Patent ID: 8430203

Claim:
A turbojet nacelle comprising: a nozzle on a downstream end thereof, the nozzle comprising an inner wall inside which a first flow from the turbojet circulates and an outer wall outside which a second flow corresponding to surrounding outside air circulates, and an aeroacoustic noise reduction device of the turbojet, comprising a plurality of chevrons arranged on a circumference of the nozzle, wherein the aeroacoustic noise reduction device also comprises a slide arranged on the circumference of the nozzle in such a way that it can rotate about an axis of the nozzle, each chevron being connected to the slide by means of a guiding element that can move along the slide during rotation of the slide in order to ensure displacement of the chevron, the rotation of the slide causing each chevron to rotate around an axis tangent to the circumference of the nozzle.