| 摘要 |
The invention relates to a turbo engine (1), especially a gas turbine, with a rotor (25) that extends along an axis of rotation (15). Said rotor (25) comprises a peripheral surface (31) that is defined by the outer radial delimiting surface of the rotor (25) and a receiving structure (33) and a first rotor blade (13A) and a second rotor blade (13B) which have each a bla de root (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first rotor blade (13A) and the blade platform (17B) of the second rotor blade (13B) adjoin. The blade platforms (17A, 17B) and the peripheral surfac e (31) define between them an intermediate space (49). A sealing system (51) i s provided on the peripheral surface (31) in the intermediate space (49), said sealing system being of the labyrinth box type.
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