FIELD: aeronautical engineering. SUBSTANCE: anti-icing system of the engine nacelle leading-edge of an aircraft double-flow turbojet engine has thermal chamber 1 formed by the contours of the outer (2) and inner (3) skins. Thermal chamber 1 is provided with pipe union 4 at the inlet and pipe union 5 - at the outlet. Pipe union 4 through piping 6 is connected to the pressure line of hydraulic lines 7, and pipe union 5 through piping 8 is connected to the suction line of hydraulic lines 7 of the engine hydraulic cooling system. EFFECT: enhanced economical efficiency at simultaneous decrease of weight. 2 dwg
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