FIELD: machine building.
SUBSTANCE: composite turbine blade of a gas turbine comprises a shank for mounting said blade in a corresponding peripheral mounting groove of the rotor, a stylus connected to the shank, and an internal bearing structure. Internal bearing structure passes at least on section of said shank, as well as at least on section of said blade. Internal bearing structure is made of high-strength eutectic ceramic material, and eutectic ceramic material has low fracture toughness. Feather is made from composite material with ceramic matrix.
EFFECT: invention ensures required mechanical properties of the blade with reduced need for cooling air during operation of the turbine.
13 cl, 8 dwg
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