Composite splitter lip for axial turbomachine compressor

1. A splitter lip for a turbomachine, the splitter lip comprising:

an upstream annular wall with a circular leading edge;

a downstream annular partition,

wherein the upstream wall comprises an annular anchoring portion arranged in the thickness of the downstream partition so as to anchor the partition and the wall to one another, wherein the downstream partition comprises an outer annular surface and an inner annular surface, the anchoring portion being at a distance from the outer annular surface and the inner annular surface, and wherein materials of the anchoring portion and of the downstream partition are intermeshed, the material of the downstream partition occupying the majority of an apparent volume defined the anchoring portion, the apparent volume being the true volume of the anchoring portion plus the volume of openings formed therein.

2. The splitter lip in accordance with claim 1 , wherein the anchoring portion comprises a grid with hexagons or triangles.

3. The splitter lip in accordance with claim 1 , wherein the anchoring portion comprises multiple anchoring roughnesses distributed over a surface thereof.

4. The splitter lip in accordance with claim 1 , wherein the anchoring portion comprises multiple anchoring openings through which passes the material of the downstream partition.

5. The splitter lip in accordance with claim 1 , wherein the anchoring portion comprises a network of interconnected junctions repeating a pattern substantially all around the splitter lip.

6. The splitter lip in accordance with claim 1 , wherein the downstream partition comprises an annular shell forming an outer annular surface.

7. The splitter lip in accordance with claim 1 , wherein the downstream partition and the upstream wall each comprise outer annular surfaces, the outer annular surfaces being tangential on the circumference of the splitter lip.

8. The splitter lip in accordance with claim 1 , wherein the upstream wall comprises a strengthening annular thickened portion, the leading edge being formed on the annular thickened portion.

9. The splitter lip in accordance with claim 1 , wherein the upstream wall comprises a profile of revolution with a portion delimited by an arc, the anchoring portion extending axially from the arc, the arc and the anchoring portion extending over the majority of the thickness of the upstream wall.

10. The splitter lip in accordance with claim 1 , wherein the anchoring portion forms a zone of lesser thickness on the upstream wall.

11. The splitter lip in accordance with claim 1 , wherein the anchoring portion is delimited upstream by at least one annular step.

12. The splitter lip in accordance with claim 1 further comprising an outer shroud surrounded by the downstream partition.

13. The splitter lip in accordance with claim 12 , wherein the splitter lip comprises an annular row of stator vanes supported by the outer shroud.

14. The splitter lip in accordance with claim 1 , wherein the upstream wall comprises an annular attachment hook oriented axially in the downstream direction.

15. The splitter lip in accordance with claim 1 , wherein the material of the downstream partition comprises a composite material with an organic matrix and fibres, the downstream partition being solid.

16. A turbomachine comprising a splitter lip, wherein the splitter lip comprises:

a composite downstream partition, and

an upstream annular wall comprising:

a circular leading edge; and

a projection for attachment in the thickness of the downstream partition,

wherein the upstream annular wall being made of another material than the composite downstream partition,

wherein materials of the projection and of the downstream composite partition are intermeshed, the composite material of the downstream partition occupies the majority of the extent of the projection, the majority of the extent of the projection being devoid of material before the projection is anchored into the composite downstream partition.

17. The turbomachine in accordance with claim 16 further comprising a compressor with an inlet delimited by the splitter lip.

18. The turbomachine in accordance with claim 16 further comprising a fan, the splitter lip surrounding the fan.

19. A method for producing a splitter lip for an axial turbomachine, wherein the splitter lip comprises an upstream annular wall with a circular leading edge and a composite downstream annular partition, said method comprising:

(a) providing the upstream annular wall, wherein the upstream wall comprises an anchoring portion; and

(b) moulding the downstream partition onto the anchoring portion so as to anchor the upstream wall in the downstream partition via the anchoring portion, wherein the downstream partition comprises an outer annular surface and an inner annular surface, the anchoring portion being at a distance from the outer annular surface and the inner annular surface, and wherein materials of the anchoring portion and of the downstream partition are intermeshed, the material of the downstream partition occupying the majority of an apparent volume defined the anchoring portion, the apparent volume being the true volume of the anchoring portion plus the volume of openings formed therein.

20. The method in accordance with claim 19 , wherein moulding a downstream partition onto the anchoring portion includes the application of an injection mould against an outer annular surface of the upstream annular wall.