Patent ID: 8887489

Claim:
A chevron ( 20 . 1 , 20 . 2 , 20 . 3 ) which is positioned at the periphery of an outlet orifice ( 5 , 11 ) for the jet ( 7 , 9 ) from a turbojet engine nozzle ( 4 , 10 ) for the purposes of attenuating the noise of said jet and the shape of which is delimited: by two at least approximately rectilinear lateral sides ( 21 , 22 ) of which front ends ( 21 A, 22 A) are secured to said nozzle ( 4 , 10 ) and which, with increasing distance therefrom, converge toward one another without meeting so that rear ends ( 21 R, 22 R) of said lateral sides ( 21 , 22 ) are separated from one another; and by a transverse line ( 23 . 1 , 23 . 2 , 23 . 3 ) which connects the rear ends ( 21 R, 22 R) of said lateral sides ( 21 , 22 ) thereby forming two lateral protrusions ( 24 . 1 , 25 . 1 - 24 . 2 , 25 . 2 - 24 . 3 , 25 . 3 ) separated by an intermediate recess ( 26 . 1 , 26 . 2 , 26 . 3 ), wherein said transverse line ( 23 . 1 , 23 . 2 , 23 . 3 ) is curvilinear in such a way that said lateral protrusions ( 24 . 1 , 25 . 1 - 24 . 2 , 25 . 2 - 24 . 3 , 25 . 3 ) and said intermediate recess ( 26 . 1 , 26 . 2 , 26 . 3 ) are rounded, wherein the lateral sides ( 21 , 22 ) of said chevrons are inclined symmetrically to one another with respect to a median longitudinal axis the overall direction of which is that of said jet ( 7 , 9 ), wherein said rounded lateral protrusions ( 24 . 2 , 25 . 2 ; 24 . 3 , 25 . 3 ) are offset from one another along said median longitudinal axis of said chevron ( 20 . 2 , 20 . 3 ), wherein no portion of the transverse line extends from the two lateral protrusions toward the nozzle as far as do the rectilinear lateral sides, and wherein the transverse line and the intermediate recess are asymmetrical about the median longitudinal axis.