Abstract
Axial compressors of aero engines should achieve both high efficiency and low weight. Recently, blade-integrated disks (blisks) have been adopted to meet these requirements. Because of this trend, problems of high-cycle fatigue (HCF) associated with forced response vibrations are occurring more frequently these days. Rotor blade fatigue can be caused by not only wakes and potential effects of adjacent stator vanes but also the asymmetric geometries inside compressors. Even the measurement probes can be the cause of severe blade failure. Although, there have been many previous studies on developing simulation approaches for the accurate prediction of blade vibration induced by adjacent stator vanes, studies of vibration induced by the measurement probes have been scarce. Thus, in this study, the vibration induced by measurement probes is studied using fluid structure interaction (FSI) simulation approach and an experimental test rig. The ways to predict and reduce blade vibration are established and validated.
