Patent ID: 8708649

Claim:
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 ( 20 ) of the inner ferrule support by means of attachment elements ( 17 ) in order to impart increased stiffness to the boxes ( 7 ); and wherein each sector of the outer ferrule support ( 15 ) comprises a zone ( 23 ) of reduced thickness at each of its ends, said zone forming with the zone ( 23 ) of the sector positioned side by side, a housing for a platform ( 9 ) of each structural vane at a blade head of each structural vane, said housing being of dimensions that are substantially equal to the dimensions of the platform ( 9 ) of each structural vane at the blade head of each structural vane and being positioned in the aerodynamic vein.