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US 5,310,317 AGranted
Quadra-tang dovetail blade
AssigneeGeneral Electric Company
InventorsMark J. Bailey, Robert K. Mitchell, Jr.
Life of this patent
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Abstract
A gas turbine engine rotor blade includes an airfoil joined to a dovetail. The dovetail includes a shank from which extends two pairs of dovetail tangs being defined by a bifurcating slot disposed therebetween. The dovetail is configured for retention in a complementary dovetail groove in a rotor disk with the bifurcating slot remaining empty for reducing weight of the blade while transferring centrifugal loads from the blade to the rotor disk.
Claims8
A rotor blade adapted to be positioned radially in a gas turbine engine comprising:
- an airfoil having a root and a tip;
- and a dovetail extending from said airfoil and including:
- a shank having a top fixedly joined to said airfoil root, and a bottom spaced from said shank top;
- first and second pairs of dovetail tangs extending radially inwardly from said shank bottom, said first pair including first and second integral dovetail tangs, and said second pair including third and fourth integral dovetail tangs, said dovetail tang pairs being symmetrical about a dovetail axis and being defined by a bifurcating slot disposed therebetween for spacing apart said dovetail pairs, said first and third dovetail tangs being coextensive on one side of said dovetail axis, and said second and fourth dovetail tangs being coextensive on an opposite side of said dovetail axis;
- and
- said dovetail being configured for retention in a complementary dovetail groove in a rotor disk with said bifurcating slot remaining empty for reducing weight of said blade while carrying centrifugal load from said blade to said rotor disk.
3 more elements
Dependencies are inferred from the claim text.