GAS TURBINE COOLING MOVING BLADES

摘要

In gas turbine cooled moving blade, cooling air passage is made shortest and temperature elevation and pressure drop of cooling air are suppressed. Cooling air passage (16) is bored in turbine cylinder wall (15) below stationary blade (11) of first stage. The cooling air passage (16) connects at one end (16a) to turbine cylinder and at the other end (16b) to space (13) and is directed to air inflow hole (6) provided in shank portion (4) of lower portion of platform (2) of moving blade (1). Cooling air is jetted from the cooling air passage (16) toward the air inflow hole (6) so as to flow into the shank portion (4) and then into the moving blade (1) for cooling thereof. Axis (17) of the cooling air passage (16) is directed with deviation in rotational circumferential direction by angle determined by jetted velocity of the cooling air jetted from the cooling air passage(16) and rotational velocity of the moving blade (1) from position of the air inflow hole when the moving blade (1) stands still in row with the stationary blade (11) in rotor axial direction. Thus, the cooling air can be jetted in optimal direction with shortest distance and temperature elevation and pressure drop of the cooling air can be suppressed to minimum. <IMAGE>