Blade system for a gas turbine, the blade system comprising a blade device (100) and a further blade device (300), the blade device comprising a shroud (110), an airfoil (105) extending from the shroud (110) along the radial direction (103), wherein the shroud (110) comprises at a circumferential end (111) a wedge face (201), wherein the wedge face (201) comprises a recess (202) extending with a component along the axial direction (102), and a damping wire (401), wherein the damping wire (401) is arranged within the recess (202) such that the damping wire (401) is adapted for contacting the shroud (110) and a further wedge face (403) of a further shroud (310) of a further blade device (300) which is arranged adjacent to the shroud (110) along the circumferential direction (104), wherein the recess (202) comprises an inclining side surface (402) which comprises a normal (n) which is non-parallel with the radial direction (103), wherein the further wedge face (403) comprises a plane surface onto which the damping wire (401) is abuttable. A corresponding method of manufacturing a blade system is also provided.