The invention relates to a turbine engine such as a turbojet engine or a turboprop engine of an aircraft, comprising at least one oil circuit (8) and means (16) for cooling the oil of said circuit (8), the cooling means (16) comprising a refrigerant circuit (17) provided with a first heat exchanger (18) capable of exchanging heat between the refrigerant and the air and forming a condenser, a second heat exchanger (19) capable of exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander (20), a compressor (21) and first control means (31) capable of controlling the pressure of the refrigerant entering the first exchanger (18).
