Ejection cone with an acoustic chamber for an aircraft turbine engine

Inventors: Tony Miossec (Moissy-Cramayel, FR); Fabien Bravin (Moissy-Cramayel, FR); Christophe Jean François Thorel (Moissy-Cramayel, FR); Marc Versaevel (Moissy-Cramayel, FR); Valentin Simeon (Moissy-Cramayel, FR)

Assignee: SAFRAN NACELLES

F02K1/04 F02C7/28

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Quick Facts

Patent No.: US 12662977
App. No.: 18/843,154
Granted: Jun 23, 2026
Kind: B2

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Abstract

An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Claims (28)

1 . 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.

2 . The exhaust cone according to claim 1 , wherein the at least one seal comprises the at least one toric portion connected to an attachment strip, wherein the attachment strip is fixed to a downstream face of the partition and the at least one toric portion is arranged at least in part against an upstream face of the at least one of the partitions.

3 . The exhaust cone according to claim 1 , 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.

4 . The exhaust cone according to claim 3 , wherein the upstream toric portion and the downstream toric portion are connected by a locking wire passing through holes provided in the partition.

5 . The exhaust cone according to claim 3 , 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.

6 . The exhaust cone according to claim 1 , wherein the at least one seal comprises an upstream toric portion and a downstream toric portion, and wherein the at least one toric portion of the at least one seal is made by the weaving or braiding of ceramic or metal fibers or wherein the upstream and downstream toric portions of the at least one seal are made by the weaving or braiding of ceramic or metal fibers.

7 . The exhaust cone according to claim 1 , wherein the at least one seal comprises an attachment strip fixed to the upstream face of the partition and a curved portion comprising a convex surface bearing against the internal wall.

8 . The exhaust cone according to claim 2 , wherein the attachment strip is fixed to the partition by a locking wire passing through holes provided in the partition and the attachment strip.

9 . The exhaust cone according to claim 1 , wherein the acoustic chambers are formed by longitudinal partitions and circumferential partitions, wherein at least one of the acoustic chambers is equipped with a seal of which a portion extends along a lateral face of one of the longitudinal partitions defining the acoustic chamber and along an upstream face of the downstream circumferential partition defining the acoustic chamber.

10 . A turbomachine for an aircraft comprising an exhaust cone according to claim 1 .

11 . 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;

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.

12 . 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;

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.