US Patent 7300250 Cooled airfoil trailing edge tip exit

A gas turbine engine airfoil comprises first and second opposite sides joined together at spaced-apart leading and trailing edges and extending from a root to a tip. An internal cooling passage is provided for channelling coolant through the airfoil. The internal cooling passage has a discharge aperture at a juncture of the tip and the trailing edge. The discharge aperture has a tip component and a trailing edge component to provide for effective cooling of the trailing tip corner region of the airfoil.