Analysis of Tip Leakage Effects in a High Subsonic Annular Compressor Cascade PUBLIC ACCESS

[+] Author Affiliations
C. Bonhommet-Chabanel

SNECMA, France

G. A. Gerolymos

Université Pierre-et-Marie-Curie, Paris, France

Paper No. 98-GT-195, pp. V001T01A050; 10 pages
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7862-0
  • Copyright © 1998 by ASME


This paper presents both experimental and numerical results of tip leakage effects in a High Speed Annular Cascade. The influence of the clearance size has been investigated. For validation purposes and a better understanding of the 3-D phenomena, a comparison of the measurements with three-dimensional Navier-Stokes computations using a k-ε closure with a low-Reynolds approach has been performed.

The high speed annular cascade facility has been specifically designed for studying tip leakage flows at the rear of high pressure compressors. In the vicinity of the clearance, the inlet swirl angle, created by a scroll, is of 60° from the axial direction and the Mach number is about 0.60. The blades are cantilevered (fixed on the casing with a clearance gap at the rotating inner wall). In order to obtain a picture of the flow field as complete as possible, different kinds of measurements have been used. 3D velocity measurements within the blade passages have been performed by means of a 3-D Laser Doppler Anemometer system. Furthermore, a five-hole probe with long stem was also used in the blade passage.

The experimental data are quite detailed and self-consistent. A leakage vortex can clearly be identified and, within the blade passage, seems to be responsible for a region of overturning above it. The clearance size has a direct impact on the inception point of the phenomena and on the direction and strength of the leakage vortex. The calculation was found to reproduce the same trends as the experiment and give good quantitative comparisons, although it overestimates the leakage effect at blade exit.

Copyright © 1998 by ASME
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