Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part II — Unsteady Flow and Pressure Field PUBLIC ACCESS

[+] Author Affiliations
H. D. Schulz, H. E. Gallus, B. Lakshminarayana

RWTH Aachen, Aachen, Federal Republic of Germany

Paper No. 89-GT-77, pp. V001T01A044; 11 pages
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME


An experimental study of the unsteady three-dimensional flow and pressure field in an annular compressor cascade with an upstream rotor has been carried out at several incidences to the stator blade. The distribution of the unsteady pressures at the blade surfaces are measured using fast response Kulite sensors. The unsteady blade boundary layers and the passage flow is measured with a hot wire sensor. Detailed interpretation of the magnitude of unsteady pressures, phase angle differences, unsteady blade boundary layers, wake transport through the stator passage is presented and analyzed in the paper. The unsteady pressures are found to be dominant near the blade leading edge. Substantially higher pressure fluctuations occur in this region as well as on the edge of the corner flow separation region.

Copyright © 1989 by ASME
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