(19)
(11) EP 2 631 325 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
09.08.2017 Bulletin 2017/32

(43) Date of publication A2:
28.08.2013 Bulletin 2013/35

(21) Application number: 13155956.9

(22) Date of filing: 20.02.2013
(51) International Patent Classification (IPC): 
C23C 10/02(2006.01)
C25D 5/02(2006.01)
C25D 13/02(2006.01)
C25D 13/16(2006.01)
 C23C 10/58(2006.01)
C25D 5/12(2006.01)
C25D 13/12(2006.01)
F01D 5/28(2006.01)
(84) Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated Extension States:
BA ME

(30) Priority: 21.02.2012 US 201261633935 P

(71) Applicant: Howmet Corporation
Independence OH 44131 (US)

(72) Inventors:
  • Murphy, Kenneth S.
    Norton Shores, MI 49441 (US)
  • Basta, William C.
    Montague, MI 49437 (US)

(74) Representative: Trinks, Ole 
Meissner Bolte Patentanwälte Rechtsanwälte Partnerschaft mbB Widenmayerstraße 47
80538 München
80538 München (DE)

   


(54) Coating and coating method for gas turbine component


(57) The present invention provides a protective coating for a gas turbine blade or other component wherein the duplex coating includes an aluminum-bearing coating, such as a diffusion aluminide, formed on a first, relatively higher temperature region of the blade/component and a later-applied chromium-bearing diffusion coating formed on an adjacent relatively lower temperature region of the blade/component subject to hot corrosion in service. The chromium-bearing coating is applied after the aluminum-bearing coating by masking that coating and depositing a metallic chromium coating on the adjacent region followed by diffusing the chromium into the blade/component alloy to form a chromium-enriched diffusion coating thereon.







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