Patent ID: 9033669
Filing Date: 2015-05-19
Classification: F01D,F05D

Abstract:
1. A rotating airfoil component of a turbomachine, the component comprising an airfoil portion aligned in a spanwise direction of the component, a shank portion, and a platform therebetween oriented transverse to the spanwise direction, the platform comprising: an outer radial surface adjacent the airfoil portion, the outer radial surface being adapted to define a radially inward boundary of a gas flow path when installed in the turbomachine so as to be subjected to gas flow in a flow direction when installed in the turbomachine; an inner radial surface adjacent the shank portion and oppositely-disposed from the outer radial surface; a cross-section between the outer and inner radial surfaces in the spanwise direction; oppositely-disposed first and second end walls, each of the end walls being between and contiguous with the outer and inner radial surfaces and approximately aligned with the flow direction; and at least a first recessed region in the outer radial surface, the first recessed region extending in a shank direction opposite the spanwise direction from a platform plane that contains an upstream portion of the outer radial surface in an upstream direction from the first recessed region opposite the flow direction and also contains a downstream portion of the outer radial surface in the flow direction from the first recessed region, the first recessed region being contiguous with the first end wall and extending therefrom toward the airfoil portion, the first recessed region defining a surface shape when viewed in the shank direction, the first recessed region defining a profile shape transverse to the flow direction and extending from the first end wall toward the airfoil portion, wherein the profile shape of the first recessed region is a continuous planar profile shape extending from the first end wall toward the airfoil portion.