FIELD: machine building.
SUBSTANCE: invention relates to the gas turbine element with film cooling, having a exposed to the hot gas surface, in which the film cooling holes are made. In its flow direction, each of the film cooling holes has a channel portion and directly adjacent thereto diffuser portion, including the diffuser portion upstream edge, two longitudinal edges and the diffuser portion downstream edge. Each longitudinal edge converges with the diffuser portion downstream edge in the corner area. To create the film cooling holes effective arrangement, which cooling film is formed closer than before, behind the diffuser portion downstream edge, corresponding channel portions axes must be inclined to the hot gas flow local direction, and their diffuser parts are made asymmetric so, that the adjacent film cooling holes immediately adjacent corner areas, when viewed in the hot gas flow direction, are aligned.
EFFECT: invention is aimed at increase in the cooling efficiency.
9 cl, 5 dwg
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