Aircraft turbine engine comprising a heat exchange system

An aircraft turbine engine, the turbine engine having a longitudinal axis and comprising:

• a gas generator extending along the axis and comprising at least one compressor, an annular combustion chamber, and at least one turbine,
• a main oil circuit for cooling mechanical equipment of the turbine engine or the gas generator,
• a secondary oil circuit for cooling electronic equipment of the turbine engine or gas generator,
• a flow duct for a gas flow which flows in the turbine engine and/or the gas generator, this duct being defined by two annular walls, external and internal respectively, which extend around each other and around the axis, and
• a heat exchange system located in said duct to be swept by at least part of said gas flow this heat exchange system comprising a first cooling circuit connected to the secondary oil circuit and a second cooling circuit connected to the main oil circuit,
• wherein the heat exchange system comprises first and second annular heat exchange devices, which are independent and arranged axially one behind the other in the duct. the first heat exchange device comprising said first cooling circuit which is dedicated to cooling the secondary oil circuit, and the second heat exchange device comprising said second cooling circuit which is dedicated to cooling the main oil circuit, the first heat exchange device being located upstream of the second heat exchange device with respect to the direction of flow of the gas flow in the duct.