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US 5,511,309 AGranted
Method of manufacturing a turbine airfoil with enhanced cooling
AssigneeUnited Technologies Corporation
InventorBrian K. Beabout
Life of this patent
Estimating the term…
Abstract
Cooling of a turbine airfoil such as a turbine stator vane in a gas turbine engine is enhanced by the provision of additional cooling air through a secondary air inlet communicating with a medial portion of an internal, serpentine cooling air passage.
Claims4
A method of fabricating a gas turbine engine airfoil with a serpentine internal cooling air passage having an upstream portion, a downstream portion and a medial portion therebetween and a primary cooling air inlet communicating with said serpentine passage at said upstream portion, said method comprising the steps of:
- casting said airfoil around a core supported by a core support rod, said core having the shape of said internal passage with said primary cooling air inlet, and around said core support rod protruding through said airfoil;
- removing said core and said core support rod from within said airfoil;
- and
- maintaining an opening formed as a result of removing said core support rod from protruding through said airfoil to allow cooling air to enter said passage at said medial portion of said passage.
1 more element
Dependencies are inferred from the claim text.