METHOD FOR COOLING A MICROCIRCUIT OF A BLADE OF A GAS TURBINE ENGINE COMPOSED OF A FAN, A COMPRESSOR, A COMBUSTOR, A TURBINE AND A NOZZLE

摘要

PURPOSE: A cooling method of a microcircuit for a turbine blade is provided to improve the performance of the engine, and to cut down operation cost of the engine by efficiently cooling the air foil of the turbine with cooling air and extending the life span of the blade. CONSTITUTION: Plural cooling microcircuits(22) are arranged in a wall(24) of the air foil of a turbine blade, and the cavity is formed in the turbine blade. The microcircuit includes a front end, a rear end(45), a first side(46), a second side(48), a first inner wall(65), a second outer wall, and pedestals(68) extended between the first inner wall and the second outer wall. The turbine rotor blade is composed of the outer wall including the inner surface, the cavity in which cooling air flows, a first cooling circuit, a second cooling circuit and a third cooling circuit mounted to the wall.