COOLED BLADE OF HIGH-TEMPERATURE TURBINE Russian patent published in 2016 - IPC F01D5/18 

FIELD: engines.

SUBSTANCE: cooled blade of high-temperature gas turbine engine includes inner cylindrical baffles-turbulators and radial ribs. Surfaces of the inner cavity of the blade airfoil, including inlet edge and radial ribs, and the outlet part of baffles-turbulators along the flow of cooling air and mainly perpendicular to direction of this flow arrange cylindrical ledges interconnecting inner surface of the leading edge, baffles and ribs. Ratio of diameter D of the cylindrical baffle-turbulator to diameter d of cylindrical projection is within 1.5…10. Ratio of diameter d of cylindrical projection to height h of cylindrical projection is within 1.5…2.5.

EFFECT: invention improves reliability of the cooled blade by increasing efficiency of convection cooling of the blade airfoil.

1 cl, 4 dwg