FIELD: machine building.
SUBSTANCE: object of the invention is a turbine rotor for a gas turbine engine, said rotor including: input turbine disc (1); output turbine disc (5); annular flange (b); first shroud (11) connecting the input turbine disc to the annular flange; second shroud (51) connecting the output turbine disc to the annular flange; an air-flow separator device including: first portion (3), forming a first ring, arranged between the input turbine disc and the output turbine disc; second portion (4), forming a second ring, having a first portion arranged opposite the output turbine disc and a second portion arranged between the first shroud and the second shroud; and thermal insulation area (6) arranged between the first portion and the second portion.
EFFECT: reducing the temperature difference, thereby preventing damage or rupture of the annular flange.
10 cl, 1 dwg
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