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 together with "hot" air between turbine disk and deflector into inner cavities of working blades through air channels in turbine wheel and control of flow rate of both "cold" and "hot" air, characterized in that the inlet cavity is divided into two cavities, the swirling unit, respectively, into two parts, each of which is connected to several supply pipelines with cutoff valves, air pressure at the working blades inner cavities is increased in the centrifugal compressor made between the turbine disk and the deflector, and control of supply and "cold" and "hot" air modes is discrete. Technical result is achieved in a device for cooling a working blade of a turbine of a double-flow gas turbine engine, comprising an air-to-air heat exchanger installed in an air path of the second circuit, an inlet cavity into a spinning device, cold air supply system together with hot air between turbine disk and deflector into inner cavities of working blades through air channels in turbine wheel and system to control flow rate of both cold and hot air, characterized in that the inlet cavity is divided into two cavities, the swirling device – into two parts, respectively, to the input of each of which there connected are several supply pipelines with shutoff valves, and to the outlet – centrifugal compressor located between the turbine disk and the deflector.
EFFECT: higher efficiency of gas turbine engines with high-temperature turbines.
6 cl, 14 dwg
