Patent ID: 11927133
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  G  D | IPC B  D  F  G

Claim 16:
17. An aircraft turbine engine comprising:
a wall; and
an acoustic attenuation edge installed on the wall and in contact with fluid flow, including:
a porous coating (39) with a mesh structure,
an acoustically absorbent material (41) covered with the porous coating and having a first volume (Vabs), and
at least one cavity (45) located between the acoustically absorbent material (41) and the porous coating (39),

wherein the mesh structure has wires (390) separating between them mesh openings (391) passing through said mesh structure,
and wherein:
each of the mesh openings (391) has an elementary surface area (So), some of the mesh openings (391) are large enough to include a circle 0.05 mm in diameter, and
said at least one cavity (45) has a second volume (Vcav), the second volume is higher than three percent of a sum of the first volume and the second volume (Vcav>3% (Vcav+Vabs)),
the fluid flow is to pass through the acoustic attenuation edge while propagating in a main propagation direction (43), the acoustic attenuation edge has a stop point (47) at which the fluid flow encounters the porous coating (39) and at which the main propagation direction (43) of said flow is normal to a front face of said porous coating (39) receiving said flow,
the mesh openings are smaller near the stop point (47) than further away from said stop point.