Invention Grant
US09376926B2 Gas turbine engine fan blade lock assembly 有权
燃气涡轮发动机风扇叶片锁组件

Gas turbine engine fan blade lock assembly
Abstract:
A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub.
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