The invention relates to a heavy-type
combustion engine high-temperature
turbine double-medium cooling blade, which is characterized in that: a first separation plate and a third separation plate are sequentially arranged from the
front edge and the end edge of a blade inner cavity to divide the blade inner cavity into a front cooling space, a middle cooling space and a rear cooling space to be independent from one another along the radial direction of the blade, the blade front cooling space is divided by a fourth separation plate into a first cooling cavity and a second cooling cavity,
impact cooling holes are equally distanced to one another to be arranged on the fourth separation plate, the
front edge of the blade is provided with four rows of gas film cooling holes which are alternatively arranged,
spoiler ribs which are arranged at equal intervals are arranged on a blade inner wall B of the middle cooling space, the middle cooling space is divided by a second separation plate into a third cooling cavity and a fourth cooling cavity, which are communicated with each other, the rear cooling space is a fifth cooling cavity, and the fifth cooling cavity is connected through fin-shaped vent holes which are equally distanced to one another; and the middle cooling space adopts a steam closed-type
cycling cooling way to be combined with the
air cooling way of the front and the rear cooling spaces, so the
cooling fluid has
high heat exchanging coefficient on each position of the blade, the
cooling effect can be improved, and the unit heat efficiency can be improved.