FIELD: power engineering.
SUBSTANCE: blade of gas turbine of turbomachine has cooling circuit, comprising at least one cavity of cooling having prolonged shape arranged in radial direction between blade tail and its end, and at least one inlet hole. Inlet hole is arranged in lower radial end of cavity and is intended for cooling air supply in it. At the same time at least one of cooling cavity walls is provided with grooves arranged till radial height that makes 30% of full radial height of blade airfoil portion from its tail to end with provision of cooling air flow excitation in specified cavity and increased heat exchange.
EFFECT: improved efficiency of blade cooling with simplification of its manufacturing.
10 cl, 6 dwg
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