GAS TURBINE MOVING BLADE, GAS TURBINE, AND GAS TURBINE MOVING BLADE ADJUSTING METHOD

摘要

PROBLEM TO BE SOLVED: To improve heat efficiency of a gas turbine by reducing an amount of cooling air of a gas turbine moving blade.;SOLUTION: A belly side cooling flow passage 41 and a back side cooling flow passage 42 are provided on a front edge side inside a gas turbine moving blade 50, and film cooling holes 1a, 1b opened on a belley side or front edge blade surface are provided on the belley side flow passage 41. A film cooling hole 1c opened on a back side blade surface is provided on the back side flow passage. The belley side flow passage 41 extends in a moving blade downward direction and supplies cooling air from an opening 15a at the lower part of the moving blade. The back side flow passage 42 constitutes a meandering flow passage connected to the cooling flow passage adjacent on a blade rear edge side, and is configured to supply the cooling air from an opening 15b at the lower part of the moving blade independent from the belley side flow passage 41, to independently adjust supplying pressures of the cooling air to the belley side flow passage 41 and the back side flow passage 42. By this cooling structure, amounts of the cooling air emitted from the film cooling holes on the belley side and the back side of the blade are individually adjusted, and therefore, a film cooling performance can be improved and the cooling air amount can be reduced.;COPYRIGHT: (C)2014,JPO&INPIT