ASSEMBLY FOR AN EJECTION CONE OF AN AIRCRAFT TURBOMACHINE

The invention relates to an assembly (10) for an ejection cone of an aircraft turbomachine, comprising a first annular wall (11) and a plurality of first partitions (12) and of second partitions (13) extending substantially perpendicularly from the first wall (11), the first partitions (12) addition...

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Bibliographische Detailangaben
Hauptverfasser:	SIMEON, Valentin, BRAVIN, Fabien, DEVANLAY, Vincent, MIOSSEC, Tony, VERSAEVEL, Marc
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to an assembly (10) for an ejection cone of an aircraft turbomachine, comprising a first annular wall (11) and a plurality of first partitions (12) and of second partitions (13) extending substantially perpendicularly from the first wall (11), the first partitions (12) additionally extending wholly in the axial direction and the second partitions (13) extending wholly in a circumferential direction between the adjacent pairs of first partitions (12) and being curved partitions comprising at least one arcuate portion (25a, 25b) in the axial direction upstream or downstream, the first wall (11), the first partitions (12) and the second partitions (13) additionally defining between them a plurality of acoustic boxes (21) distributed around the first wall (11).