Abstract: An axial turbine engine for an aircraft, in particular a ducted fan turbine engine. The engine comprises an oil circuit with a cooler fitted with a first heat exchange surface in contact with oil of the oil circuit, and a second heat exchange surface in contact with a secondary air flow entering the turbine engine. The cooler is of the air/oil type (ACOC) and comprises fins. To increase the capacity of the cooler, the cooler is fitted with a device for injecting a cooling liquid, e.g., water with additives. The thermal capacity of the water amplifies the cooling. Evacuation of the water increases the thrust of the turbine engine. A method is also provided for cooling the turbine engine of an aircraft by injection of a cooling liquid at the time of take-off.

Abstract: An axial turbine engine for an aircraft, in particular a ducted fan turbine engine. The engine comprises an oil circuit with a cooler fitted with a first heat exchange surface in contact with oil of the oil circuit, and a second heat exchange surface in contact with a secondary air flow entering the turbine engine. The cooler is of the air/oil type (ACOC) and comprises fins. To increase the capacity of the cooler, the cooler is fitted with a device for injecting a cooling liquid, e.g., water with additives. The thermal capacity of the water amplifies the cooling. Evacuation of the water increases the thrust of the turbine engine. A method is also provided for cooling the turbine engine of an aircraft by injection of a cooling liquid at the time of take-off.