Blade system, and corresponding method of manufacturing a blade system

A blade system for a gas turbine, the blade system comprising:

• a blade device and a further blade device, the gas turbine comprising a rotor shaft having an axial direction, a radial direction and a circumferential direction,
• the blade device comprising
• a shroud,
• an airfoil extending from the shroud along the radial direction,
• wherein the shroud comprises at a circumferential end a wedge face,
• wherein the wedge face comprises a recess extending with a component along the axial direction, and
• a damping wire,
• wherein 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,
• wherein the 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,
• the further blade device comprising
• a further shroud and a further airfoil extending from the further shroud along the radial direction, wherein the further shroud comprises at a further circumferential end a further wedge face,
• wherein the further shroud is arranged adjacent to the shroud along the circumferential direction such that the wedge face and the further wedge face face each other,
• wherein the damping wire is arrangeable within the recess such that the damping wire contacts the shroud and the further wedge face of the further shroud,
• wherein the further wedge face comprises a plane surface onto which the damping wire is abuttable.