公开(公告)号：US12116931B2

公开(公告)日：2024-10-15

申请号：US17510785

申请日：2021-10-26

Applicant: Safran Nacelles

Inventor： Denis Guillois ,  Fabienne Quenu ,  Anne Mounier ,  Franck Philippe Gérald Zaganelli

IPC: F02C7/045

CPC classification number: F02C7/045 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2230/60

Abstract: An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.