FIELD: engines and pumps.
SUBSTANCE: gas-turbine engine includes at least one cooled turbine stage with a nozzle diaphragm with blades above it and under it, turbine rotor and stator cooling systems, a turbine housing and a radial clearance control system. The turbine housing consists of an external housing and an internal cover with at least one annular insert installed between them. Rotor and stator cooling systems of each turbine stage are independent and contain cooling air extraction lines and flow rate controls, but all the cooling air extraction lines are connected to a cavity after a compressor. The gas-turbine engine can contain an onboard computer and radial clearance measuring sensors above each impeller of all the cooled turbine stages, which are connected with electrical communications to the onboard computer. Each annular insert can be hollow. The internal cavity of each annular insert can be filled with a heat-accumulating substance.
EFFECT: achieving efficient control of radial clearances in the turbine in all modes, increasing engine thrust in takeoff and augmented modes, and improving turbine efficiency and reliability.
4 cl, 6 dwg
