Author:
Schwerdt Lukas,Maroldt Niklas,Panning-von Scheidt Lars,Wallaschek Joerg,Seume Joerg R.
Abstract
AbstractCurrent developments in turbomachinery favor blade designs which are characterized by low damping. The associated reduction of structural damping, however, creates new problems such as higher vibration amplitudes. Therefore, accurate predictions of these vibration amplitudes and of the fatigue life become increasingly important. Analyzing multistage machinery by only simulating isolated stages can be insufficient. This is particularly the case during repair processes when mistuning, such as that created by wear and repair, magnifies said amplitudes. In this chapter selected current results of the subproject C6 of the Collaborative Research Center (CRC) 871 are presented, building on the earlier research in the subprojects C3 and C6 focussing on mistuning and aeroelasticity, respectively. First, a simulation approach which accounts for structural and aeroelastic interstage coupling under conditions of mistuning is described, followed by an approach for incorporating large mistuning effects into a reduced order model of a single rotor stage. The former model is used to study the effect of intentional mistuning to decrease the sensitivity to additional mistuning due to wear and repair and to allow for smaller safety margins. The aeroelastic models are validated for a 11/2-stage axial compressor.
Publisher
Springer International Publishing
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