| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving cooling performance while suppressing a pressure loss of a pin fin cooling structure. <P>SOLUTION: The gas turbine blade 1 having a pin fin passage 10 composed of opposed back side cooled surface 6a and ventral side cooled surface 6b in an interior is equipped with a pin fin 11 laid between two cooled surfaces 6a, 6b and a triangular pyramid shape vortex shedder 14 projected on at least the ventral side cooled surface 6b. The vortex shedder 14 is disposed so that an apex angle of the bottom surface 15 in contact with the cooled surface faces the upstream side of the flow direction of the cooled air, the apex 16 separated from the cooled surface has a shape biased to the upstream side of the flow direction of the cooled air, and is disposed at the upstream side of the flow direction of the cooled air with respect to the pin fin 11. <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
