Patent ID: 9120144
Filing Date: 2015-09-01
Classification: B22C,F01D

Abstract:
1. A casting core comprising: an airfoil portion having: an airfoil base end, an airfoil tip end, a concave side exterior surface, a convex side exterior surface, a leading edge, and a trailing edge, wherein the airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end, wherein the airfoil portion comprises a first void between the concave side exterior surface and the convex side exterior surface and extending radially, the first void defined by a first leading edge surface of the airfoil portion extending between the concave side exterior surface and the convex side exterior surface and extending radially, and a first trailing edge surface of the airfoil portion extending between the concave side exterior surface and the convex side exterior surface and extending radially, wherein in a radial cross section the first void tapers from one of the concave side exterior surface and the convex side exterior surface to the other of the side exterior surfaces, wherein the first leading edge surface and the first trailing edge surface are twisted from the airfoil base end to the airfoil tip end of the first void, and wherein the casting core is configured to define a serpentine cooling channel.