System for cooling a liquid for lubricating an aircraft turbomachine

A system for cooling a lubricating liquid of an aircraft turbomachine comprising:

• a heat exchanger comprising a first cooling volume for the lubricating liquid,
• a first circuit for cooling a two-phase heat transfer fluid by means of a thermo-capillary pumped two-phase fluid circulation loop, comprising:
• a first condenser comprising:
• 1. a vapour inlet for the heat transfer fluid in the vapour state,
• 2. channels extending along a first outer surface of a nacelle of the turbomachine to cool the channels, the channels being connected in parallel with one another, to enable the fluid circulating in the condenser to be cooled from a vapour state to a liquid state,
• 3. a liquid outlet for the heat transfer fluid in the liquid state,
• a first capillary evaporator of the heat exchanger, to absorb heat from the first volume in which the lubricating liquid circulates, the first evaporator comprising:
• 1. a first volume comprising a liquid inlet for the heat transfer fluid connected to the liquid outlet of the first condenser,
• 2. a second volume comprising a vapour outlet for the heat transfer fluid, connected to the vapour inlet of the first condenser
• 3. a capillary porous wick located between the first volume and the second volume, for separating the two-phase fluid between a liquid phase and a gas phase by a capillary pressure rise.