FIELD: engines and pumps.
SUBSTANCE: gas turbine engine includes at least one cooled stage of a turbine with a nozzle assembly with cavities above it and below it, turbine rotor cooling and stator blowing systems, a turbine housing and a radial gap adjustment system. The turbine housing consists of an external housing and an internal cover with at least one annular insert installed between them. Rotor cooling and stator blowing systems of each turbine stage are independent, contain air intake main lines and flow meters, but all cooling air intake main lines are connected to a cavity behind the compressor. Electrical air heaters are installed in stator blowing systems. The gas turbine engine can contain an onboard computer and sensors for measurement of a radial gap above each impeller of all the cooled turbine stages. Each annular insert can be hollow or filled with a heat accumulating substance.
EFFECT: achieving effective control of radial gaps in a turbine in all modes; increasing engine thrust in takeoff and boost modes; improving efficiency and reliability of a turbine.
4 cl, 6 dwg
