| 摘要 |
A gas turbine engine airfoil comprises first and second opposite sides joine d together at spaced-apart leading and trailing edges and extending from a root to a ti p. 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 a nd the trailing edge. The discharge aperture has a tip component and a trailing edg e component to provide for effective cooling of the trailing tip corner region of the airfoil.
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