The invention relates to an air intake (3) for a nacelle (1) for an aircraft engine (6). The air intake (3) comprises a front lip (31) connecting a substantially cylindrical internal wall (32) and a substantially cylindrical external wall (33), the air intake comprises at least one acoustic structure (40) comprising acoustic cells (41), and the acoustic structure (40) is situated in the space (50) delimited by the internal wall (32), the external wall (33) and the front lip (31). The air intake (3) is characterized in that the acoustic structure (40) is an added part secured to the air intake (3) by securing means (60), and the acoustic cells of the acoustic structure (40) is arranged facing a region of the internal wall (32) and/or of the lip (31) at a predetermined distance (d) that is configured in order that the acoustic cells (41) of the acoustic structure (40) are not in contact with the internal wall (32) and/or the lip (31) while ensuring an acoustic attenuation function.
本发明涉及一种用于飞行器发动机(6)的短舱(1)的进气道(3),所述进气道(3)包括连接大致圆柱形内壁(32)和大致圆柱形外壁(33)的前唇(31),所述进气道包括至少一个包括声学单元(41)的声学结构(40),所述声学结构(40)位于由所述内壁(32)、所述外壁(33)和所述前唇(31)界定的空间(50)中,所述进气道(3)的特征在于,所述声学结构(40)是通过固定装置(60)固定到所述进气道(3)的附加部件,所述声学结构(40)的声学单元以预定距离(d)面向所述内壁(32)和/或所述唇(31)的区域布置,所述预定距离(d)被配置成使得所述声学结构(40)的声学单元(41)在确保声学衰减功能的同时不与所述内壁(32)和/或所述唇(31)接触。
NACELLE AIR INTAKE AND NACELLE COMPRISING SUCH AIR INTAKE
短舱进气道和包括这种进气道的短舱
2021-12-17
Patent
Electronic Resource
Chinese
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