Rising demands on engines in the aerospace industry require high engine inlet temperatures in modern gas turbines in order to increase the efficiency. Single-crystal nickel-based superalloys were developed in order to meet these rising demands and confer high pressure turbine blades with the necessary wear and oxidation resistance at high temperatures. The blades of the high-pressure turbine are subject to significant wear due to the high mechanical strain under extreme conditions, which appears in the form of cracks in the single-crystal substrate material. There are no approaches for the restoration of the original material properties since the repair of cracks and erosions by polycrystalline laser cladding can be applied only to a limited extent. The aim of the subproject is the restoration of defect, single-crystal high-pressure turbine blades. This objective was achieved by developing a novel two-stage laser metal deposition process based on simulation, laser process development, process monitoring and temperature control.