Turbine blade root configurations
AssigneeGeneral Electric Company
InventorBradley T. Boyer
Life of this patent
Estimating the term…
Abstract
A rotor blade for a turbine engine comprising a root and, extending in a radial direction from the root, an airfoil, wherein: the root comprises a shank and a dovetail; the shank extends from the dovetail and comprises a platform at an radial outward surface; the dovetail includes one or more tangs; the platform comprises an axially and circumferentially oriented surface that defines, at least in part, the inner most radial boundary of the flow path through the turbine; the dovetail is linear; and the platform is curved.
Claims20
A rotor blade for a turbine engine comprising a root and, extending in a radial direction from the root, an airfoil, wherein the root includes a linear dovetail and a curved platform.
A rotor blade for a turbine engine comprising a root and, extending in a radial direction from the root, an airfoil, wherein:
- the root comprises a shank and a dovetail;
- the shank extends from the dovetail and comprises a platform at an radial outward surface;
- the dovetail includes one or more tangs;
- the platform comprises an axially and circumferentially oriented surface that defines, at least in part, the inner most radial boundary of the flow path through the turbine;
- the dovetail is linear;
- and
- the platform is curved.
Dependencies are inferred from the claim text.