Dimensionally stable durable thermal spray masking system
A masking system protects portions of a part, such as a turbine engine component, to be coated. The masking system has a base, a conduit positioned on said base, a part to be coated being positioned over the conduit, and an annular plate positioned over the conduit and resting on a first portion of the part.
1. A masking system for protecting portions of a turbine engine component being coated comprising:
a central conduit positioned on a base;
a central support column positioned on said base, said central support column abutting said central conduit;
a turbine engine component having a plurality of airfoils positioned over said central conduit and in contact with said central support column;
means for reducing overspraying adhering to said airfoils; and
a top mask for protecting a first portion of said turbine engine component from being coated and a lower mask mounted on an annular tube for protecting said airfoils from being coated.
2. The masking system of claim 1 , wherein said means for reducing overspraying comprises means for creating a flow of pressurized air in said annular tube which exits at a base of said airfoils.
3. The masking system of claim 2 , wherein said means for creating a flow of pressurized air comprises a source of pressurized air connected to said central conduit and holes in said central conduit for introducing said pressurized air into said annular tube.
4. The masking system of claim 1 , wherein
said top mask comprises an annular plate positioned over said central conduit and resting on a first portion of said part.
5. The masking system according to claim 4 , further comprising an outer masking element positioned at an end of said annular plate.
6. The masking system according to claim 5 , further comprising said outer masking element resting on a second portion of said part.
7. The masking system according to claim 1 , wherein said lower mask comprises:
said annular tube being positioned on said base; and
an annular masking element positioned on an upper end of said annular tube.
8. The masking system according to claim 7 , further comprising said annular masking element overlapping said plurality of airfoils.
9. The masking system of claim 2 , wherein said means for creating a flow of pressurized air comprises:
said central conduit having a plurality of holes; and
said central support column having a plurality of holes aligned with the holes in said central conduit.
10. The masking system of claim 9 , wherein said means for creating a flow of pressurized air further comprises a source of air connected to an interior of said central conduit via a fitting.
11. The masking system of claim 1 , further comprising said central support column supporting an interior portion of said turbine engine component.
12. The masking system of claim 1 , wherein said base is a rotatable base.