FIELD: machine building.
SUBSTANCE: invention relates to high-temperature turbines of gas turbine engines, namely to methods and systems of cooling of turbine blades of aircraft engines. Disclosed is a method of cooling and controlling radial clearances of turbine of double-flow gas turbine engine, including control of radial clearances, extraction of cooling air (CE) from air cavity (11) of combustion chamber (12), its transportation through inlet cavity (22) into swirling unit (23), further supply of CE into internal cavities (27) of working blades (28) and control of flow rate CE. CE temperature is reduced in air-to-air heat exchanger (6) installed in second circuit (7). Inlet cavity (22) is divided into several identical sectors (39), to each of which several supply pipelines (5) with shutoff valves (3) are connected. Air pressure at the inlet of inner cavities (27) of working blades (28) is increased in centrifugal compressor (30) made between impeller (26) of the turbine and deflector (29).
EFFECT: technical result is improvement of cooling of turbine working blades of double-flow gas turbine engine in the whole range of operation.
8 cl, 14 dwg
