FIELD: machine building.
SUBSTANCE: turbine assembly of aircraft gas turbine engine comprises first blade rotor, vane stator and second vane rotor arranged in series. Rotors are installed on shaft, and sealing plate passes between stator and shaft. Sealing plate separates the first cavity located between the first rotor and the stator from the second cavity located between the stator and the second rotor. Inside the first cavity there are means of reducing pressure containing multiple radial ribs forming a centrifugal compressor.
EFFECT: invention allows reducing leakage of working medium between cavities in turbine of gas-turbine engine.
11 cl, 6 dwg
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