In this paper the three-dimensional inverse design code TURBOdesign-1 is applied to the design of the blade geometry of a centrifugal compressor impeller with splitter blades. In the design of conventional impellers the splitter blades normally have the same geometry as the full blades and are placed at mid-pitch location between the two full blades, which can usually result in a mismatch between the flow angle and blade angles at the splitter leading edge. In the inverse design method the splitter and full blade geometry is computed independently for a specified distribution of blade loading on the splitter and full blades. In this paper the basic design methodology is outlined and then the flow in the conventional and inverse designed impeller is compared in detail by using computational fluid dynamics (CFD) code TASCflow. The CFD results confirm that the inverse design impeller has a more uniform exit flow, better control of tip leakage flow and higher efficiency than the conventional impeller. The results also show that the shape of the trailing edge geometry has a very appreciable effect on the impeller Euler head and this must be accurately modeled in all CFD computations to ensure closer match between CFD and experimental results. Detailed measurements are presented in part II of the paper.
Investigation of an Inversely Designed Centrifugal Compressor Stage—Part I: Design and Numerical Verification
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38531. Review Chair: H. R. Simmons.
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Zangeneh, M., Schleer, M., Pløger, F., Hong, S. S., Roduner, C., Ribi, B., and Abhari, R. S. (March 26, 2004). "Investigation of an Inversely Designed Centrifugal Compressor Stage—Part I: Design and Numerical Verification ." ASME. J. Turbomach. January 2004; 126(1): 73–81. https://doi.org/10.1115/1.1645868
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