The design and optimization of a multistage radial compressor vaneless diffuser, cross-over and return channel is presented. An analytical design procedure for 3D blades with prescribed load distribution is first described and illustrated by the design of a 3D return channel vane with leading edge upstream of the cross-over. The analysis by means of a 3D Navier–Stokes solver shows a substantial improvement of the return channel performance in comparison with a classical 2D channel. Most of the flow separation inside and downstream of the cross-over could be avoided in this new design. The geometry is further improved by means of a 3D inverse design method to smooth the Mach number distribution along the vanes at hub and shroud. The Navier–Stokes analysis shows a rather modest impact on performance but the calculated velocity distribution indicates a more uniform flow and hence a larger operating range can be expected. The impact of vane lean on secondary flows is investigated and further performance improvements have been obtained with negative lean.
Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor
Contributed by the Fluids Engineering Division for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received by the Fluids Engineering Division October 14, 2002; revised manuscript received April 29, 2004. Associate Editor: B. Schiavello.
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Veress, A., and Van den Braembussche, R. (December 7, 2004). "Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor ." ASME. J. Fluids Eng. September 2004; 126(5): 799–806. https://doi.org/10.1115/1.1792258
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