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Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

[+] Author Affiliations
Dale E. Van Zante

NASA Glenn Research Center, Cleveland, OH

Wai-Ming To

AP Solutions, Inc., Cleveland, OH

Jen-Ping Chen

Mississippi State University, Mississippi State, MS

Paper No. GT2002-30575, pp. 969-980; 12 pages
doi:10.1115/GT2002-30575
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2002, Parts A and B
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3610-X | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect of the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

Copyright © 2002 by ASME
Topics: Compressors , Blades

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