FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises compressor with at least one stage, combustion chamber with fire tube, turbine including at least one cooled stage with distributor with cavities above and under it. Turbine rotor incorporated cooled impeller and swirler arranged there ahead. Turbine stator comprises at least two turbine casings with cavities there between and radial clearance adjustment system including ring insert arranged above the impeller. Cavity above distributor is communicated via air bleed pipeline including flow rate controller with compressor outlet. One of said cavities between turbine casings is communicated via pipeline including second flow rate controller with compressor mid stage. Radial clearance adjustment means comprises radial clearance transducers and onboard computer electrically connected with flow rate controllers and radial clearance transducers.
EFFECT: efficient control over radial clearance, higher takeoff and augmenter thrust, efficiency and reliability.
3 cl, 16 dwg
