To provide a gas turbine cooling vane capable of reducing the amount of air used as cooling medium and reducing a combustion temperature to improve a gas turbine effect and reduce NOX in a detailed cooling structure according to a heat load on the vane surface of the gas turbine cooling vane.
This gas turbine cooling vane in the cooling structure for cooling from the inside thereof by leading the cooling medium 9 into a cooling passage 22 formed therein comprises a plurality of cooling parts 21 in a size according to a heat load on the vane surfaces opposed to each other, a first hole 23 provided in the cooling parts 21 and allowing the cooling medium 9 to flow therein from the cooling passage 22, and a second hole 24 allowing the cooling medium 9 allowed to flow into the cooling part 21 to flow out for film cooling. The cooling medium 9 is allowed to flow into the cooling parts 21 through the first hole 23, sprayed on the inside walls 21a of the cooling parts 21, and then allowed to flow to the outside through the second hole 24.
HASHIMURA JUNJI
MATSUURA MASAAKI
TAKEISHI KENICHIRO
TOMITA YASUMOTO
KUWABARA MASAMITSU
INADA MITSURU
SUGISHITA HIDEAKI
