| 摘要 |
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. |
