| 摘要 |
<p num="1">The invention relates to a guide-vane arrangement (1) of a turbo-machine (4), in particular, a gas turbine. Said device comprises at least one guide vane support (2) which is secured to the housing (5) of a turbo-machine (4), several guide vanes (3) which are secured to the guide vane support (2) and are arranged adjacent to each other in the direction of the periphery. Each guide vane (3) comprises a platform (6) which comprises a first locking section (8) and a second locking section (9) which is arranged at an axial distance therefrom. The vane guide support (2) comprises a first support section (12) and the second support section (13) is arranged at an axial distance therefrom. Each locking section (8, 9) and the respective support section (12, 13) are embodied in such a manner that they provide an axially insertable and radial positive fit connection between the guide vane support (2) and the respective guide vane (3). At least one securing element (14) is secured to the guide vane support (2) and is embodied in such a manner that it forms an axial fixation for at least one of the guide vanes (3).
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