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Cavity and Protrusion Effects in a Single-Stage Compressor

[+] Author Affiliations
A. A. J. Demargne, J. P. Longley

University of Cambridge

Paper No. 2001-GT-0433, pp. V001T03A055; 8 pages
doi:10.1115/2001-GT-0433
From:
  • ASME Turbo Expo 2001: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • New Orleans, Louisiana, USA, June 4–7, 2001
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7850-7
  • Copyright © 2001 by ASME

abstract

The effect of opening a stator-shroud cavity to the mainstream (no net leakage), upstream of a moderately loaded stator is investigated in a single-stage research compressor.

The investigations consist of a series of measurements and calculations, which reveal various inconsistencies in flow turning, secondary flow and blockage. CFD analysis is used as a diagnostic tool to show that the unexpected trends measured in the single-stage compressor can be attributed to the protrusion of the arrangement used to seal the cavity into the mainstream, disrupting the hub endwall flow into the stator passage.

The CFD results on the single-stage compressor without protrusion confirm the trends observed in the linear cascade experiment relative to the effects of the upstream shroud cavity on the hub endwall flow and stator performance, in the presence of the stator blade pressure field. These results clearly illustrate the strong sensitivity of the performance of the stator row to small protrusions and cavities in the endwalls. Such effects are no longer negligible when compared to the level of resolution and sophistication achieved with current solvers.

Copyright © 2001 by ASME
Topics: Compressors , Cavities

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