US2019093483A1PendingUtilityA1
Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine
Est. expiryNov 24, 2035(~9.4 yrs left)· nominal 20-yr term from priority
F05D 2260/202F05D 2230/14B23B 2215/81F05D 2260/20F05D 2230/10F05D 2230/21F05D 2230/80F01D 5/186F05D 2240/305F05D 2230/11F01D 5/18F01D 5/005F05D 2220/32F05D 2250/52F01D 5/225F05D 2240/306B23P 15/00
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Claims
Abstract
A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.
Claims
exact text as granted — not AI-modifiedThat which is claimed:
1 . An airfoil for a gas turbine engine, the airfoil comprising:
a suction side; a pressure side opposite the suction side; and one or more hole starter bosses cast on the suction side, the pressure side, or both.
2 . The airfoil of claim 1 , wherein the one or more hole starter bosses comprise a protrusion.
3 . The airfoil of claim 1 , wherein the one or more hole starter bosses comprise an indentation.
4 . The airfoil of claim 1 , wherein the one or more hole starter bosses comprise a plurality of holes.
5 . The airfoil of claim 1 , further comprising one or more line-of-sight access holes in a shroud of the airfoil.
6 . The airfoil of claim 1 , further comprising one or more holes in a shank of the airfoil.Cited by (0)
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