Effect of Rotor Tip Geometry on Axial Compressor Performance

Abstract

Experiments were conducted to investigate the characteristics of a low-speed 1.5-stage axial compressor under conditions where the blade tip clearance is large and using two different types of blades．The kink point that occurred in the blade total pressure rise characteristic moved to the lower flow rate，and the performance was confirmed to be improved by using modified rotor with an open inlet metal angle．Modified rotor had the effect of improving the flow field inside the rotor blade and delaying the occurring flow rate of rotating instability．On the other hand，at low flow rates，the diffusion factor at the blade tips was increased．These results suggest that opening the inlet metal angle has a positive effect in the high flow rate but has the effect of reducing the stall margin in the low flow rate．