초록 ▼

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 maint

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.

대표청구항 ▼

A gas turbine engine blade comprising: an airfoil having a root; a shank extending from said airfoil root; and a dovetail extending from said shank; said shank having two oppositely facing lateral surfaces, and first and second oppositely facing end surfaces, said lateral surfaces being wider than s

A gas turbine engine blade comprising: an airfoil having a root; a shank extending from said airfoil root; and a dovetail extending from said shank; said shank having two oppositely facing lateral surfaces, and first and second oppositely facing end surfaces, said lateral surfaces being wider than said end surfaces, and said shank second end surface including a pocket extending therein toward said shank first end surface and between said dovetail and said airfoil root, said pocket defining first and second laterally spaced and longitudinally extending legs, said shank including a solid forward portion extending from said first surface to said pocket, said airfoil being generally aligned with respect to a longitudinal axis of said blade along substantially only said first leg and said solid forward portion for providing a generally straight load path from said airfoil to said dovetail.