FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft engine nacelle anti-icing system that comprises air intake 2 equipped with bead 3. Air intake tubular part 4 with acoustic isolation panel 5 is arranged behind said bead. Besides, proposed system comprises anti-icing appliances (6, 6a, 6b, 6c, 6d) made up of the grid of resistive heating elements immersed in electro-insulating material. Note here that said anti-icing appliances are made up of a layer comprising resistive elements arranged in depth of air intake bead. Proposed system forms a part of bead wall that overlaps bead part 3a external with respect to air intake.
EFFECT: reduced sizes, increased anti-icing zone.
26 cl, 17 dwg
