System and method for repairing a damaged blade of a gas turbine engine

A method for repairing a damaged blade of a gas turbine engine, the method comprising:

• removing a portion of the damaged blade to form at least one stub portion, wherein the at least one stub portion protrudes from a root of the damaged blade and defines a deposition surface;
• positioning a sacrificial build platform on the damaged blade proximal to the at least one stub portion of the damaged blade, wherein the sacrificial build platform includes a base defining a pair of cavities, the damaged blade is at least partially received within the cavities of the sacrificial build platform, the at least one stub portion includes a pair of projections, each cavity is configured to receive a corresponding projection from the pair of projections;
• fusing the sacrificial build platform with the damaged blade;
• and
• depositing, by an additive manufacturing system, material on the base of the sacrificial build platform and the deposition surface of the at least one stub portion to form a base structure of a repaired blade.