| 摘要 |
<p>A disk having a closed channel construction and which is especially suited for supporting the rotating blades of a gas turbine engine is disclosed. In one embodiment, the disk supports the fan blades of a turbofan engine which extend radially therefrom. The disk structurally includes an upstream web, a downstream web and a plurality of arcuate plugs disposed in end to end relationship between the webs to form a toroidal type structure having a substantially rectangular cross section. The disk is contoured to provide a level of torsional and bending stiffness which limits the most critical stage vibratory frequencies to values above the engine operating range while limiting the maximum value of the disk hoop stress during operation to a level below the durability limits of the disk material utilized. A method for making the disk is further disclosed.</p> |
