Patent ID: 10145246

Abstract:
An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.