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US 7,303,375 B2Granted
Refractory metal core cooling technologies for curved leading edge slots
AssigneeUnited Technologies Corporation
InventorsFrank Cunha, William Abdel-Messeh
Life of this patent
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Abstract
A turbine engine component has an airfoil portion with a leading edge portion. The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion. A method for forming the leading edge portion using refractory metal core technology is described.
Claims10
A process for fabricating a cooling system in a leading edge portion of an airfoil portion of a turbine engine component, said process comprising the steps of:
- providing a die in the shape of an airfoil portion to be formed;
- inserting at least one ceramic core into said die to form at least one central core element;
- inserting a refractory metal sheet having a plurality of curved finger portions into said die;
- introducing molten metal into said die to form said airfoil portion;
- and
- removing said at least one ceramic core and said refractory metal sheet to form a plurality of staggered holes in said leading edge portion, a plurality of curved passageways associated with said holes, and a central core element communicating with said plurality of curved passageways.
3 more elements
Dependencies are inferred from the claim text.