FIELD: machine building.
SUBSTANCE: turbine guide blade has a hollow airfoil, in which there is a coolant bypass channel, having inner and outer sides separated by walls. Coolant bypass channel extends from the first component of the gas turbine to the second component of the gas turbine and has means that change heat transfer between the inner and outer sides and/or the flow mode on the inner and outer sides. Means for changing heat transfer between the inner side and outer sides includes a coating comprising a ceramic material. As an additional means of changing heat transfer between the inner and outer sides, it is provided that the walls are hollow. Cavity of the walls is sealed against the inside and outside.
EFFECT: invention is aimed at extending the service life of gas turbine components and increasing efficiency.
8 cl, 5 dwg
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