Stator assembly for an aircraft turbine engine

An assembly for an aircraft turbine engine having a longitudinal axis comprising a distributor which has a ring of stator vanes (10) including a foot at a radially inner end of the distributor, the foot having an annular seal configured to engage in a non-contact sealing manner with a cylindrical shroud of a rotor of the turbine engine, which shroud is disposed radially under the distributor, the seal comprising:

• a plurality of seal segments distributed circumferentially about the longitudinal axis,
• each seal segment comprising:
• a radially outer annular wall segment;
• and
• a radially inner annular wall segment connected to each other by an elastically deformable member,
• wherein each radially outer annular wall segment is attached to a seal support, the seal support being annular and being secured to the foot of the distributor and wherein the seal support comprises at least two radial annular tongues spaced longitudinally apart from one another and between which a radial partition of the foot of the distributor is mounted by radial sliding.