GAS TURBINE BLADED DISK ASSEMBLY

摘要

13LN-1691 GAS TURBINE BLADED DISK ASSEMBLY 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.