Patent ID: 11939936
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  G  Y | IPC F

Claim 0:
1. A cascade type thrust reverser device for a turbomachine of an aircraft, the cascade type thrust reverser device comprising a thrust reverser cascade and a casing, the thrust reverser cascade extending in a first plane defining a first direction and a second direction and including first partitions positioned successively in the first direction and parallel to one another, second partitions intersecting said first partitions and each extending in planes parallel to one another and parallel to the first direction, and cavities each defined by two first partitions and two second partitions, the casing comprising an opening extending in a plane orthogonal to said first direction and a housing wherein the thrust reverser cascade can be inserted in said first direction via said opening, and the casing and said thrust reverser cascade being in relative translation with respect to one another in the first direction between a first position of the cascade type thrust reverser device in which the thrust reverser cascade is entirely positioned in the housing and a second position of the cascade type thrust reverser device in which said thrust reverser cascade is at least partially outside said housing,
wherein the casing comprises an acoustically reflecting wall, and a perforated wall intended to be in contact with an air flow and to be positioned between said air flow and the thrust reverser cascade when the cascade type thrust reverser device is in the first position, the perforated wall including a plurality of orifices and a plurality of wall strips with no orifices and intended to face the first partitions of the thrust reverser cascade when the cascade type thrust reverser device is in the first position, at least one orifice being positioned between two successive wall strips in the first direction and facing a cavity when the cascade type thrust reverser device is in the first position,
the thrust reverser cascade is positioned between the acoustically reflecting wall and the perforated wall when the cascade type thrust reverser device is in the first position, wherein the acoustically reflecting wall, the perforated wall and the thrust reverser cascade forming an acoustic panel with said cavities forming resonant cavities when the cascade type thrust reverser device is in the first position.