| 摘要 |
A turbomachine blade assembly (100a) comprises at least two blades (100) assembled adjacent each other and defining a gap (G) as well as three feather seals (207, 209a, 209b), each blade including a blade root (101) defining three feather seal slots on a lateral portion thereof. The seal slots include two leg slots (109a, 109b), each leg slot extending radially, and a cross member slot (107) extending axially. An airfoil portion (103) extends radially from the blade root. |
