GAS TURBINE ENGINE AIRFOIL WITH BI-AXIAL SKIN COOLING PASSAGE AND CORRESPONDING GAS TURBINE ENGINE

摘要

An airfoil (62) for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls (70, 72) that extend from a leading edge (74) to a trailing edge (76) in a chord-wise direction. A core cooling passage (78, 80) is provided between the pressure and suction side walls (70, 72) and extends in the radial direction. A skin passage (82) is arranged in one of the pressure and suction side walls (70, 72) between the core cooling passage (78, 80) and the exterior airfoil surface. The skin passage (82) includes a first passageway (88) that extends in the radial direction. The first passageway (88) turns to a second passageway (90) that extends in the chord-wise direction to terminate at an exit arranged near the trailing edge (76). A corresponding gas turbine engine is also provided.