AIR INFLOW LIP FOR TURBOJET NACELLE

The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic treatment device; and a pneumatic de-icing device comprising a de-icing fluid supply device. The invention is characterised in that the inner wall (23) of the lip comprises a plurality of acoustic boreholes (28) and in that the pneumatic de-icing device comprises a honeycombed de-icing plate (27) mounted inside said cavity on said inner wall (23) of the lip andcomprising a plurality of conduits (35) for the circulation of a de-icing fluid and a plurality of acoustic wells communicating with said acoustic boreholes (28). 本发明涉及一种用于飞行器的涡轮喷气发动机的机舱的进气唇缘，包括由机舱的前缘和环形壁限定的空腔，所述进气唇缘包括：内壁(23)；声学处理装置；以及包括除冰流体供应装置的气动除冰装置。本发明的特征在于，唇缘的内壁(23)包括多个声学孔(28)，并且在于气动除冰装置包括蜂窝状除冰板(27)，该除冰板安装在唇缘的所述内壁(23)上的所述空腔内，并且包括用于除冰流体的循环的多个管道(35)和与所述声学钻孔(28)连通的多个声学井。