Stator assembly for an aircraft turbine engine

A seal for an aircraft turbine engine, the seal comprising a plurality of seal segments that are circumferentially distributed about a longitudinal axis, each seal segment comprising:

• a radially outer annular wall segment;
• a radially inner annular wall segment, the radially outer and radially inner wall segments connected to each other by an elastically deformable member, the radially outer annular wall segments forming a monolithic outer shroud, the radially inner annular wall segments arranged circumferentially end-to-end, each radially inner annular wall segment comprising a first circumferential edge and an opposite second circumferential edge which each have a slit;
• and
• a tongue mounted in part in the slit of the first circumferential edge (612) of one radially inner annular wall segment (610) and in part in a circumferentially opposite slit of the second circumferential edge of a circumferentially adjacent radially inner annular wall segment.