| 摘要 |
The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening means (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening means (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26). |
