GAS TURBINE ENGINE TURBINE BLADE TIP WITH COATED RECESS
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United States of America Patent
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Issued Date -
Oct 22, 2015
app pub date -
Apr 15, 2015
filing date -
Apr 22, 2014
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Abstract
A blade for a gas turbine engine includes an airfoil that has a tip with a terminal end surface. The terminal end surface includes a recess that has a depth of less than 40 mils (1.016 mm). The recess is filled with a thermal barrier coating. The recess is without any cooling holes.
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