| 摘要 |
A cooling blade of a gas turbine having a turning angle of at least 115 is provided. The blade has such a shape that the diameters of circles inscribing the belly and back sides at different positions of adjacent blades decreases as one goes from the front edge to the rear edge. Since the blade has such a shape, even if the influent angle and effluent angle of gases are increased, a deceleration passage is not formed in the passage between the adjacent moving blades. The blade has a cooling passage which is near the rear edge, and the ratio of the distance from the cooling passage to the rear edge and the wall thickness of the rear edge of the blade is 2 or less.
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