Assembly for an ejection cone of an aircraft turbomachine

A set for an ejection cone of an aircraft turbomachine, comprising:

• a first annular wall centered on a longitudinal axis of axial direction oriented from upstream to downstream, and
• a plurality of first partitions and second partitions extending substantially perpendicularly from the first annular wall,
• wherein the first partitions extend generally in the axial direction and are distributed circumferentially around the first annular wall,
• wherein the second partitions extend generally in a circumferential direction between pairs of adjacent first partitions and are distributed circumferentially around the first annular wall in at least one circumferential row,
• wherein the first annular wall, the first partitions and the second partitions define therebetween a plurality of acoustic enclosures distributed around the first annular wall,
• wherein the second partitions are bent walls comprising at least one portion arched in the axial direction upstream or downstream,
• wherein an assembly formed by the first and second partitions is attached to the first annular wall with first attachment members arranged upstream and second attachment members arranged downstream, and
• wherein the first attachment members are offset circumferentially relative to the second attachment members.