INTERNAL 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 formed within the interior structure of the side walls of the airfoil so as to extend between and along but not intersect spaced internal and external surfaces of the side walls extending between leading and trailing edge portions of the airfoil. 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 walls having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes extending between and along opposite sides of adjacent nodes and a plurality of flow intersections interconnecting the hole portions of the cooling holes and being 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. The jet interactions restrict air flow and produce a pressure drop which creates turbulences in the air flow that enhance convective heat transfer between the airfoil side walls and the cooling air.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1CHING-PANG LEE

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