| 摘要 |
PROBLEM TO BE SOLVED: To properly cool this area, while reducing a mass part associated to a large fillet part 18, by substantially increasing a fillet radius of a turbine blade 11. SOLUTION: The blade 11 of a gas turbine engine has the relatively large fillet part 18 for improving a passing air flow characteristic. The fillet part 18 has a thin wall for defining a fillet cavity 24 in-between together with a collision rib 35. Cooling air is provided so as to collide with a rear surface 27 of the fillet part 18 by passing through a collision hole 26 of the collision rib 35. The collision hole 26 is formed substantially slender in the horizontal direction to the radial direction in a cross-sectional shape. COPYRIGHT: (C)2006,JPO&NCIPI
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