F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/28 (2006.01) C22C 19/05 (2006.01) C23C 10/00 (2006.01) F01D 5/18 (2006.01)
Patent
CA 2645780
A gas turbine blade (10) comprises a base metal, a platform (14), an airfoil (12) extending upwardly from the platform, a shank (18) extending downwardly from the platform. The shank has an exterior wall (71) and an internal passage (84), and the airfoil (12) has a cooling flow channel (34) inside the airfoil for flowing a cooling flow therethrough. The blade has a first chromide coating (102) contacting the base metal of at least a portion of an interior surface of the shank (18) and interdiffused therewith, wherein the first chromide coating does not have an aluminide coating deposited over it. The blade has a second chromide coating (144) contacting the base metal of at least a portion of an interior surface of the airfoil (12) and interdiffused therewith. A method (200) for preparing a gas turbine blade comprises the steps of applying chromide coatings (71, 72, 73, 74), sealing the interior passages (80) of the shank and airfoil and applying (82, 84) an aluminide or platinum aluminide coating and an optional ceramic layer (86) on the airfoil.
Brammer Kathleen Diana
Hazel Brian Thomas
Polley Nicole Marie
Wortman David John
Wustman Roger Dale
Company General Electric
Craig Wilson And Company
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