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US 2008/0175714 A1Published application
Dual cut-back trailing edge for airfoils
AssigneeUnited Technologies Corporation
InventorsBrandon W. Spangler, Edward F. Pietraszkiewicz
Life of this patent
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Abstract
A cooling system for an airfoil portion of a turbine engine component is provided. The cooling system includes a first cavity dedicated to cooling a trailing edge portion of an airfoil portion and a second cavity dedicated to cooling an aft portion of a pressure side wall.
Claims33
A cooling system for an airfoil portion of a turbine engine component including:
- a first cavity dedicated to cooling a trailing edge portion of said airfoil portion;
- and
- a second cavity dedicated to cooling an aft portion of a pressure side wall of said airfoil portion.
A turbine engine component which comprises:
- an airfoil portion having a trailing edge, a suction side wall, and a pressure side wall;
- a first cavity adjacent said suction side wall for cooling said trailing edge;
- and
- a second cavity adjacent said pressure side wall for cooling an aft portion of said pressure side wall.
1 more element
Dependencies are inferred from the claim text.