| 摘要 |
The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support 19 to an outer ferrule support 14, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors 20,15 respectively, the plurality of fixed vanes comprising so-called structural vanes 5 surrounding so-called non-structural or aero vanes 6 so as to form boxes 7, said structural vanes 5 being rigidly attached to the ends of the sectors of the inner ferrule support 20 by means of attachment elements 17 in order to impart increased stiffness to the boxes 7.
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