| 摘要 |
<p>A blade retaining system for securing rotor blades (14) to a rotor disc (12) used in gas turbine engines includes an inwardly radially extending annular groove (22) defined in the periphery of the rotor disc (12), intersecting the 'fir tree' (20) mounting slots into which the rotor blades (14) are mounted. A resilient split ring (32) is received in both the annular groove of the rotor disc (22) and a groove (28) defined in the bottom end (30) of the root portion (18) of each blade (14), in order to restrain axial movement of the blade (14) relative to the rotor disc (12). The resilient split ring (32) under its radial expanding spring force, radially and outwardly abuts the rotor blades (14) and is radially spaced apart to ensure the engagement in both the grooves (22) of the rotor disc (12) and each rotor blade (14), while permitting disengagement therefrom when required. The resilient split ring (32) is disposed downstream of the cooling air inlets (40) in the bottom end (30) of each rotor blade (14) to direct the cooling air into the inlets (36) in order to facilitate the blade cooling air circulation (F). The blade retaining structure is simple to manufacture and maintain.</p> |
