COOLED BLADE FOR GAS TURBINE Russian patent published in 2015 - IPC F01D5/18 

FIELD: machine building.

SUBSTANCE: cooled blade for gas turbine contains radially continuing aerofoil profile with frond edge, rear edge, suction and discharge sides. At the suction side of the rear edge the hanging projection is provided, it additionally contains multiple radial internal through channels, connected by bends to create multipassage serpentine for the cooling medium flow. For the rear edge cooling there is ejection area of the rear edge, containing passage of rear edge of the multipassage serpentine passing, in principle, in parallel with the rear edge and connected through the full length with the relief device of the discharge side. The cooling flow from the rear edge passage towards the relief device of the discharge side is determined mainly by staggered field of rods, that is provided between the relief device of the discharge side and rear edge passage, with set size of rods increased in direction of the cooling medium flow. In area of the bushing and blade tip the local rods field of the bushing and tip is provided with increased number of rods. At least inside the local rods field of the bushing and tip the rods are located by the straight rows that are inclined relatively to the axial direction at specified angle.

EFFECT: invention ensures optimal local heat exchange.

9 cl, 7 dwg