In order to prevent in-flight fatigue failure, a numerical analysis of in service-operative cases is an useful approach for preliminary evaluation of most stressed and critical zones in components of aeronautical engine. The zero-stage compressor rotor disk and blades represent one of the most critical part of aircraft turbojet. This paper presents a verification FEM analysis of this component. An accurate 3D scanning was performed to reconstruct both blade and disk real geometry and the detailed point cloud was obtained and opportunely elaborated by using specific software to generate CAD sections and volumes given in input to finite element analysis. The stress field due to different operating conditions is studied for a suitable evaluation of the most stressed and critical areas where a failure may occur, particularly near the rotor connection under contact conditions. FEM and flight data analysis are finally used for a subsequent fatigue life verification, based on classical Palmgren Miner’ rule. The suggested procedure for verification of engine aeronautical component is here optimized for maintenance program improvements.

为了防止飞行中的疲劳失效，对在役情况下的数值进行分析是一种有用的方法，用于初步评估航空发动机部件中的最大应力区域和关键区域。零级压缩机转子盘和叶片代表了飞机涡轮喷气发动机最关键的部分之一。本文介绍了对此组件的验证FEM分析。进行了精确的3D扫描以重建叶片和磁盘的实际几何形状，并通过使用特定软件生成CAD截面和有限元分析输入中给出的体积，详细获得了点云并进行了详细阐述。研究了由于不同工作条件引起的应力场，以便对可能发生故障的最受应力和最关键的区域进行适当的评估，特别是在接触条件下靠近转子连接处。最终，根据经典的Palmgren Miner规则，将FEM和飞行数据分析用于随后的疲劳寿命验证。此处针对发动机航空部件的验证建议程序已针对维护程序改进进行了优化。