| 摘要 |
<p>A vane assembly for a gas turbine engine includes: a first mounting platform (106) having a first slot (116); a first airfoil (110) extending from the first mounting platform (106); and a feather seal (104) having opposing faces (120, 122), a first side (126) extending between the faces (120, 122), and a first tab, the first tab (131) extending outwardly beyond the first side (126); the first slot (116) being sized and shaped to receive the feather seal (104) including the first tab (131).</p> |
