Turbine airfoil cooling passageway

摘要

An internally cooled gas turbine engine turbine vane (120) has an outboard shroud (24) and an airfoil (26) extending from an outboard end (30) at the shroud to an inboard end (28). A cooling passageway (50) has an inlet (52) in the shroud, a first turn (62) at least partially within the airfoil, a first leg (60) extending from the inlet inboard through the airfoil to the first turn, and a second leg (70) extending from the first turn. A dividing wall (122) is in the passageway and has an upstream end (124) in an outboard half of a span of the airfoil and has a plurality of vents (140). The vane may be formed as a reengineering of a baseline configuration (20) lacking the dividing wall.