Airfoil cooling using non-line of sight holes
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United States of America Patent
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Jun 7, 2022
Grant Date -
Apr 2, 2020
app pub date -
Jul 31, 2019
filing date -
Apr 15, 2016
priority date (Note) -
In Force
status (Latency Note)
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Abstract
An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.
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