| 摘要 |
The invention relates to a blade of a turbomachine, in particular of a gas turbine, comprising at least one fastening section (10) for fastening the same in a locating section (11) of a rotor-side or stator-side component of the turbomachine. According to the invention, the or each fastening section (10) has a core region (18) which is made of a relatively brittle and relatively light material and is embedded in an encasing region (19) made of a material having relatively high ductility. |
