Air inlet of an aircraft turbojet nacelle with ventilation openings for a hot defrost air flow

摘要

An air inlet of an aircraft turbojet nacelle extending along an axis X in which circulates an air flow from upstream to downstream, the air inlet extending circumferentially around of the X axis and having an inner wall (21) facing towards the X axis to guide an inner air flow INT and an outer wall (22), which is opposite the inner wall (21), to guide a exterior air flow EXT, the walls (21, 22) being connected by a leading edge (23) and an internal partition (25) so as to define an annular cavity (24), the air inlet comprising means for injecting at least one hot air stream FAC into the interior cavity (24) and at least one ventilation opening (3) formed in the exterior wall (22) to allow the exhaust of the stream of hot air FAC after heating the interior cavity (24), the air inlet comprising at least one element (4) for disturbing the flow of exterior air EXT, positioned upstream of the ventilation opening lation (3), which projects outwardly from the outer wall (22). Abstract figure: Figure 5