System for cooling an aircraft turbojet engine

A nacelle for a turbojet engine, the nacelle comprising:

• an outer structure and an inner structure defining an annular flow path configured to direct a secondary air stream, the outer structure comprising an outer fairing defining an outer aerodynamic surface and an inner fairing defining an inner aerodynamic surface, the outer fairing and the inner fairing being connected upstream by a leading edge wall forming an air inlet lip;
• a thrust reverser;
• and
• a cooling system comprising:
• a first heat-exchanger configured to exchange heat between a heat-transfer fluid and a lubricant of the turbojet engine;
• a second heat-exchanger configured to exchange heat between the heat-transfer fluid and air;
• a heat-transfer fluid inlet conduit configured to permit the heat-transfer fluid to flow into the second heat-exchanger;
• and
• a heat-transfer fluid outlet conduit configured to permit the heat-transfer fluid to flow out of the second heat-exchanger,
• wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are configured to form a recirculation loop between the second heat-exchanger and the first heat-exchanger,
• wherein the second heat-exchanger is movable relative to the first heat-exchanger and is disposed in the thrust reverser, and the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are extendable, flexible, or extendable and flexible to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.