FIELD: aviation equipment.
SUBSTANCE: invention relates to the aviation equipment, namely to the aircraft turbojet engine with the high-pressure turbines cooling system. Technical result is achieved by the fact that the aircraft turbojet engine contains housed in the body nacelle the first high-pressure turbine 3, second high pressure turbine 4 and compressors, one of which 2 via the outer shaft 10 is connected to the first high pressure turbine 3, other compressor 5 via the middle shaft 11 is connected to the second high pressure turbine 4, the third compressor 7 via the inner shaft 20 is connected to the low pressure turbine 8. Turbojet engine comprises the high pressure turbines 3 and 4 cooling system including internal evaporators 16, located inside the high pressure turbines 3 and 4, located inside the non-freezing liquid tank external evaporator 17, condenser 15 and mounted on the inner shaft 20 cooling system compressor 21, at that the outer shaft 10, middle shaft 11 and the inner shaft 20 are located coaxially, the electric starter-converter armature and the alternator rotor are located on the outer shaft, alternator stator is rigidly mounted in the body nacelle, and the condenser, the external evaporator and the non-freezing liquid tank are located inside the made outside the body nacelle air duct.
EFFECT: technical result, to which the claimed invention is aimed, is increase in the high-pressure turbines cooling efficiency, which contributes to increase in the turbojet engine power.
1 cl, 7 dwg
