Patent ID: 8783619

Claim:
An air intake of an aircraft nacelle, comprising: a pipe that extends over the circumference of said air intake and that is bordered to the rear by a front frame ( 20 ); and means ( 24 ) for localized injection of hot air in said pipe ( 22 ) that provides circulation of hot air in the pipe along a circumference of the nacelle in one direction, wherein, in the pipe ( 22 ), there is provided a vortex generator ( 38 ) that disrupts a flow of hot air that flows along the length of the pipe so as to compensate for an action of centrifugal force and reduce a temperature gradient between an inner side and an outer side of said pipe ( 22 ), the vortex generator ( 38 ) comprising a surface, said surface having a first side in connection with and running along a surface of the pipe, and a second side defined by a first end connected to an upstream end of the first side and a second end distanced from the surface of the pipe and positioned downstream from the first end.