FILM COOLING OF TURBINE AIRFOIL WALL USING MESH COOLING HOLE ARRANGEMENT

Abstract

A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least at a pressure side and extending from an internal chamber to the airfoil exterior. The cooling holes of each plurality extend generally parallel to one another. The cooling holes of the first and second pluralities intersect so as to define a plurality of spaced apart internal solid nodes in the side wall having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes which extend between and along opposite sides of adjacent nodes and a plurality of flow intersections which interconnect the hole portions of the cooling holes and are disposed between the corners of adjacent nodes. The sides of the nodes have lengths which are greater than the widths of the hole portions between adjacent nodes such that, when cooling fluid is passed through the cooling holes, jet flow actions are created through the hole portions which in turn generate jet interactions at the flow intersections to cause restriction of air flow and produce a pressure drop. Also, the cooling holes have flow inlets at the internal surface and flow outlets at the external surface of the airfoil side wall. The area of the flow inlets is substantially less than the area of the flow outlets.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1CHING-PANG LEE

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