FIELD: chemistry.
SUBSTANCE: invention relates to high-temperature turbines of gas turbine engines, namely, to methods and systems for regulation of radial clearances of turbines of aircraft engines. Disclosed is a method of cooling and controlling radial clearances of a turbine of a double-flow gas turbine engine, comprising controlling radial clearances, extracting cooling air (CA) from combustion chamber (12) air cavity (11), its transportation through nozzle blades (21) into inlet cavity (22) and further into swirling unit (23), further supply of CA into internal cavities (27) of working blades (28) and control of flow rate CA. CA temperature is reduced in air-to-air heat exchanger (6) installed in second circuit (7). Inlet cavity (22) is divided into several identical sectors (52), to each of which several supply pipelines (5) with shutoff valves (3) are connected. Pipelines (5) of CA feed are fed through middle nozzle blades (21) of blocks (36), which consist of three nozzle blades and are divided into two cavities: front (40) and rear (41) cavities.
EFFECT: improved control of radial clearances of turbine of double-flow gas turbine engine in the whole range of operation.
8 cl, 19 dwg
