FIELD: mechanical engineering; engines.
SUBSTANCE: proposed gas turbine engine contains axial-flow turbocompressor with radial labyrinth seals between spaces of turbine or compressor made on rotor and stator of turbine or compressor in form of labyrinth rings, each provided with at least one straight and one inverted radial tooth. Points of teeth are directed in operation relative to ring flanges on stator or rotor. Seals of straight and inverted radial teeth form blind space separating duct space of turbocompressor from dummy space of turbine or compressor. At least one labyrinth ring of radial seal is provided with additional outer or inner flanges. At least one additional radial tooth is made on one of said flanges opposite to direction of straight tooth or, respectively, inverted radial tooth on other flange of labyrinth ring. Radial labyrinth seal is furnished with additional seal on its mating ring flange for additional radial tooth. Buffer space is formed by additional radial tooth and additional seal on its mating ring flange, and by straight or inverted radial tooth on one of flanges of labyrinth ring. Buffer space separates duct space of turbocompressor from dummy space of turbine or compressor.
EFFECT: improved reliability of labyrinth seals, stabilized axial loads of turbocompressor, improved economy of operation under abnormal conditions.
3 cl, 6 dwg
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