| 摘要 |
In the blade structure in a gas turbine, inlet included angles are made large. As a result, a curve of a relative relationship between incidence angles icl and isl and pressure loss becomes mild. Entrance metal angles, which are formed by an axial direction of the gas turbine and a tangential direction to a camber line at the front edge of the stationary blade, are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
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