FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, namely, to turbojet aircraft nacelle. Air intake comprises outer wall 7 including leading edge 9 and is arranged to displace relative to said medium element from rear position to front position and back, baffle 11 confining anti-icing compartment 13 in said leading edge 9, anti-icing manifold 15 extending through said compartment 13 and air duct 17 to feed hot air in manifold 15. Said baffle 11 is tightly secured inside leading edge 9 while said air duct 17 is coupled with manifold by detachable seals 27, 29, 31, 35.
EFFECT: higher tightness of air intake walls.
12 cl, 14 dwg
