GAS TURBINE BLADE WITH CONVECTIVE COOLING SYSTEM Russian patent published in 2017 - IPC B01J3/00 

FIELD: machine engineering.

SUBSTANCE: known gas turbine blade with the convective cooling system, containing the stylus, bounded by the input and the output edge with the slotted hole and the profiled section with the convex and the concave walls, restricting the cooled cavity of the feather, the holes in the end face of the feather and the rim, the profiled ribs, forming the system of distributing and cyclone radial channels in the cooled cavity of the feather, cooling intensifiers made in the cooled cavity, the channels in its locking part for the air supply, the channels in its locking part are connected to the cooling cavity, with the holes in the end surface of the feather and with the slotted hole in the output edge, by proposal, the profiled ribs, forming the radial channel system are made pairswise of one length, and the distance from the radial channels peripheral ends to the end surface for each subsequent pair in the direction from the leading edge to the output edge is greater than the previous one. The feather end face rim can be located along the profile generatrix of the convex wall and the input edge.

EFFECT: reduction of the cooling air consumption, the simplification and reduction of the production costs, the increase of mechanical strength and resistance to contamination, the increase of efficiency and the working life of the blade and the engine as the whole.

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