GAS TURBINE COOLED MOVING BLADE

摘要

Gas turbine cooling moving blades, wherein a cooling air supply path is shortened to prevent possible temperature rise of a cooling air and suppress pressure drop until the cooling air reaches the blades. Cooling air passages (16) are formed in a casing wall below first stage stationary blades (11) with one end (16a) thereof opened toward a casing and the other end (16b) thereof opened toward a space (13). The cooling air passages (16) are oriented to permit the cooling air to jet toward air flowing holes (6) provided in shank portions (4) below platforms (2) of moving blades (1), flow into the shank portions (4) from the air flowing holes (6) and enter the moving blades (1). Since axes (17) of the cooling air passages (16) are deviated at an angle, which is determined by a speed of the cooling air jetting from the cooling air passages (16) and a revolving speed of the moving blades (1), in a circumferential direction from positions of the air flowing holes (6) when the moving blades (1) are stationary to align with the stationary blades (11) in an axial direction, the cooling air can be oriented and jetted in an optimum direction over a shortest distance. Accordingly, temperature rise and pressure drop are suppressed to the minimum.