Patent ID: 7270514

Claim:
A turbine blade for a gas turbine engine, comprising: (a) an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge; (b) the first and second sidewalls extending from a root positioned adjacent a dovetail to a tip cap; (c) a squealer tip extending outwardly from the tip cap, the squealer tip comprising: (i) a plurality of spaced-apart notches formed in the airfoil proximate the tip cap and between the leading edge and the trailing edge of the airfoil, wherein each notch is recessed with respect to the first sidewall to form a respective tip shelf, and further wherein each notch is defined by a top wall oblique with respect to a plane perpendicular to a longitudinal axis of the blade and oblique to the first and second spaced-apart sidewalls, and the respective tip shelves are perpendicular to a surface of the first and second spaced-apart airfoil sidewalls; and (ii) at least one hole in each tip shelf communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil.