| 摘要 |
PURPOSE:To allow the securing of a prescribed outflow Mach level by forming the peripheral part of rotary vanes in the shape of wings with small curvature at their rear end part and deciding an angle formed by almost flat intrados and the periphery at that point appropriately in relation to non-dimensional peripheral speed. CONSTITUTION:In an axial flow turbine with rows of rotary vanes 1, 2 which are revolving at transonic speed, the back surface 8 and the intrados 7 of the vane surface at its rear end part 6 are formed to be almost flat at an outer peripheral part in the radial direction where the channels for the rows 1 and 2 of the rotary vanes form the transonic flow of the rotary vanes shaping tapering passages between the front end part 5 and the rear end part 6 of rotary vanes 1, 2. The intrados outlet angle rP is set to be smaller than the straight line connecting a point with the non- dimensional peripheral speed of 0.9 and rP of 41 degrees and another point with the non-dimensional peripheral speed of 0.9 and rP of 31 degrees in relation to non- dimensional peripheral speed for respective stage surfaces for the peripheral part in the radial direction for transonic flows. It is also set to be larger than a straight line connecting between a point with non-dimensional peripheral speed of 0.9 and rP of 31 degrees and another point with the non-dimensional peripheral speed of 1.54 and rP of 10 degrees.
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