Directionally solidified thermal barrier coating

Coating processes – Spray coating utilizing flame or plasma heat – Metal oxide containing coating

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427446, C23C 402, C23C 410

Patent

active

058979212

ABSTRACT:
A method and apparatus form a thermal barrier coating on a metal component. A molten thermal barrier coating powder is sprayed on the component in sweeping strokes. A plurality of overlapping solidified coating ribbons are deposited on the component and include a sequentially deposited surface ribbon forming sublayer ribbons therebelow. The surface ribbon is preheated at a spray site so that the sprayed molten powder remelts the surface ribbon at the spray site for sequentially welding the sequentially deposited surface ribbons to the sublayer ribbons.

REFERENCES:
patent: 5073433 (1991-12-01), Taylor
patent: 5688564 (1997-11-01), Coddet et al.
patent: 5705231 (1998-01-01), Nissley et al.
"Development of Improved-Durability Plasma Sprayed Ceramic Coatings for Gas Turbine Engines", by I.E. Sumner, NASA Lewis Research Center, Cleveland, Ohio; and D. Ruckle, Pratt & Whitney Aircraft, East Hartford, Conn. Jun. 30-Jul. 2, 1980, pp. 4-13.
"Experimental and Theoretical Aspects of Thick Thermal Barrier Coatings for Turbine Applications" by G.Johner, V. Wilms, Hanau, West Germany and K.K. Schweitzer, P. Adam, Motoren-Und Turbinenion Munchen, Munchen West Germany, pp. 155-165 (no date).

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