| 摘要 |
The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterised in that it comprises a duct (12) for circulating a flow of cold air (F1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F1), located in the duct (12), downstream from the injection means (16). |
