| 摘要 |
<p>A turbine blade assembly, in particular of a gas turbine, comprising a turbine disc (4) with rotor blades (2) inserted onto notches (8) of the turbine disc (4) and locking plates (16) that are placed inside circular grooves (11, 13) with rims (10, 12) in the turbine disc (4) and in the rotor blades wherein the edges of the locking plates (16) that are orientated towards the center of the turbine disc (4) are castellated by providing teeth (18) and wherein a part of the rim (12) of the circular groove (13) of the turbine disc (4) is also castellated by providing gaps which match the teeth (18) of the locking plates (16). The plates are sprung to provide both locking and sealing capabilities during engine operation.</p> |
