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

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 forced response. In some unconventional cases however, may even result in a benefit response reported by researchers. Many previous studies indicated that neglecting mistuning-induced changes aerodynamic forcing and damping would lead erroneous results. To include these effects, natural approach perform fully-coupled multi-passage simulation. However, it apparent this need higher simulation cost. paper we propose an efficient two-scale method simulations. The validity effectiveness of demonstrated case mistuned bladerow. proposed methodology shown one order magnitude faster than baseline fine-mesh simulations, while having similar accuracy.