AIR INLET OF AN AIRCRAFT NACELLE INCLUDING OPTIMIZED FROST TREATMENT

摘要

The invention relates to an air inlet of an aircraft nacelle including a pipe, extending over the circumference of said air inlet and defined in the back by a front frame, and a means for the localized injection of hot air into said pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. Said inlet is characterized in that it includes at least one vortex generator (38) in the pipe (22), said generator being plate-shaped or shaped in a manner projecting from the wall of the pipe (22), in order to disrupt the hot air flow so as to compensate the effect of the centrifugal force and reduce the temperature gradient between the inside and outside of said pipe (22).