Aircraft turbofan comprising an intermediate ring with simplified downstream support

1. An assembly for an aircraft turbofan comprising a flowpath splitter, said assembly comprising, downstream of said flowpath splitter, a fan flowpath inner delimitation ring and a compressor case located radially inwards from the delimitation ring, the assembly also comprising a plurality of outlet guide vanes passing through the fan flowpath and being provided with an inner platform located in the downstream continuity of the delimitation ring,

wherein the assembly comprises at least one part to support the delimitation ring, said support part comprising a radially outer end fixed to a downstream part of this ring and a radially inner end fixed to the compressor case,

wherein the delimitation ring is formed from a single part around 360°;

wherein the assembly also comprises a coupling ring making the aerodynamic link between an upstream end of the delimitation ring and a downstream end of the outer delimitation wall of the fan flowpath defined by the splitter;

wherein the splitter comprises an axial stop cooperating with a complementary axial stop on the upstream end of the delimitation ring, so as to retain the delimitation ring in the upstream direction; and

wherein the assembly is designed such that the delimitation ring can be put into position by sliding it along the upstream to downstream direction around the splitter, until cooperation between said axial stop and complementary axial stop.

2. The assembly according to claim 1 , comprising sealing means between the downstream end of the delimitation ring and the upstream edge of the inner platform of each outlet guide vane.

3. The assembly according to claim 1 , wherein said assembly is free of any mechanical support for the downstream end of the delimitation ring on the upstream edge of the inner platform of each outlet guide vane.

4. The assembly according to claim 1 , wherein the upstream edge of the inner platform of each outlet guide vane is plane, and orthogonal to a longitudinal axis of the turbine engine.

5. The assembly according to claim 1 , wherein the radially outer end of each support part is fixed to the delimitation ring using screwed elements, preferably with axes orthogonal to the longitudinal axis of the turbine engine, and/or in that the radially inner end of each support part is fixed to the compressor case by screwed elements, preferably with axes parallel to the longitudinal axis of the turbine engine.

6. The assembly according to claim 1 , comprising a plurality of support parts at a circumferential spacing from each other.

7. The assembly according to claim 1 , wherein said coupling ring is made from a single piece or comprises several ring sectors added on independently between the splitter and the delimitation ring, and wherein said coupling ring comprises a material selected from the group consisting of a metallic material, titanium, aluminium, aluminium alloys, a composite material, an elastic material, and an elastomer.

8. An aircraft turbofan comprising an assembly according to claim 1 .

9. A method for assembling an assembly according to claim 1 , comprising a step of installing the delimitation ring, on an assembly comprising the compressor case, the splitter and each support part fixed to the case, by sliding this delimitation ring along the axial upstream-to-downstream direction around the splitter, until cooperation develops between said axial stop and said complementary axial stop, and wherein this step is followed by a step to assemble the coupling ring between the outer wall of the splitter and the delimitation ring.