Structure of discrete guide vane in the internal cooling channel to control local cooling performance on internal surface

摘要

The guide vane structure for local control of cooling performance after the bending portion inside the gas turbine blade according to an embodiment of the present invention includes a first flow path through which the cooling gas flows, a second flow path through which the cooling gas flows, And a guide vane installed from the point where the bending portion and the first flow path meet to the point where the bending portion and the second flow path meet.;