Patent ID: 9004874
Filing Date: 2015-04-14
Classification: F01D,F05D

Abstract:
1. A turbomachinery blade, comprising: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix, wherein the shank includes a pair of spaced-apart side faces, the side faces cooperatively defining: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum; wherein a first transition portion is disposed between the first neck portion and the second neck portion, and wherein the side faces are convex-curved within the first transition portion.