VANE FOR A GAS TURBINE ENGINE AND METHOD FOR COMMUNICATING A COOLING AIRFLOW WITHIN A COMPONENT

A component for a gas turbine engine (20) includes a mateface (82) with a purge flow interface (98), the mateface (82) comprises a pocket (100) located in communication with a feather seal slot (90) in the mateface (82). A vane (72) for a gas turbine engine (20) includes a platform (76, 78) that extends from the airfoil (74), the platform (76, 78) comprising a mateface (82) with a feather seal slot (90) and a pocket (100) in communication with the feather seal slot (90), wherein the pocket (100) is of a cross-sectional shape larger than the feather seal slot (90).