| 摘要 |
PROBLEM TO BE SOLVED: To provide a dovetail assembly 61 comprising a non-parallel relief surface 82 that aids in reducing brinelling on a pressure surface in a turbine engine 10. SOLUTION: The dovetail assembly 61 comprises a plurality of rotor blades 24 including a dovetail 44. The dovetail comprises at least a pair of blade claws (66, 68, 70, 72) including blade relief surfaces (82, 84). The dovetail assembly further comprises a rotor disk 26 including a plurality of dovetail slots 60, and each slot is made in a size for receiving the dovetail. Each slot is formed of at least a pair of opposed disk claws (120, 122, 124, 126) including disk relief surfaces (148, 150). The disk relief surfaces are non-parallel to the blade relief surfaces when the dovetail is fitted in the dovetail slot. |
