503 ノズル励振によるラジアルタービン翼の振動応答予測(翼振動・羽根車,OS-4 ロータダイナミクス)

概要

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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 (steady 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 nozzle wake. Predicted responses are compared to the experimental data and predicted value based on unsteady CFD 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
2004-09-27