Ejection cone with an acoustic chamber for an aircraft turbine engine

An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis, the exhaust cone comprising:

• a radially internal annular wall;
• a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall;
• partitions mounted radially between the external skin and the internal annular wall and intersecting the external skin and the internal annular wall in a manner that together with the external skin and internal annular wall delimits acoustic chambers;
• and
• at least one seal arranged between a radial end of one of the partitions and at least one of the partitions constituting the internal annular wall or the external skin, wherein the at least one seal comprises at least one toric portion arranged at least in part against an upstream face of at least one of the partitions,
• wherein the at least one seal comprises an upstream toric portion and a downstream toric portion, wherein the upstream toric portion is arranged in contact with the upstream face of the partition and the downstream toric portion is arranged in contact with the downstream face of the partition, and
• wherein the upstream toric portion and the downstream toric portion are connected by a locking wire passing through holes provided in the partition.

An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis, the exhaust cone comprising:

• a radially internal annular wall;
• a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall;
• partitions mounted radially between the external skin and the internal annular wall and intersecting the external skin and the internal annular wall in a manner that together with the external skin and internal annular wall delimits acoustic chambers;
• and
• at least one seal arranged between a radial end of one of the partitions and at least one of the partitions constituting the internal annular wall or the external skin, wherein the at least one seal comprises at least one toric portion arranged at least in part against an upstream face of at least one of the partitions,
• wherein the at least one seal comprises an upstream toric portion and a downstream toric portion, wherein the upstream toric portion is arranged in contact with the upstream face of the partition and the downstream toric portion is arranged in contact with the downstream face of the partition, and
• wherein the at least one seal is arranged between the radially internal end of the partition and the internal wall, and wherein the upstream toric portion and the downstream toric portion of the at least one seal are connected by a connecting strip arranged under the radially internal end of the partition.