Coating and coating method for gas turbine engine component
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United States of America Patent
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Issued Date -
Jan 14, 2016
app pub date -
Feb 4, 2013
filing date -
Feb 21, 2012
priority date (Note) -
Abandoned
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Abstract
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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