Numerical Flow Analysis in a Subsonic Vaned Radial Diffuser With Leading Edge Redesign

[+] Author and Article Information
E. Casartelli, A. P. Saxer, G. Gyarmathy

Turbomachinery Laboratory, Institute of Energy Technology, Swiss Federal Institute of Technology, 8092 Zurich, Switzerland

J. Turbomach 121(1), 119-126 (Jan 01, 1999) (8 pages) doi:10.1115/1.2841219 History: Received February 01, 1997; Online January 29, 2008


The flow field in a subsonic vaned radial diffuser of a single-stage centrifugal compressor is numerically investigated using a three-dimensional Navier–Stokes solver (TASCflow) and a two-dimensional analysis and inverse-design software package (MISES). The vane geometry is modified in the leading edge area (two-dimensional blade shaping) using MISES, without changing the diffuser throughflow characteristics. An analysis of the two-dimensional and three-dimensional effects of two redesigns on the flow in each of the diffuser subcomponents is performed in terms of static pressure recovery, total pressure loss production, and secondary flow reduction. The computed characteristic lines are compared with measurements, which confirm the improvement obtained by the leading edge redesign in terms of increased pressure rise and operating range.

Copyright © 1999 by The American Society of Mechanical Engineers
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