公开(公告)号：US20210102513A1

公开(公告)日：2021-04-08

申请号：US17103424

申请日：2020-11-24

Applicant: Safran Nacelles

Inventor： Loïc Hervé André LE BOULICAUT ,  Christophe THOREL ,  Simon VERGER ,  Mathieu PREAU

IPC: F02K1/82 ,  B64C7/02 ,  F02K1/34 ,  F02C7/24

Abstract: The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.