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Performance Test Diagnosis of a Compact Two Stage High Pressure Ratio Compressor

[+] Author Affiliations
C. Rodgers

Inventive Turbomachinery Consultant, San Diego, CA

D. Brown

Brown Turbo Consulting, Lebanon, NH

Paper No. GT2010-22038, pp. 1677-1685; 9 pages
doi:10.1115/GT2010-22038
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

The intent of this paper was to resolve significant performance shortfalls encountered during the development of a small two stage research 15.0:1 centrifugal compressor designed fabricated and tested in the late 1990’s. The emphasis of the research project was on the aerodynamic flowpath that eliminates use of a large external diameter radial cross-over duct. This was achieved with an innovative small diameter “Sbend” crossover duct, using computational fluid dynamic (CFD) tools of the later 1990’s era to assist in the design process. Test results revealed major performance shortfalls stemming from limited efficient operating ranges of both the 1st stage mixed flow impeller and mixed flow diffuser, which precipitated stage mismatching consequently confining both 1st stage components to operate in semi-stalled modes. The performance of the conventional 2nd stage centrifugal compressor however met design expectations. Eventually program cost limitations curtailed further testing and intended supplementary CFD analyses of the performance deficiencies with more refined computational techniques. During the elapsed decade turbomachinery CFD codes have been extensively refined prompting this renewed diagnosis of the 1st stage mixed flow impeller, mixed flow diffuser and Sbend duct as described within.

Copyright © 2010 by ASME

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