FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, namely, to aircraft bypass turbojet engine two high pressure turbines cooling system. Bypass turbojet engine two high pressure turbines cooling system comprises turbine housing, first high-pressure turbine with blades and second high pressure turbine. First high pressure turbine is located on outer shaft, on which second stage compressor turbines are also arranged. Second high pressure turbine is located on inner shaft, on which first stage compressor turbines are also arranged and low pressure turbines. Inside high pressure turbines internal evaporators are arranged. System comprises condenser, located outside of aircraft fuselage, which is connected with compressor and internal and external evaporators using capillary tubes. Compressor by means of reduction gear and gearing is connected to first high pressure turbine, wherein external evaporators are located inside tank with anti-freezing grease.
EFFECT: enabling increasing cooling efficiency of jet turbine engine.
1 cl, 5 dwg
