Blade/disk dovetail backcut for blade/disk stress reduction...

Details Blade/disk dovetail backcut for blade/disk stress reduction... Blade/disk dovetail backcut for blade/disk stress reduction...

2006-06-28

2008-10-21

Edgar, Richard (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific working member mount

Blade received in well or slot

C416S248000

Reexamination Certificate

active

07438532

ABSTRACT:
Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

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