| 摘要 |
PURPOSE: To obtain a good cooling effect by cooling air having few rate and low pressure by arranging a passage of a radial direction adjacently to a profile of a turbine blade, and forming a plurality of film cooling air holes opened to a pressure side of a blade communicating with the passage. CONSTITUTION: An axial flow turbine blade made of high heat resistance alloy is provided with a front edge 12, a rear edge 14, and a ring part for defining a profile surface having a suction side 20 (low pressure) and a pressure side 22. A plurality of holes are arranged on a profile surface so as to achieve desired cooling, and a plurality of cooling air passages defined by a rib 26 for making air flow in a bending shape is arranged so as to obtain optimal reflux cooling. A cylindrical cooling air channel 30 is formed adjacently to a profile surface, and cooling air is blown out from multiple film cooling air holes opened to the channel 30 so as to form a cooling film on the pressure side 22.
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