The current development in civil aviation is characterized by increasing cost and competitive pressure, which is partly passed to the maintenance, repair and overhaul companies by the airlines. To improve the engine maintenance, the condition-based maintenance is becoming more established. The condition-based maintenance is characterized by tailored maintenance actions for each part of the engine, depending on the particular engine history and operating conditions. In the future, this maintenance philosophy continues to the item level, which is requiring a detailed knowledge of the influences of different piece part conditions on the associated engine performance. Using the example of the high pressure compressor, the aim is to accurately evaluate the aerodynamic performance of each compressor airfoil. However, this knowledge is currently not available sufficiently in the current engine overhaul. Thus, at this moment it is not possible to build up a compressor with selected blades to achieve desired performance characteristics. The work presented here is intended to reduce this knowledge gap and will help to further improve the condition-based engine maintenance in terms of an assembly recommendation for the compressor. For this purpose, a process was developed, that is able to evaluate the aerodynamic performance of digitized compressor airfoils and to predict their impact on engine performance parameters. In the present work, this process is first theoretically run through and the necessary theoretical foundations of the respective process steps are discussed. Subsequently, the process is run through with the example of the high pressure compressor of a civil engine of medium thrust class. First, the geometrical variations caused by deterioration on a front and rear compressor stage are statistically evaluated. Subsequently, the geometric parameters dominating the aerodynamic performance are identified by means of a modern design of experiments and the influence on the engine performance parameters is evaluated. As a result of this work, it is possible to name the dominant geometric parameters for the aerodynamic performance of the compressor stages. These parameters should be measured and evaluated during maintenance in addition to those, prescribed in the engine manual. As a result, the performance characteristics of the compressor can be roughly estimated for future repaired compressors even before the engine is tested and therefore expensive troubleshooting could be avoided.weiterlesen