| 摘要 |
<p>A dovetail assembly (61) including non-parallel relief faces (82) that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail (44). Each dovetail includes at least a pair of blade tangs (66, 68, 70, 72) including blade relief faces (82, 84). The dovetail assembly also includes a rotor disk (26) including a plurality of dovetail slots (60), each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs (120, 122, 124, 126) including disk relief faces (148, 150). The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.</p> |
