System for cooling an aircraft turbojet engine

A cooling system for a turbojet engine assembly for an aircraft, the turbojet engine assembly including a turbojet engine and a nacelle, the nacelle having an outer structure including an outer fairing defining an outer aerodynamic surface, and an inner fairing defining an inner aerodynamic surface, the cooling system comprising:

• a first heat-exchanger configured to transfer heat between a heat-transfer fluid and a lubricant of the turbojet engine;
• a second heat-exchanger configured to transfer heat between the heat-transfer fluid and air;
• and
• a first circulation pipe configured to circulate the heat-transfer fluid in closed circuit, the circulation pipe including a portion forming the second heat-exchanger and configured to be disposed in the nacelle in contact with the inner fairing of the nacelle, the outer fairing of the nacelle, or both the inner and outer fairings of the nacelle,
• wherein the cooling system comprises at least one regulation device for regulating heat extracted from the lubricant of the turbojet engine, the at least one regulation device being controlled by a control module configured to receive information according to different flight phases via a controller member of the turbojet engine,
• wherein the at least one regulation device for regulating heat extracted from the lubricant of the turbojet engine comprises a plurality of electrical devices for regulating a flow rate of the heat-transfer fluid, each electrical device of the plurality of electrical devices for regulating the flow rate of the heat-transfer fluid including an electric motor,
• wherein the electrical devices of the plurality of electrical devices for regulating the flow rate of the heat-transfer fluid are mounted in parallel in the circulation pipe, and
• wherein each electrical device of the plurality of electrical devices for regulating the flow rate of the heat-transfer fluid comprises an independent power module, controlled by the control module, the control module being dedicated to the plurality of electrical devices for regulating the flow rate of the heat-transfer fluid, the control module being controlled by the controller member of the turbojet engine.