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High Resolution RANS NLH Study of Stage 67 Tip Injection Physics

[+] Author Affiliations
Allan D. Grosvenor, Gregory S. Rixon, Logan M. Sailer

Ramgen Power Systems, LLC, Bellevue, WA

Michael A. Matheson

Oak Ridge National Laboratory, Oak Ridge, TN

David P. Gutzwiller

Numeca USA, San Francisco, CA

Alain Demeulenaere

NUMECA USA, San Francisco, CA

Mathieu Gontier

Numeca International, Brussels, Belgium

Anthony J. Strazisar

AJS Aero Incorporated, Chesterland, OH

Paper No. GT2014-27219, pp. V02BT39A045; 15 pages
doi:10.1115/GT2014-27219
From:
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 2B: Turbomachinery
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4561-5
  • Copyright © 2014 by ASME

abstract

Numerical prediction of the Stage 67 transonic fan stage employing wall jet tip injection flow control and study of the physical mechanisms leading to stall suppression and stability enhancement afforded by endwall recirculation/injection is the focus of this paper. Reynolds averaged Navier-Stokes computations were used to perform detailed analysis of the Stage 67 configuration experimentally tested at NASA’s Glenn Research Center in 2004. Time varying predictions of the stage plus recirculation and injection flowpath were executed utilizing the Nonlinear Harmonic approach. Significantly higher grid resolution per passage was achieved than what has been generally employed in prior reported numerical studies of spike stall phenomena in transonic compressors. This paper focuses on characterizing the physics of spike stall embryonic stage phenomena and the influence of tip injection, resulting in experimentally and numerically demonstrated stall suppression.

Copyright © 2014 by ASME

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