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Flow Ranges of 8.0:1 Pressure Ratio Centrifugal Compressors for Aviation Applications

[+] Author Affiliations
C. Rodgers

ITC, San Diego, CA

Paper No. GT2005-68041, pp. 801-811; 11 pages
doi:10.1115/GT2005-68041
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

A treatise encompassing aerodynamic design features, which are conducive to the flow range extension of 8.0:1 pressure ratio centrifugal compressors for aviation applications, is presented. To support the analyses the flow ranges and characteristics of several existing gas turbine aviation type centrifugal compressors are reviewed, and their design specific speed selection corroborated with aero-thermodynamic cycle performance computations. Critical design parameters are identified which promotes increased flow range between compressor surge and choke based upon inducer and diffuser choke margins in lieu of traditional incidence criteria. No singularly dominant parameter is however identified as a key range extension guarantee. Although the individual component flow range characteristics and critical compressor design parameters discussed promote range extension, they provide only a partial insight to the affirmative resolution of flow range versus operating efficiency related dilemmas.

Copyright © 2005 by ASME

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