Cooled airfoil trailing edge tip exit

Details Cooled airfoil trailing edge tip exit Cooled airfoil trailing edge tip exit

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01)

Patent

CA 2560811

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.

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