| 摘要 |
A blade (200) of a gas turbine engine is provided having an airfoil (202), a platform (204), a shank (206), a dovetail (208), and a skirt (218). The airfoil (202) may extend distally from the platform (204), and the shank (206) may extend proximally from the platform (204). The dovetail (208) may also be provided to extend proximally from the shank (206). The skirt (218) may be disposed on an aft side of the shank (206) and may extend from the shank (206) in a direction at least partially axially aft from the shank (206). |
