GAS TURBINE COOLED BLADE Russian patent published in 2009 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine cooled pump blade root, hollow body with back and suction and pressure faces, and baffles arranged to make chamber there between whereto cooling medium is fed. Suction and pressure faces have openings for cooling medium to escape. The chamber formed by baffle and pressure face as well as suction and pressure surfaces have ribs that stay in contact between themselves to make crossing channels, a matrix, for cooling air to pass there through. The baffles are arranged to make chamber between two cavities whereto the distributed channel and collector are made. Ribs on suction face are inclined at acute angle to blade root plane against the outer stream. Ribs on pressure face are inclined at acute angle to blade root plane against the outer stream. Pressure face has openings with inlet cross section area smaller than outlet cross section area, and with axes inclined along outer flow at acute angle to tangential line to pressure surface profile, at the point aforesaid flow crosses the opening axis. Aforesaid openings communicate manifold with flow passage.

EFFECT: higher efficiency of cooling.

10 cl, 5 dwg