| 摘要 |
A multi-component hybrid turbine blade (10) comprises a shank portion (12) and an airfoil portion (14). The airfoil portion (14) comprises a composite section (28) having a first density. The composite section (28) comprises a recess (40) and an insert section (38). The insert section (38) has a second mass density, which is less than the first mass density. The insert section (38) is disposed in the recess (40), and the insert section (38) is bonded to the composite section (28). The composite section (28) and the insert section (38) together define an airfoil shape. A fabrication method comprising laying up composite material layers to form a portion of the composite section. The portion of the composite section comprises a recess. Disposing the insert section in the recess. Laying up additional composite material layers to achieve a final desired thickness of the composite section while covering the insert section. |
