FIELD: turbines or turbomachines.
SUBSTANCE: invention relates to turbine blade of gas-turbine engine. Blade comprises a foot with a blade having a leading edge and a trailing edge, a trough wall and a back wall, as well as a front edge cooling coil, supply channel for collecting air at the level of the blade leg and supplying the collector, a side cavity extending along the back wall and supplied with air supplied from the blade root, to form a heat shield opposite the feed channel. Trombone-shaped contour comprises an intermediate portion extending along the feed channel and extending transversely to the back wall, wherein said middle section is supplied with air by means of a supply channel at the level of the feather apex.
EFFECT: invention allows improving cooling efficiency of turbine blades.
10 cl, 4 dwg
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