US 11,788,489 B2
Thrust reverser cascade including acoustic treatment
Norman Bruno André Jodet, Moissy-Cramayel (FR); and Jéremy Paul Francisco Gonzalez, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/608,265
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Apr. 3, 2020, PCT No. PCT/EP2020/059560
§ 371(c)(1), (2) Date Nov. 2, 2021,
PCT Pub. No. WO2020/224887, PCT Pub. Date Nov. 12, 2020.
Claims priority of application No. 1904654 (FR), filed on May 3, 2019.
Prior Publication US 2022/0325680 A1, Oct. 13, 2022
Int. Cl. F02K 1/72 (2006.01); F02C 7/24 (2006.01); F02K 1/34 (2006.01); F02K 1/82 (2006.01)
CPC F02K 1/72 (2013.01) [B64D 33/06 (2013.01); F02C 7/24 (2013.01); F02K 1/827 (2013.01); F05D 2240/129 (2013.01); F05D 2260/963 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A cascade for a thrust reversal device to be mounted on a turbomachine of an aircraft, the cascade comprising first partitions extending in a first direction, second fixed partitions extending in a second direction orthogonal to the first direction, and a frame inside which the first partitions and the second fixed partitions extend, the frame comprising at least two fixed walls extending according to the first direction, and at least one part of each first partition extending between two of the second fixed partitions in a plane comprising the first and second directions,
wherein at least one of said first partitions is mobile according to the second direction between a first position wherein said at least one of said first partitions is distant, in the second direction, from said fixed walls of the frame to form a plurality of resonating cavities with the first partitions and/or the fixed walls of the frame, and a second position wherein said at least one of said first partitions is in contact with one of said at least two fixed walls of the frame or another first partition of said first partitions.