| 摘要 |
The interior of a gas turbine moving blade is sectioned by a rib into cooling passage portions. Cooling air enters one of the cooling passage portions and turns to flow into the other cooling passage portion. A stagnation area occurs in an end corner portion of the one cooling passage portion, but a cooling hole is provided so that air flow comes outside of the blade through the cooling hole, and thus cooling air flow occurs thereat. Also, a separation area occurs in a tip end portion of the rib due to separation of air flow, but another cooling hole is provided so that air flow comes outside of the blade and cooling air flow occurs thereat. Further, in a gas turbine moving blade having turbulators provided in multi-stages on a cooling passage inner wall, a film cooling hole structure for eliminating separation of cooling air flow between the turbulators is also provided.
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