| 摘要 |
In shower head cooling out of a prior art film cooling of gas turbine blade, as cooling holes (1) are arrayed on a straight line toward blade hub side (HS) from blade tip side (TS), there occur different pressures at each position of the cooling holes (1) with result that uniform film cooling cannot be done. The present invention is to provide a gas turbine blade which dissolves said problem in the prior art and attains uniform pressure over the shower head cooling holes, so that uniform film cooling can be done. A plurality of shower head cooling holes (1) bored in blade leading edge portion are arranged on one line biased so as to correspond to a respective case where direction of swirling flow in combustor is clockwise or counter-clockwise; that is, on one line biased to the left hand side, seen from upstream, toward blade hub side (HS) from blade tip side (TS) in the former case or on one line biased to the reverse side in the latter case, thus avoiding influence of the swirling flow, pressure at each position of the cooling holes (1) is made constant, so that uniform cooling can be attained.
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