Patent ID: 6761534
Filing Date: 2004-07-13
Classification: F01D

Abstract:
An open cooling circuit for a gas turbine airfoil and substantially planar tip shroud at a radially outermost end of the airfoil and extending in a plane substantially perpendicular to the airfoil comprising:a first group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a leading edge of the airfoil; a second group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a trailing edge of the airfoil; a common plenum in the tip shroud in direct communication with said first and second group of cooling holes, said plenum extending throughout substantially all of the tip shroud and within the plane of the tip shroud wherein said plenum is sealed by a pair of covers located over the first and second groups of cooling holes and further wherein a metering hole is provided in at least one of said covers; and a plurality of exhaust holes extending from said plenum, through said tip shroud and opening along a peripheral edge of the tip shroud.