TURBINE BLADE AND ENGINE COMPONENT

摘要

A turbine blade used in the turbine of a gas turbine engine and cooled by cooling air is provided with: a cooling channel which is formed within the turbine blade and through which the cooling air flows; closed-end recesses (15) which are formed in a blade surface of the turbine blade and which have tilted downstream inner walls (15a); and ejection holes (17) which are formed in the respective bottoms of the closed-end recesses, the ejection holes (17) communicating with the cooling channel and ejecting cooling air. The ejection holes are formed in such a manner that the centerlines (17L) thereof extend along the downstream inner walls (15a). The cooling effect of the turbine blade is improved without a reduction in efficiency.