Importance

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Abstract

A locking system for blades in a circumferential dovetail groove in a rotor of a gas turbine engine, the blades having dovetail roots in the groove and platforms resting on steady rest flanges on the outside surface of the rotor on opposite sides of the slot between converging shoulders of the dovetail groove. The blade locking system includes an inner lock member between roots of a pair of adjacent blades, an outer lock member captured in aligned notches in the steady rest flanges between the rotor and the platforms of the adjacent blades, and a screw extending through a clearance hole in the outer lock member into a threaded bore in the inner lock member. When the screw is tightened, the inner and outer lock members are clamped against the rotor.

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First Claim