Apparatus and method for selectively coating internal and external surfaces of an airfoil
AssigneeGeneral Electric Company
InventorsJeffrey A. Pfaendtner, Joseph D. Rigney, Nripendra N. Das, Ramgopal Darolia
Life of this patent
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Abstract
A gas turbine airfoil has an external surface and an internal passage therethrough. The internal passage is selectively coated by providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil, and providing a coating prevention structure overlying at least a portion of the external surface. The flowable precursor coating material is flowed from the source of the flowable precursor coating material and through the internal passage of the airfoil. The coating prevention structure prevents contact of the flowable precursor coating material with the external surface of the airfoil.
Claims24
A method for coating a portion of a gas turbine airfoil having an external surface and an internal passage therethrough, comprising:
- providing a source of a flowable precursor coating material in contact with the internal passage of the airfoil;
- providing a coating prevention structure overlying at least a portion of the external surface;
- and
- flowing the flowable precursor coating material from the source of the flowable precursor coating material and through the internal passage of the airfoil, the coating prevention structure substantially preventing contact of the flowable precursor coating material with the external surface of the airfoil.
A method for coating a portion of a gas turbine airfoil having an external surface and an internal passage therethrough with an inlet end, comprising the steps of:
- providing a coating deposition apparatus;
- assembling the gas turbine airfoil and a coating prevention structure together within the coating deposition apparatus, wherein the coating prevention structure overlies at least a portion of the external surface of the airfoil and permits coating on the internal passage but not on the portion of the external surface of the airfoil;
- and
- providing a gaseous precursor coating material within the coating deposition apparatus;
- and
- flowing the gaseous precursor coating material into the inlet end of the internal passage and through the internal passage, the coating prevention structure substantially preventing contact of the gaseous precursor coating material with the portion of the external surface of the airfoil.
A method for coating a portion of a gas turbine airfoil having an external surface and an internal passage therethrough with an inlet end, comprising the steps of:
- providing a coating deposition apparatus having a source chamber;
- assembling the gas turbine airfoil and a coating prevention structure together within the coating deposition apparatus, wherein the coating prevention structure overlies at least a portion of the external surface of the airfoil and permits coating on the internal passage but not on the portion of the external surface of the airfoil;
- and
- flowing a gaseous precursor coating material from the source chamber, into the inlet end of the internal passage of the gas turbine airfoil, and through the internal passage, the coating prevention structure substantially preventing contact of the gaseous precursor coating material with the portion of the external surface of the airfoil.
Dependencies are inferred from the claim text.