FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft has turbines. Low-pressure turbine rotor comprises working wheels with discs, working blades and outer labyrinths. Every said outer labyrinth is bolted to external flange of appropriate disc rim on working blade inlet edge. Besides, every labyrinth includes the flange abutting on the disc lock joint radial ledges. Said flange features L-like cross-section shape. Lock joint of every disc gas axial ledges directed towards working blade inlet edge. Axial ledges are arranged so that ratio between axial ledge IDs and radial clearance between axial ledges and L-like flange makes 300…8000.
EFFECT: higher reliability owing to ruled out vibration strains.
3 dwg
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