Attachment of a nozzle to a casing of a turbomachine

1. An assembly comprising a turbomachine casing ( 7 ) and a nozzle ( 1 ) made of ceramic matrix composite material having a blade ( 21 ), a frontside and a backside surfaces of which delimit an internal cavity ( 29 ), and which is connected at a radially external end of the blade by a connecting part ( 31 ) of the nozzle ( 1 ) to the casing ( 7 ), said connecting part ( 31 ) extending radially outwards, the blade ( 21 ) and said connecting part ( 31 ) being formed in one piece, said assembly being characterized in that the connecting part ( 31 ) is fastened to a first radial wall ( 85 ) integral with the casing ( 7 ) by fastening means ( 53 ), wherein the radially external end of said connecting part ( 31 ) comprises at least one radial flange ( 49 ), extending strictly radially and extending longitudinally in a direction having a circumferential component and a longitudinal component, substantially similar or parallel to a direction connecting a leading edge to a trailing edge of the blade, the radial flange being applied in the circumferential direction to said first radial wall ( 85 ).

2. An assembly according to claim 1 , characterized in that it the assembly comprises an intermediate part ( 81 ) for fastening the nozzle ( 1 ) to the casing ( 7 ), the intermediate part ( 81 ) comprising a circumferential wall ( 83 ) and said first radial wall ( 85 ), said first radial wall extending radially inward from said circumferential wall ( 83 ) and being fastened to said at least one radial flange ( 49 ) of the connecting part ( 31 ).

3. An assembly according to claim 2 , characterized in that the nozzle ( 1 ) comprises a platform ( 17 ) having a circumferential wall externally defining an air flow path ( 9 ) and a second radial wall ( 65 , 67 ) extending radially outwards from said circumferential wall, said second radial wall ( 65 , 67 ) being fastened by said fastening means ( 53 ) to the first radial wall ( 85 ) and said connecting part ( 31 ).

4. An assembly according to claim 3 , characterized in that fastening means ( 53 ) pass through said flange ( 49 ) of the connecting part ( 31 ), said first radial wall ( 85 ) of the intermediate part ( 81 ) and said second radial wall ( 65 , 67 ) of the platform ( 17 ).

5. An assembly according to claim 2 , characterized in that the nozzle ( 1 ) comprises a platform ( 17 ) having a circumferential wall externally defining an air flow path ( 9 ) and a second radial wall ( 65 , 67 ) extending radially outwards from said circumferential wall, said second radial wall ( 65 , 67 ) being fastened by said fastening means ( 53 ) to the first radial wall ( 85 ) and said connecting part ( 31 ).

6. An assembly according to claim 2 , characterized in that said at least one radial flange ( 49 ) is fastened to said first radial wall ( 85 ) by bolting.

7. An assembly according to claim 2 , characterized in that the connecting part ( 31 ) comprises at least one opening ( 57 , 71 , 97 ) in fluid communication with the internal cavity ( 29 ) of the blade ( 21 ).

8. An assembly according to claim 1 , characterized in that the nozzle ( 1 ) comprises a platform ( 17 ) having a circumferential wall externally defining an air flow path ( 9 ) and a second radial wall ( 65 , 67 ) extending radially outwards from said circumferential wall, said second radial wall ( 65 , 67 ) being fastened by said fastening means ( 53 ) to the first radial wall ( 85 ) and said connecting part ( 31 ).

9. An assembly according to claim 8 , characterized in that said at least one radial flange ( 49 ) is fastened to said first radial wall ( 85 ) by bolting.

10. An assembly according to claim 8 , characterized in that the connecting part ( 31 ) comprises at least one opening ( 57 , 71 , 97 ) in fluid communication with the internal cavity ( 29 ) of the blade ( 21 ).

11. An assembly according to claim 8 , characterized in that the ceramic matrix composite material of the blade ( 21 ) and the connecting part ( 31 ) comprise continuous reinforcing fibers extending in the radial direction.

12. An assembly according to claim 8 , characterized in that said at least one radial flange of the connecting part ( 31 ) comprises two radial flanges ( 49 , 95 a , 95 b ), the radial flanges ( 49 , 95 a , 95 b ) extending parallel and being spaced from each other.

13. An assembly according to claim 1 , characterized in that the nozzle ( 1 ) comprises a platform ( 17 ) having a circumferential wall externally defining an air flow path ( 9 ) and a second radial wall ( 65 , 67 ) extending radially outwards from said circumferential wall, said second radial wall ( 65 , 67 ) being fastened by said fastening means ( 53 ) to the first radial wall ( 85 ) and said connecting part ( 31 ).

14. An assembly according to claim 1 , characterized in that said at least one radial flange ( 49 ) is fastened to said first radial wall ( 85 ) by bolting.

15. An assembly according to claim 1 , characterized in that the connecting part ( 31 ) comprises at least one opening ( 57 , 71 , 97 ) in fluid communication with the internal cavity ( 29 ) of the blade ( 21 ).

16. An assembly according to claim 1 , characterized in that the ceramic matrix composite material of the blade ( 21 ) and the connecting part ( 31 ) comprise continuous reinforcing fibers extending in the radial direction.

17. An assembly according to claim 1 , characterized in that said at least one radial flange of the connecting part ( 31 ) comprises two radial flanges ( 49 , 95 a , 95 b ), the radial flanges ( 49 , 95 a , 95 b ) extending parallel and being spaced from each other.