Structural and aerodynamic module for a turbomachine casing and casing structure comprising a plurality of such a module

1. A module for producing a turbomachine casing comprising:

two blades each extending along a longitudinal axis, each blade each comprising a leading edge, a trailing edge, a radially inner edge and a radially outer edge, the radially outer and radially inner edges of the blades having a curved profile, said blades comprising bores for passage of screws,

a radially inner platform mechanically connecting the radially inner edges of the two blades, and

a radially outer platform mechanically connecting the radially outer edges of the two blades,

wherein the two blades and the radially outer and inner platforms delimit a flow stream,

wherein the two blades and the radially outer platform are made from a composite material, and

wherein the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies mounted in the bores of the blades.

2. The module according to claim 1 , wherein an axis of the screws is substantially orthogonal to the longitudinal axes of the blades.

3. The module according to claim 1 , wherein the blades and the radially outer platform comprise fibers woven in three dimensions.

4. The module according to claim 3 , wherein the fibers of the blades and the fibers of the radially outer platform are the same.

5. A platform for making a module according to claim 1 , intended to connect two blades at radially outer edges or radially inner edges thereof, said edges being fixed on the platform by screw-nut assemblies, said platform comprising two opposite lateral edges intended to be in contact with faces of the blades comprising bores intended to be passed through by the screws, said lateral edges having a curved profile corresponding to a curved profile of the blades, said platform being made from a composite material.

6. The platform according to claim 5 , wherein the platform is a radially inner platform comprising a radially outer face which recreates a flow stream.

7. A structure comprising:

a plurality of modules arranged angularly on an inner hub, each module comprising:

two blades each extending along a longitudinal axis, each blade each comprising a leading edge, a trailing edge, a radially inner edge and a radially outer edge, the radially outer and radially inner edges of the blades having a curved profile, said blades comprising bores for the passage of screws,

a radially inner platform mechanically connecting the radially inner edges of the two blades, and

a radially outer platform mechanically connecting the radially outer edges of the two blades,

wherein the two blades and the radially outer and inner platforms delimit a flow stream,

wherein the two blades and the radially outer platform are made from a composite material, and

wherein the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies in the bores of the blades.

8. The structure according to claim 7 , wherein said modules are arranged relative to each other so that a distance between two blades of two adjacent modules is substantially equal to a distance between two blades of a same module.

9. The structure according to claim 7 , further comprising a first group of at least one metal vane in angular position at twelve o'clock and a second group of at least one metal vane in angular position at six o'clock, the modules being arranged between the first and second groups of metal vanes.

10. The structure according to claim 9 , further comprising:

first radially inner aerodynamic panels and first radially outer aerodynamic panels arranged between each pair of modules so as to recreate flow streams, and

second aerodynamic panels arranged between each pair of metal vanes between two radially outer platforms.

11. The structure according to claim 7 , further comprising radially inner aerodynamic panels and radially outer aerodynamic panels arranged between each pair of modules so as to recreate the flow streams.

12. A turbomachine comprising a structure according to claim 7 .

13. The turbomachine according to claim 12 , forming a dual-flow turbojet engine, wherein the structure forms an intermediate casing fixed on an inner hub and on an outer shroud.