FIELD: machine building.
SUBSTANCE: turbine blade (1) of gas turbine engine comprises backrest (11), trough (12), front edge (13) and rear edge (14), as well as bath (2) at its end. Said bath (2) is formed by bead (2a) and comprises inner rib (3), which is located at distance from bead (2a) forming said bath (2). Inner rib (3) is made to restrict inside bath cavity (4), inside of which passage of leakages (5) is limited. Bath (2) comprises bottom (2b). Cavity (4) is confined by part of bath bottom (2b), which is surrounded by said inner rib (3).
EFFECT: invention is aimed at improvement of efficiency of turbine due to improvement of its aerodynamic and aerothermal characteristics of turbine.
10 cl, 12 dwg
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