GAS TURBINE WITH VARIABLE INTERNAL COOLING PASSAGE USING SHAPE MEMORY ALLOY

摘要

The present invention relates to a gas turbine having a variable cooling passage comprising: a blade rotated by a high-temperature and high-pressure gas of a combustion device; a blade dovetail formed in a lower portion of the blade to support the blade; and a cooling passage enabling a cooling air supplied from a compressor to be introduced to the inside of the blade through the inside of the blade dovetail to cool the blade. The gas turbine comprises: a tube fixated to the inside of the cooling passage; and a plurality of variable members installed along an inner circumferential surface of the tube and formed to have two layers to enable a shape of the variable member to be changed by temperature changes of the cooling air and varying an inner cross-sectional area of the tube to control a flow rate of the cooling air.