FIELD: aviation.
SUBSTANCE: invention relates to aeronautical engineering, in particular, to a cooling system for bearings of turbines of a gas turbine engine of an aircraft. Technical result is achieved by the fact that the cooling system of bearings of turbines of a gas turbine engine contains evaporators located in body chambers on both sides of the bearings, connected in parallel with the evaporators located inside the high-pressure turbines. Evaporators are connected to a condenser placed in front of the low-pressure turbines and to a compressor installed on a rotating axis. Bearings are housed in housings, each with a temperature sensor attached to one side, and on the other hand, a strain gauge communicated with a conversion and computing unit connected to an on-board computer communicated with a power unit, giving the command to an electropneumatic valve to operate evaporators located in body chambers.
EFFECT: technical result of the proposed cooling system is to ensure the operation of the gas turbine engine at higher revolutions of the turbines, which makes it possible to increase the power of the gas turbine engine.
1 cl, 5 dwg
