The invention relates to a cooling system (10) for an aircraft turbojet, the cooling system comprising: - a first exchanger (12), called a hot source exchanger, between a coolant (C) and a lubricant (H) for a turbojet engine. , - a second heat exchanger (14), called the cold source heat exchanger, between the heat transfer fluid and the air (F), - an inlet pipe (18) for heat transfer fluid in the second cold source heat exchanger, and - a pipe heat transfer fluid outlet (20) from the second cold source exchanger, the inlet and outlet conduits forming a recirculation loop between the first hot source exchanger and the second cold source exchanger, the second cold source exchanger being movable relative to the first hot source exchanger and the heat transfer fluid inlet and outlet conduits being extendable and / or flexible to allow the relative movement between the two exchangers to be accommodated. Abstract figure: Fig. 2
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