The purpose which has guided the integration and the development of the quick-start system is the increase of safety during intended single-engine operation for rotorcraft application, leading to an effective reduction of the start-up time of the inactive turboshaft engine. The acceleration torque provided by the system is obtained through a pressurized air injection at the compressor section using an impingement system made up by three De Laval nozzles, integrated into the impeller casing. During maintenance operations on the modified engine at the TUM laboratory, one blade of the last stator stage in the axial compressor has found damaged and the investigation of the possible causes that have lead to this failure was the aim of this work of the thesis.