Blade cooling structure of gas turbine

Abstract

A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).

Dependencies are inferred from the claim text.