Influence of blade root fillet and blade tip clearance on the aerodynamic performance of a transonic axial compressor

Through the numerical simulation of the flow field of a single-stage transonic axial compressor a study was conducted of the impact of rotating-blade root fillet and tip clearance on the flow field aerodynamic performance. The results of the study indicate that the blade tip clearance will lead to a flow blockage at the top zone and increase the separation loss at that zone. The blade root fillet will decrease the flow turning angle at the blade root, decrease work-performing capacity and enlarge the blade root separation zone. This will lead to a decrease in flow rate and an increase in separation loss at the root zone. In view of the above, the rotating blade tip clearance and the blade root fillet should be taken into account in order to enhance the accuracy of the numerical simulation.