Assembly for an ejection cone of an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-12429015-B2
Application number	US-202218714334-A
Country	US
Kind code	B2
Filing date	Dec 2, 2022
Priority date	Dec 3, 2021
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

First claim

The invention claimed is:

1. 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.

2. The set according to claim 1 , wherein the arched portions of the second partitions of at least one of the circumferential rows define a pattern repeating along said circumferential row and wherein the pattern of the arched portions of the second partitions of said circumferential row consists of a portion arched upstream or downstream, such that all the arched portions of the second partitions of said circumferential row are oriented in a same axial direction, upstream or downstream.

3. The set according to claim 1 , wherein the arched portions of the second partitions of at least one of the circumferential rows define a pattern repeating along said circumferential row and wherein the pattern of the arched portions of the second partitions of said circumferential row consists of a portion arched upstream followed by a portion arched downstream, so as to obtain an alternation of a portion arched upstream and a portion arched downstream all along said circumferential row.

4. The set according to claim 1 , wherein the arched portions of the second partitions of at least one of the circumferential rows define a pattern repeating along said circumferential row and wherein the pattern of the arched portions of the second partitions of said circumferential row consists of two portions arched upstream followed by two portions arched downstream, so as to obtain an alternation of two portions arched upstream and two portions arched downstream all along said circumferential row.

5. The set according to claim 1 , wherein, along at least one of the circumferential rows, two or more successive arched portions are interposed between each pair of adjacent first partitions.

6. The set according to claim 1 , wherein each second partition of at least one of the circumferential rows carries a single arched portion.

7. The set according to claim 1 , wherein each second partition of at least one of the circumferential rows carries a portion arched upstream and a portion arched downstream.

8. An ejection cone for an aircraft turbomachine comprising the set according to claim 1 .

9. An aircraft turbomachine, comprising the ejection cone according to claim 8 .

Assignees

• Safran Nacelles

Inventors

• Miossec Tony
• Bravin Fabien
• Devanlay Vincent
• Versaevel Marc
• Simeon Valentin

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title

• F02K1/82

  Jet pipe walls, e.g. liners · CPC title

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F02K1/40

  Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet · CPC title