Patent ID: 8167232

Claim:
An aircraft nacelle comprising: a pipe ( 22 , 36 ) into which a gas stream flows, whereby said pipe ( 22 , 36 ) is delimited by two approximately concentric inside walls ( 40 ) and outside walls ( 42 ), covered at least partially by a coating whose purpose is to absorb a portion of sound energy, wherein at least one partition ( 38 , 38 ′) extends over at least one portion of a length of the pipe ( 22 , 36 ) between said inside and outside walls ( 40 , 42 ) and a profile of each of two walls ( 44 , 46 ) of said at least one partition ( 38 , 38 ′) comprises a convex portion, and on each side of said convex portion a concave portion oriented towards the inside wall of the pipe and a concave portion oriented towards the outside wall of the pipe to increase the number of reflections of an acoustic beam on the coating to absorb a portion of the sound energy.