| 摘要 |
PROBLEM TO BE SOLVED: To provide a binary cooling medium type turbine blade. SOLUTION: The turbine blade (46) includes a dovetail (56) and a hollow airfoil part (54) joined to a platform (58). The airfoil part (54) includes leading- and trailing-edge cooling circuits (68, 70) arranged along the leading- and trailing-edges (64, 66) of the airfoil part between the positive- and negative-pressure side walls (60, 62) facing the airfoil part. The leading-edge cooling circuit (68) includes the radial inlet (74) starting from the basement of the dovetail (56) and the trailing-edge cooling circuit (70) includes the axial inlet (76) starting from the rear face of the dovetail (56), which receives the cooling medium having the different pressure and temperature. COPYRIGHT: (C)2005,JPO&NCIPI
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