A numerical study of the effects of blade angle distribution on the performance and loss generation of centrifugal compressor impellers

The blade angle distribution from the inlet to outlet of an impeller in a centrifugal compressor is known to have significant influence on its flow characteristics. With the aim of understanding the effect of the blade angle distribution, particularly on performance, loss generation, and operating range, four different blade angle distributions were defined with fixed inlet and outlet blade angles, and numerical calculations were conducted over their whole operating ranges, as defined by their stall points and choke conditions. The impeller blade Blade80, which has the smallest variation of blade angle and is relatively radial, was found to exhibit the smallest wall skin friction loss due to its small surface area but the highest blade loading loss. Further, the flow separation near the hub at the suction side and the tip and resulting energy loss give rise to the smallest stall margin of the blades. In contrast, Blade110, which has the largest variation of blade angle, exhibits the largest wall skin friction and hub-to-shroud loading losses but the lowest blade loading loss because the flow from the inlet to the outlet is well guided. As the flow coefficient increases, the performance of Blade110 steeply decreases. The poor performance of Blade110 at high mass flowrates can be explained in terms of flow blockage at the narrow throat. An attempt is made to explain the relationships between the blade angle distributions and the flow characteristics, loss generation, and performance of these impellers.