Abstract: Disclosed is a method of repairing gas turbine blade which has at least one cavity and which has damage in the region of its blade tip, which damage extends through a rim region and a core region of the blade into the at least one cavity. The method comprises at least: a) removing blade material at least in the region of the damage, forming at least one cutaway reaching into the cavity; b) replacing the damaged region by filling the at least one cutaway with a repair material using at least one generative production method; and c) finishing the blade at least in the region of the at least one refilled cutaway. The invention also relates to a gas turbine blade repaired in this manner.