Gas turbine bladed disk

Details Gas turbine bladed disk Gas turbine bladed disk

F - Mech Eng,Light,Heat,Weapons

01

D

170/73

F01D 5/14 (2006.01) F01D 5/30 (2006.01)

Patent

CA 2034478

GAS TURBINE BLADED DISC Abstract A new and improved rotor blade and bladed disk assembly are disclosed. In the preferred embodiment, the blade includes a curved and twisted dovetail disposed generally parallel to a sloping outer perimeter of a rotor disk which allows the dovetail to accommodate centrifugal loading of the blade through complementary dovetail slots for obtaining improved low cycle fatigue and high cycle fatigue life limits and a relatively stiff blade for maintaining 2/REV margin. In an exemplary embodiment, the dovetail comprises a section of a helix and the dovetail is self retaining in the dovetail slot against axial components of centrifugal loading.

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