The invention relates to an air intake lip of an aircraft turbomachine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall so as to delimit an annular cavity, the lip comprising an annular acoustic device mounted in the annular cavity. The lip has a first module, comprising the outer wall, the wall and a front wall forming an upstream portion of the inner wall, and a second module, comprising the acoustic device and a front skin forming a downstream portion of the inner wall, the first module and the second module being secured together so that the front wall and the front skin together form the inner wall of the lip.
LÈVRE D'ENTRÉE D'AIR DE NACELLE DE TURBOMACHINE COMPRENANT UN DISPOSITIF ACOUSTIQUE ET PROCÉDÉ DE FABRICATION D'UNE TELLE LÈVRE
AIR INTAKE LIP FOR A TURBOMACHINE NACELLE, COMPRISING AN ACOUSTIC DEVICE, AND METHOD FOR PRODUCING SUCH A LIP
LUFTEINLASSLIPPE FÜR EINE TURBOMASCHINENGONDEL MIT AKUSTISCHER VORRICHTUNG UND VERFAHREN ZUR HERSTELLUNG EINER SOLCHEN LIPPE
2022-04-06
Patent
Elektronische Ressource
Französisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Europäisches Patentamt | 2022
|Europäisches Patentamt | 2020
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