722 遠心翼の振動応答簡易予測手法の検討

概要

論文の詳細を見る
A method for predicting radial inflow turbine forced response is presented. Minding to use easily in design routine, this method does not use unsteady technique (unsteady CFD, structural transient analysis) but only uses established technique (stead state CFD and structural eigenvalue analysis) these are usually used in actual blade design. This method is applied to radial inflow turbine blade of turbo-charger excited by multiple orders of shaft rotational frequencies. In this case, excitation source is assumed to be circumferential non-uniformity of flow caused by the existence of tang in scroll outlet. Predicted responses and these normalized values called as 'Stimulus' are compared to the empirical design curve and published experimental data respectively. Result shows the effectiveness of this method for rough estimation of forced response level in design routine. But at same time, some discrepancies still exists and more improvements will be required for the precise prediction.
一般社団法人日本機械学会の論文
2002-09-13