摘要：This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial *** experiment is carried out in a single-stage large-scale low-speed *** investigated tip geometries include flat tip as the baseline and suction side squealer *** tip clearance of the baseline is 0.5% of the blade *** static pressure rise characteristic curves of both the rotor and the stage are *** flow field at the exit of the rotor is measured by a 5-hole probe under design and off-design *** static pressure on the endwall of the rotor passage is also *** results show that the pressure rise characteristic curves obtained by measuring the pressure on the end wall are almost unchanged by using the suction side squealer *** measuring results of the 5-hole probe show the static pressure and the total pressure in tip region is slightly greater than that of the flat tip at the design condition at the exit of the *** also leads to greater av-eraged static pressure rise and total *** the near stall condition,the averaged static pressure and total pressure is lower than the baseline which is related to the redistribution of the blade load caused by the suction side squealer tip.