FIELD: turbines or turbomachines.
SUBSTANCE: group of inventions relates to high-temperature turbines of gas turbine engines, namely, to methods and systems of cooling of turbine blades of aircraft engines. Technical result is achieved in cooling method of turbine working blades of double-flow gas turbine engine, which includes extraction of cooling air from air cavity of combustion chamber, its transportation through an air-to-air heat exchanger installed in the air path of the second circuit, and through the inlet cavity into the spinning device, further supply of "cold" air between turbine disk and deflector into inner cavities of working blades through air channels in turbine wheel and control of "cold" air flow rate, by the fact that the inlet cavity is divided into several identical sectors, to each of which several supply pipelines with cutoff valves are connected, air pressure at the inlet of the inner cavities of the working blades is increased in the centrifugal compressor made between the turbine disk and the deflector, and the cold air supply control is performed discretely by closing the shutoff valves. Technical result is achieved in device for cooling of turbine working blade of double-flow gas turbine engine containing air-to-air heat exchanger installed in air circuit of the second circuit, inlet cavity into spinning device, cold air supply system between turbine disk and deflector into inner cavities of working blades through air channels in turbine wheel and cold air flow rate control system, according to invention input cavity is divided into several identical sectors, to input in each of which there connected are one supply pipeline with shut-off valves, and to outlet – centrifugal compressor arranged between turbine disk and deflector.
EFFECT: higher efficiency of gas turbine engines with high-temperature turbines.
4 cl, 13 dwg
