Sub-assembly for a low-pressure compressor of an aircraft turbine engine

A sub-assembly for a low-pressure compressor of an aircraft turbine engine extending along an engine axis directed from upstream towards downstream, the sub-assembly comprising:

• a rotor comprising a hub extending axially and circumferentially around the engine axis;
• and
• a stator comprising a straightener equipped with vanes extending substantially radially towards the hub;
• wherein:
• the hub comprises an inner recess directed towards the engine axis;
• and
• the rotor comprises an inner shroud:
• covering the inner recess so as to define a cavity between the hub and the inner shroud,
• each of the vanes comprising a free head facing at least partially the inner shroud and/or the cavity;
• comprising orifices in fluidic communication with the cavity;
• and wherein the cavity is partitioned into cells bounded by edges, each cell extending both axially and circumferentially, in an axially inclined direction, so that each cell comprises:
• a downstream segment radially facing a space between first and second of the vanes which are successively circumferentially aligned;
• and
• an upstream segment radially facing another space between third and fourth of the vanes which are successively circumferentially aligned, at least one of the third and the fourth vanes being distinct from both the first and second vanes, the fourth vane corresponding to the first vane, so that the third, first and second vanes, in that order, are successively aligned circumferentially:
• wherein the inner recess is formed by at least one deformation of a wall of the hub, and the inner shroud is formed of an annular plate portion.