FIELD: machine building.
SUBSTANCE: invention relates to turbine engine, such as jet turbine engine or turbo-jet engine of aircraft. Turbine engine includes at least one oil circuit (8) and cooling means (16) for oil cooling in said circuit (8), wherein cooling means (16) comprise coolant circuit (17), in which first heat exchanger (18) is made, enabling heat exchange between coolant and air and forming a capacitor, a second heat exchanger (19), providing the possibility of heat exchange between the coolant and oil in the oil circuit and forming an evaporator, pressure reducer (20), compressor (21) and first control means (31) configured to control the coolant pressure coming into first heat exchanger (18). Also disclosed is cooling system (16) for cooling fluid in a circuit of hot fluid medium of aircraft turbine engine (1) containing coolant circuit (17).
EFFECT: invention allows improving turbine engine efficiency.
12 cl, 5 dwg
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