Efficient modeling of mistuned blade aeroelasticity using fully-coupled two-scale method

Abstract

Blade-to-blade variations, known as mistuning, significantly affect the turbomachinery aeroelastic performance. Typically mistuning is observed to be beneficial for flutter stability but detrimental for forced response. In some unconventional cases however, mistuning may even result in a benefit in forced response as reported by some researchers. Many previous studies indicated that neglecting the mistuning-induced changes in aerodynamic forcing and damping would lead to erroneous results. To include these aerodynamic effects, the natural approach is to perform a fully-coupled multi-passage simulation. However, it is apparent that this approach would need a higher simulation cost. In this paper we propose an efficient two-scale method for fully-coupled simulations. The validity and effectiveness of the method is demonstrated in forced response case studies for a mistuned bladerow. The proposed methodology is shown to be by one order of magnitude faster than the baseline fine-mesh simulations, while having a similar accuracy.