BLADE SYSTEM AND CORRESPONDING METHOD OF MANUFACTURING A BLADE SYSTEM Russian patent published in 2018 - IPC F01D5/22 F01D5/30 

FIELD: machine building.

SUBSTANCE: blade system for a gas turbine comprises a blade device and a further blade device. Blade device comprises a shroud, an airfoil extending from the shroud a damping wire. Shroud comprises at a circumferential end a wedge face with a recess, and the damping wire is arranged within the recess such that the damping wire is adapted for contacting the shroud and a further wedge face of a further shroud of a further blade device which is arranged adjacent to the shroud along the circumferential direction. Recess comprises an inclining side surface which comprises a normal which is non-parallel with the radial direction, such that the radial distance to the rotary axis of the damping wire changes when being moved along the inclining side surface. Damping wire is contained within only one inclined recess in the shroud of one blade so that when using a gas turbine, the damping wire moves along the inclining side surface of the recess from the radially outer position in the recess to the radially inner position of the recess. Damping wire contacts the shroud and the further wedge face of the further shroud in a radially outer position in the recess. Further wedge face comprises a plane surface onto which the damping wire is abuttable. When manufacturing the blade system further shroud is placed adjacent to the shroud along the circumferential direction so that the wedge face and the further wedge face faces each other, and the damping wire is contained within only one inclined recess in the shroud of one blade.

EFFECT: group of inventions provides simpler assembly and disassembly of a gas turbine blade system of which comprises a damping wire between the shrouds of adjacent blades.

8 cl, 4 dwg