FIELD: gas turbines.
SUBSTANCE: proposed blade has hollow feather built of front and rear spaces separated by means of partition and provided with perforated baffle plates. Holes are also made in wall of front space of feather. Radial rib with hole is provided on partition at rear space end. Ratio of hole areas in rear space baffle plate on tray and blade back ranges between 0.5 and 0.65.
EFFECT: reduced temperature field nonuniformity in sectional area of blade; reduced thermal stresses.
1 cl, 3 dwg
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