FIELD: engine building.
SUBSTANCE: invention relates to high-temperature turbines of gas turbine engines, namely, to methods for cooling the buckets of turbines of gas turbine engines for various purposes. The air intended for cooling the buckets 10 in the impeller of the turbine 2 is collected from the air path 18 behind the rotor of the compressor 1 through inputs 17 in the blades 12 of the rectifying apparatus 6 and supplied into the air channels 14 of the heat exchange modules 11 located in the blades 12 of the rectifying apparatus 6 of the compressor, and through the outputs 19 into the twisting apparatus 8. Fuel from the fuel collector 5 is supplied to the fuel channels 13 of the heat exchange modules 11 located in the blades 12 of the rectifying apparatus 6 of the compressor through the inputs 15, and to the fuel injectors 7 of the combustion chamber 4 installed in the body 3 through the outputs 16. The air cooled in the heat exchange modules 11 is supplied to the internal cavities of the buckets 10 of the turbine from the twisting apparatus 8 through channels 9 in the impeller 2.
EFFECT: increase in the efficiency of the gas turbine engine is achieved by maintaining high efficiency of the thermodynamic cycle thereof.
2 cl, 3 dwg
