Retention device for a composite blade of a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorSteven A. RADOMSKI
Life of this patent
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Abstract
A liner 2 for a composite blade 40 of a gas turbine engine is disclosed. The liner comprises a metallic shoe 4, operable substantially to encase a blade root 42 of a composite blade 40 and defining an inner surface 17 and an outer surface 19. The liner 2 further comprises a retention lug 6 formed on the shoe 4 and comprising inner and outer keys 24, 22 which project from opposed portions of the inner and outer surfaces. The keys are operable to engage corresponding recesses on a dovetail slot and a blade root to resist axial displacement of the composite blade.
Claims14
A liner for a composite blade of a gas turbine engine, the liner comprising a metallic shoe for at least partially encasing a blade root of a composite blade, metallic shoe having an inner, an outer surface, and a retention lug, wherein the retention lug comprises an outer key which projects from an outer surface of the retention lug for axial retention of the blade.
Dependencies are inferred from the claim text.