| 摘要 |
The invention relates to a rotating blade system for a row of rotating blades of a turbomachine, especially a thermal gas turbine, comprising at least two rotating blade clusters (10a, 10b), each comprising at least two rotating blades (12) arranged at least predominantly radially in relation to a rotational axis of the row of rotating blades, between a radially inner and a radially outer covering strip (14a, 14a', 14b, 14b'), and coupled to the covering strips (14a, 14a', 14b, 14b'). At least the radially outer covering strips (14b, 14b') of the two rotating blade segments (10a, 10b) comprise contact surfaces corresponding with each other, radial equilibrium axes (A) of adjacent rotating blades (12) of the at least two rotating blade clusters (10a, 10b) being arranged respectively axially in a tilted manner at an angle (aa, ab) in relation to the respective basic tilt thereof, the angles (aa, ab) having opposite signs to the basic tilt. The invention also relates to a turbomachine, and to a method for mounting a row of rotating blades for a turbomachine. |
