Trailing edge cooling arrangement for an airfoil of a gas turbine engine
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United States of America Patent
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Dec 11, 2018
Grant Date -
Jan 29, 2015
app pub date -
Jul 26, 2013
filing date -
Jul 26, 2013
priority date (Note) -
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Abstract
An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114′) defining plugged holes (115) and cooling holes (116) along a radial direction (117). A selective group (314) of the cooling and plugged holes are based on a reduced cooling fluid requirement at the trailing edge (114′) resulting from an improved thermal barrier coating (126). A process (200) is also provided including removing (202) an airfoil from service in a gas turbine engine and adding or improving (204) a thermal barrier coating on the airfoil. The process also includes selectively (206) plugging holes in the airfoil in response to a reduced cooling fluid required through the airfoil as a result of the added or improved thermal barrier coating.
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