An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.
ENTRÉE D'AIR DE NACELLE À PANNEAU ACOUSTIQUE
NACELLE AIR INTAKE WITH ACOUSTIC PANEL
LUFTEINLASS EINER GONDEL MIT AKUSTIKPLATTE
2023-11-01
Patent
Electronic Resource
French
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