GAS-TURBINE BLADE WITH COOLING LOOPS Russian patent published in 2007 - IPC F01D5/18 

FIELD: mechanical engineering; gas turbines.

SUBSTANCE: proposed gas turbine blade for gas-turbine engine has feather overlapped in blade head area by cross wall and radially projecting beyond said wall to form bath. Blade contains also first cooling loop arranged in central part of blade with at least one outer space adjoining suction face of blade feather, at least one inner space, adjoining blade pressure surface, at least one central space arranged in central part of blade between inner space and outer space. Blade has also second cooling loop independent from first cooling loop. Said second cooling loop has at least one rear space arranged close to trailing edge of blade. Cross wall of blade has at least one outlet hole opening into rear space of second cooling loop and onto head of blade.

EFFECT: reduced average temperature of blade, prevention of formation of temperature gradients.

12 cl, 5 dwg