COOLED BLADE OF GAS TURBINE Russian patent published in 2005 - IPC

FIELD: mechanical engineering; gas turbines.

SUBSTANCE: proposed cooled blade of gas turbine contains hollow airfoil portion with three radial partitions. Front partition is located at leading edge, separating partition is located between front and rear spaces of airfoil portion of blade and rear partition is arranged in rear space of blade. Inclined ribs are made on walls of airfoil portion between front and separating partitions. Ribs on suction face are displaced through half of pitch relative to ribs on blade pressure surface. Holes are made in front partition. Cross ribs at pitch equal to pitch on holes in front partition are installed in channel arranged along leading edge on inner surface of wall from side of blade pressure surface. Four rows of cylindrical pins and cross ribs of trailing edge are arranged in channels of trailing edge. Cross ribs are made with extension along cylindrical surface of leading edge, their height being not less than diameter of holes. Rear partition is made in form of two semiribs installed on walls from side of suction face and blade pressure surface and interconnected by cylindrical pins.

EFFECT: improved cooling of leading edge and equalizing temperature field in rear space of blade airfoil portion.

2 dwg