GAS TURBINE BLADE Russian patent published in 2016 - IPC F01D5/18 

FIELD: machine building.

SUBSTANCE: gas turbine blade contains a shank and body of the blade with entry and output edges, and tip, channels system for cooling air, going from the cooling air hole in the shank by means of the tortuous serpentinous channel to the channel located in zone of the output edge near the output edge having air outlet in the output edge, and bypass channel for air. The bypass channel connects the cooling air hole in the shank with channel, located in the zone of the output edge, bypassing the serpentinous channel. The channels system for the cooling air contains a radial channel, opened to the throughput serpentinous channel, and to the channel located in the tip zone and connecting the cooling air hole in the shank by means of the said radial channel with at least one air outlet on the located at side of the output edge area of the external in radial direction surface of the blade tip on top part of the tip, supplying the cooling air to the located at side of the output edge area of the external in radial direction surface of the blade tip on top part of the tip.

EFFECT: increased efficiency of cooling of the output edge of the blade body.

13 cl, 3 dwg