抄録
In the flow of a transonic compressor, shock waves occur around blades and cause instabilities. The present research investigates the instabilities caused by the shock waves. Four blades were designed with changing the blade leading edge in order to investigate the effect of the blade geometry on the two-dimensional supersonic flow of the blade row. The numerical calculation were carried out for various pressure ratios and circumferential speed ratios. The location of the shock wave in the blade passage are determined by the pressure ratio. The blade without the camber angle can obtain the high pressure ratio, but cannot operate in the wide-range condition. Compared to the original blade, the blade with the thin leading edge can operate in the higher mass flow rate.
