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 17:
18. The aircraft turbine engine of claim 17, further comprising at least one of:
(a) the mesh structure forms a porous membrane;
(b) the wires (390) have a wire width extending between two adjacent mesh openings (391), at least 50% of the wire widths (Sf) are lower than 0.13 mm;
(c) said elementary surface areas (S0) are lower than 0.01 mm2;
(d) each of the mesh openings (391) define a rectangle having an opening length (L1) and an opening width (L2), the opening length (L1) and the opening width (L2) are lower than 0.1 mm;
(e) more than 50% of the elementary surface areas (S0) are higher than 0.0025 mm2;
(f) as the opening lengths (L1) are higher than 0.05 mm and the opening widths (L2) are higher than 0.05 mm;
(g) the mesh structure:
is curved to a rounded apex, in a direction (51) of curvature,
has said wires (390) oriented in different directions in order to display said mesh openings (391) between them, and
displays, between two of said wires crossways to said direction of curvature:
a dimension Lx which is as a function of an angle ∝ formed between a tangent to the porous membrane, for a given section, and
an axis (55) passing through said rounded apex and through a median to the acoustically absorbent material (41) and Lx<0.1/sin(∝).