FIELD: turbines.
SUBSTANCE: gas turbine engine guide vanes sealing device, containing turbine rotor, wherein said turbine guide vanes comprises, at least one internal annular section, wherein said turbine rotor includes output side located substantially in axial direction, wherein said sealing device contains at least one sealing sheet, arranged radially between internal platform and turbine rotor outlet flange to form overlapping clearance.
EFFECT: technical result of invention is sealing reinforcement, making it possible to avoid rotor discs heating.
10 cl, 9 dwg
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