METHOD AND DEVICE TO PREVENT COATING A DOVETAIL OF A TURBINE AIRFOIL

• US 20090252872A1
• Filed: 03/13/2006
• Published: 10/08/2009
• Est. Priority Date: 03/13/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: King, Jackie Lee, Saylor, Matthew David
• Granted Patent: US 7,632,541 B2
• Time in Patent Office: Days
• US Class Current: 427/248.100
• CPC Class Codes: C23C 10/04 Diffusion into selected surface areas, e.g. using masks
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment
• CPC Class Codes: F05D 2300/611 Coating

Abstract

A method and masking assembly for masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade. The masking assembly comprises at least two masking members, each having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion. By mating the masking members, the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates the dovetail portion, and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion to entrap the dovetail portion within the interior cavity of the masking assembly.

Claims

1. A method of masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade and a platform of the blade between the airfoil and dovetail portions, the method comprising the steps of:

placing the dovetail portion in a solid masking assembly so that the airfoil portion and the entire platform of the blade remain outside the masking assembly, the masking assembly comprising at least two masking members, each masking member having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion, the dovetail portion being placed in the masking assembly by mating the masking members so that the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates at least part of the dovetail portion and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion, the undulatory surfaces of the masking members entrapping the dovetail portion within the interior cavity of the masking assembly while the masking members remain mated;

supplying a coating vapor to deposit a coating on the airfoil portion and on the entire platform of the blade while preventing deposition of coating on the dovetail portion with the masking assembly; and

then

separating the masking members to release the blade from the masking assembly.

2. The method according to claim 1, wherein the masking members are formed to be substantially identical.

3. The method according to claim 1, further comprising securing the masking members together with a retaining ring after placing the dovetail portion in the masking assembly.

4. The method according to claim 1, further comprising applying a sealant to interfaces defined by and between the masking members and by and between the dovetail portion and the masking members to prevent the coating vapor from entering the interior cavity of the masking assembly.

5. The method according to claim 4, wherein the sealant is a masking tape, putty, or slurry.

6. The method according to claim 1, wherein the masking members are formed of a material chosen from the group consisting of metallic and ceramic materials.

7. The method according to claim 1, wherein the masking members are formed of a nickel-base superalloy.

8. The method according to claim 1, further comprising reusing the masking assembly to deposit a coating on an airfoil portion of a second blade while preventing deposition of coating on a dovetail portion of the second blade with the masking assembly.

10. A method of masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade, the method comprising the steps of:

placing the dovetail portion in a solid masking assembly so that the airfoil portion of the blade remains outside the masking assembly, the masking assembly comprising at least two masking members, each masking member having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion, the dovetail portion being placed in the masking assembly by mating the masking members so that the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates at least part of the dovetail portion and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion, the undulatory surfaces of the masking members entrapping the dovetail portion within the interior cavity of the masking assembly while the masking members remain mated;

supplying a coating vapor to deposit a coating on the airfoil portion of the blade while preventing deposition of coating on the dovetail portion with the masking assembly; and

then

separating the masking members to release the blade from the masking assembly;

wherein the blade further comprises an internal cooling passage and the masking assembly has a passage therein through which the coating vapor enters the internal cooling passage during the supplying step.

9. The method according to claim 10, wherein the blade further comprises a platform between the airfoil and dovetail portions, and the placing step results in the entire platform being exposed during the step of supplying the coating vapor so that the coating is also deposited on the platform in its entirety.

11-20. -20. (canceled)