FIELD: mechanical engineering; turbines. SUBSTANCE: proposed turbine blade relates to cooled blades of gas-turbine engines of ground or aircraft application. It contains airfoil portion with leading and trailing edges, blade pressure surface and blade suction face, with cooled inner space. Inner space of airfoil portion is connected by channels with pocket arranged on trailing edge of blade from side of pressure surface. Ratio of size of blade profile chord to width of pocket along middle line of blade profile is 6-20. EFFECT: provision of effective cooling of blade trailing edge, increased efficiency of turbine. 2 dwg
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