FIELD: machine building.
SUBSTANCE: group of inventions relates to high-temperature turbines of gas turbine engines, namely to methods and systems for controlling radial clearances of turbines of aircraft engines. Method of control of radial clearances of turbine of double-flow gas turbine engine includes control of radial clearances, selection of cooling air from air cavity of combustion chamber, its transportation through inlet cavity into spinning device. Further, cooling air is supplied between turbine disk and deflector into inner cavities of working blades through air channels in turbine wheel. Cooling air flow is regulated depending on its operation mode and radial clearance value. Cooling air temperature is reduced in air-to-air heat exchanger installed in the second circuit. Inlet cavity is divided into several identical sectors, to each of which there connected are several supply pipelines with cutoff valves. Air pressure at the inner cavities of the working blades is increased in a centrifugal compressor made between the turbine disc and the deflector. Additional control of the cooling air supply temperature is performed by changing the efficiency of the air-to-air heat exchanger operation by the heat exchange control device.
EFFECT: group of inventions is aimed at increasing economy of gas turbine engines with high-temperature turbines due to optimization of radial clearances and flow rate of cooling air in working blades of high-pressure turbines in the entire range of operation of the multi-mode engine while maintaining a satisfactory temperature state of the cooled blades, that is while maintaining reliability and service life of the engine.
8 cl, 14 dwg
