Gas turbine engine component with combined mate face and platform cooling
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United States of America Patent
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Mar 12, 2019
Grant Date -
Dec 31, 2015
app pub date -
Feb 7, 2014
filing date -
Feb 15, 2013
priority date (Note) -
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Abstract
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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