| 摘要 |
A rotor disk 44 for a gas turbine engine having an axis of rotation 24 and an axial centerline 60 includes a rim 48, forward and aft hubs 54,56, and forward and aft webs 50,52. The forward web 50 extends between the rim 48 and the forward hub 54, and the aft web 52 extends between the rim 48 and the aft hub 56. The forward and aft hubs 54,56 are separated. Each web 50,52 is skewed from the axial centerline 60. A circumferentially extending cavity 62 is formed between the webs 50,52 and the hubs 54,56. <IMAGE> |
