| 摘要 |
<p>13LN-1496 An integral composite airfoil and disc assembly for use in a turbomachine is provided wherein the assembly includes an airfoil portion having a plurality of axially adjacent first filaments extending in a first direction. The assembly further includes a hub portion having at least one second filament extending in a second direction and a matrix material dispersed between filaments of the first plurality and the second filament. The first and second filaments are disposed so as to extend in the direction of principal stress in the airfoil and disc portions respectively.</p> |
