| 摘要 |
The blades (1, 11, 12, 13, 1n) of a turbine or compressor are fastened into a groove (8) on the rotor (6) or stator of the turbine or compressor by means of the blade roots (4), there being no play or a prestress prevailing between the root plate (3) and/or the blade root (4), and adjacent blades (1, 11, 12, 13, 1n) thereby being supported relative to one another with respect to torsional moments (12) and not or only slightly on the rotor (6) or stator. This is possible, for example, by means of a bevel (9).
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