Airfoil cooling with staggered refractory metal core microcircuits
AssigneeUnited Technologies Corporation
InventorsFrancisco J. Cunha, Edward F. Pietraszkiewicz
Life of this patent
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Abstract
A turbine engine component has an airfoil portion with a pressure side wall and a suction side wall and a cooling system. The cooling system has at least one cooling circuit disposed longitudinally along the airfoil portion. Each cooling circuit has a plurality of staggered internal pedestals for increasing heat pick-up.
Claims33
A turbine engine component having an airfoil portion with a pressure side wall and a suction side wall and a cooling system, said cooling system comprising an arrangement of chordwise overlapping cooling circuits positioned between said pressure side wall and said suction side wall having a plurality of chordwise spaced exit slots, said overlapping cooling circuits each being supplied fluid from a first supply cavity, each said cooling circuit having at least one exit for distributing said cooling fluid over an external surface of said pressure side wall, each said cooling circuit being disposed longitudinally along the airfoil portion, and each said cooling circuit having a plurality of staggered internal pedestals for increasing heat pick-up.
A turbine engine component comprising:
- an airfoil portion having a pressure side wall, a suction side wall, a leading edge and a trailing edge;
- a cooling system comprising an arrangement of chordwise overlapping cooling circuits,
- said arrangement of chordwise overlapping cooling circuits comprising a plurality of cooling circuits within said airfoil portion;
- said cooling circuits being positioned between an interior surface of said pressure side wall and an interior surface of said suction side wall;
- said plurality of cooling circuits each being supplied with cooling fluid from a first supply cavity;
- each said cooling circuit having a plurality of spaced apart exit slots extending through said pressure side wall for distributing said cooling fluid over an external surface of said pressure side wall,
- each said cooling circuit being disposed longitudinally along the airfoil portion;
- and
- each of said cooling circuits having a plurality of internal staggered pedestals.
A method for forming a turbine engine component comprising:
- forming an airfoil portion;
- and
- said forming step comprising forming an arrangement of chordwise overlapping cooling circuits having exit slots spaced chordwise along a pressure side wall of said airfoil portion wherein said overlapping cooling circuits are each supplied fluid from a first supply cavity, wherein each said cooling circuit has an inlet at a common chordwise point, wherein each said cooling circuit has at least one of said exit slots extending through said pressure side wall of said airfoil portion for distributing said cooling fluid over an external surface of said pressure side wall, and wherein each said cooling circuit extends longitudinally within said airfoil portion.
A method for forming a turbine engine component comprising:
- forming an airfoil portion;
- and
- said forming step comprising forming at least one cooling circuit extending longitudinally within said airfoil portion and having at least one exit slot extending through a pressure side wall of said airfoil portion,
- wherein said at least one cooling circuit forming step comprises forming a plurality of longitudinally extending cooling circuits within said airfoil portion,
- wherein said at least one cooling circuit forming step further comprises forming each said cooling circuit with a plurality of staggered internal pedestals;
- wherein said at least one cooling circuit forming step further comprises using at least one refractory metal core element to form each said cooling circuit;
- wherein said at least one cooling circuit forming step comprises using a plurality of refractory metal core elements to form said cooling circuits;
- and
- wherein said at least one cooling circuit forming step comprises placing each of said refractory metal core elements within a mold.
Dependencies are inferred from the claim text.