FIELD: engines and pumps.
SUBSTANCE: engine turbine comprises at least one cooled stage with distributor with chamber above and under it and turbine rotor with cooled impeller and turbine stator. Stator comprises at least two turbine housings with chambers between them. Radial clearance adjustment system includes circular insert fitted above turbine impeller. Chamber above guide vanes is communicated via air bleed pipe including flaw rate regulator with compressor outlet. Radial clearance adjustment system comprises onboard computer, radial clearance transducers and flow rate controller. Radial clearance transducers are electrically connected with onboard computer. Circular insert is made of material with high specific resistance and connected by power cables via switchboard with power source. Radial clearance is measured to cut on electric current through circular insert depending on current magnitude.
EFFECT: higher engine thrust at takeoff and afterburning, engine efficiency and reliability.
6 cl, 9 dwg
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