curable masking compound to the surface over an entirety of each of the at least one area, including blocking access from the surface to cooling holes defined in one or more of the at least one area by applying the masking compound continuously over the cooling holes without completely filling the cooling holes with the masking compound;
- forming a respective solid masking element completely covering each of the at least one area by curing the masking compound;
- applying the surface treatment to the at least one selected portion;
- and
- removing the masking compound.
A method of masking an area of a surface of a gas turbine component, the method comprising:
- relatively displacing the component and a nozzle of a pneumatic distribution system while maintaining a predetermined relative distance between a tip of the nozzle and the surface;
- expelling a viscous curable masking compound from the nozzle onto the area during the relative displacement until the area is completely covered by the masking compound;
- curing the masking compound to form a solid masking element completely covering the area.
Dependencies are inferred from the claim text.