| 摘要 |
The invention refers to a rotor blade arrangement (20), especially for a gas turbine, which rotor blade arrangement (20) can be fastened on a blade carrier (19) and comprises in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by blade aerofoil element (10) and platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19). |
