MOVING BLADE OF GAS-TURBINE ENGINE TURBINE Russian patent published in 2014 - IPC F01D5/20 F01D5/18 

FIELD: machine building.

SUBSTANCE: moving blade of a gas turbine engine turbine comprises an upper end platform with labyrinth seal teeth being set on it. The platform is fitted by a through hole for cooling air and is made as a parallelogram with two sides of the latter being oriented in the rotation direction and the other two being fitted by oppositely directed cuts with contact surfaces and strain compensators embracing them. The platform is equipped by support and control ribs. The support rib is set between the strain compensators with the length of (0.7 - 0.9)H and at the distance of (0.1 - 0.9)L from the cut vertex. The control rib is provided on the side edge of the platform on the side of the convex surface of the profile part between the strain compensator and the labyrinth seal tooth with the height of (0.7 - 0.85)h of the seal tooth height. The height of the strain compensators and the support rib respectively amounts to (1 - 2)d and (1.5 - 3)d, where H stands for the distance between the strain compensators; L - distance from the cut vertex to the rear side of the platform oriented in the rotation direction; h - seal tooth height; d - platform thickness.

EFFECT: longer service life of engine turbine blade at keeping the necessary air consumption via the cooling system for a moving blade and insignificant increase of weight.

3 cl, 5 dwg