TURBINE ROTOR BLADE, TURBINE ROTOR AND TURBINE Russian patent published in 2015 - IPC F01D5/16 

FIELD: machine building.

SUBSTANCE: gas turbine rotor blade contains aerofoil profile, bandage at its outside edge and bandage flange at internal edge. The bandage flange contains the upper plate installed near the aerofoil profile, tail, located beneath the top plate, and fixture under the tail. The blade also contains walls located along movement at front and aft of the tail. In the tail area a cavity is made passing through the wall arranged along movement at front or aft. The cavity has open side looking in the same direction as the front side of the tail. Front side of the tail is concave, and rare side is convex. Cavity in radial direction at the appropriate outside end has in axial direction length determined by thickness of the appropriate wall part. Cavity depth in the direction along the circumference increases or decreases in axial direction, and depth difference is determined as difference between maximum and minimum depths. The cavity length is below then 1.5 of diameter of the round touching the concave and convex sides of the tail, width of the cavity is below 0.7 of diameter of the above round, and depth difference is below 0.45 of diameter of the above round. Other inventions of the group relate to the turbine rotor containing the specified blades, and to the turbine with above mentioned blades and/or rotor.

EFFECT: group of inventions increases service life of the turbine blades due to rotor vibration decreasing.

11 cl, 3 dwg