US 11,719,192 B2
Acoustic attenuation panel for an aircraft jet engine nacelle
Loïc Hervé André Le Boulicaut, Gonfreville l'Orcher (FR); Christophe Thorel, Gonfreville l'Orcher (FR); Simon Verger, Gonfreville l'Orcher (FR); and Mathieu Preau, Gonfreville l'Orcher (FR)
Assigned to Safran Nacelles, Gonfreville l'Orcher (FR)
Filed by Safran Nacelles, Gonfreville l'Orcher (FR)
Filed on Nov. 24, 2020, as Appl. No. 17/103,424.
Application 17/103,424 is a continuation of application No. PCT/FR2019/051205, filed on May 24, 2019.
Claims priority of application No. 18/54404 (FR), filed on May 24, 2018.
Prior Publication US 2021/0102513 A1, Apr. 8, 2021
Int. Cl. F02K 1/82 (2006.01); B64C 7/02 (2006.01); F02K 1/34 (2006.01); F02C 7/24 (2006.01)
CPC F02K 1/827 (2013.01) [B64C 7/02 (2013.01); B64D 33/06 (2013.01); F02C 7/24 (2013.01); F05D 2260/963 (2013.01)] 11 Claims
OG exemplary drawing
 
1. An acoustic attenuation panel for an aircraft turbojet engine nacelle, the acoustic attenuation panel including 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,
wherein:
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 front and rear structures each comprising a peripheral border, said border of the front and rear structures being fastened to each other for assembly of the front and rear structures, 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 first and second networks of alveolar walls are spaced from the front and rear skins by a clearance d.