Assembly for an exhaust cone of an aircraft turbomachine

An assembly of an exhaust cone of an aircraft turbomachine, comprising:

• a first annular wall centered on a longitudinal axis running axially from upstream to downstream, and
• first partitions and second partitions extending substantially perpendicularly from the first annular wall,
• wherein the first partitions extend generally in an 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 of the 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 and absorbing combustion gas noises from the aircraft turbomachine,
• wherein an arrangement formed by the first and the second partitions is fixed to the first annular wall with first fixing members arranged upstream relative to second fixing members and the second fixing members arranged downstream relative to the first fixing members, the first fixing members including all fixing members disposed at a same first axial location and the second fixing members including all fixing members disposed at a same second axial location, the first fixing members and the second fixing members forming mechanical point connections, and
• wherein each first fixing member of the first fixing members is offset circumferentially relative to each second fixing member of the second fixing members.