General Electric Company

Douglas Bryan Ballantyne

Mark Douglas Gledhill

Gaoqiu Zhu

David D Klassen

A turbine blade assembly for a gas turbine engine that includes a turbine platform including contoured edges. The turbine blade assembly includes a platform, a turbine airfoil extending radially outward from the platform, a shank that extends radially inward from the platform, and a dovetail extending from the shank. The platform includes a leading edge and a trailing edge separated by a pressure edge and an opposite suction edge, the pressure edge including a plurality of arcs extending between the leading edge and the trailing edge, the suction edge including a plurality of arcs extending between the leading and trailing edges.

Method and apparatus for turbine blade contoured platform

Disclosed is a bladed disk assembly having a new and improved rotor blade. The blade includes a shank and dovetail extending from an airfoil portion thereof. The shank includes a pocket extending therein from an end surface thereof. The shank pocket allows for reduced weight of the blade while maintaining acceptable bending stiffness thereof. In an exemplary embodiment of the invention, the bladed disk assembly is effective for being interchangeable with a blisk assembly having an inlet hub radius ratio of about less than about 0.5 and a root solidity of greater than about 2.2.

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Ipswich, MA, United States of America

Douglas Bryan Ballantyne