| 摘要 |
The present disclosure provides devices related to aircraft engine fan assemblies (300) and blade lock retainers (210). In various embodiments, a blade lock retainer (210) is formed from sheet metal and comprises an annular ring portion (211), an outer retainer tab portion (212), and an inner tab portion (213). In various embodiments, the outer retainer tab portion (212) is disposed on an outer circumference of the annular ring portion (211), oriented substantially perpendicular to the annular ring portion (211), and extends in an aft direction from the annular ring portion (211). In various embodiments, the inner retainer tab portion (213) is disposed on an inner circumference of the annular ring portion (211) and radially aligned with the outer retainer tab portion (212), oriented substantially perpendicular to the annular ring portion (211), and extends in a forward direction from the annular ring portion (211). |
