Patent ID: 9528441
Filing Date: 2016-12-27
CPC Classification: F01D,F02C,F02K,F05D,Y02T,Y10T

Claim Text:
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.