| 摘要 |
PURPOSE:To prevent occurrence of a crack in the through hole part of a front edge by providing grooves, which have opening parts perpendicular to a flow of high temperature gas, in the front edge part of a blade and also providing through holes which guide cooling air blow perpendicularly to the wall surfaces of said grooves. CONSTITUTION:A front edge part 31 of a gas turbine blade is provided with grooves 12, 13, which have opening parts nearly perpendicular to a flow of high temperature gas, and also provided with through holes 14, 15 for guiding cooling air blow perpendicularly to wall faces of said grooves 12, 13. Cooling air which flows in from the base part of the blade flows through a flow passage 2 and spouts out from through holes 14, 15 and, after dashing against wall surfaces of the grooves 12, 13, spouts outside the blade from the opening part. Thus, since the through holes, to which thermal stress is concentrated, are inside the groove and do not make direct contact with the high temperature gas, occurrence of a crack in the through hole part can be prevented. |
