Periodic Transition on an Axial Compressor Stator — Incidence and Clocking Effects: Part II — Transition Onset Predictions PUBLIC ACCESS

[+] Author Affiliations
W. J. Solomon

Ohio Aerospace Institute/General Electric Aircraft Engines, Cincinnati, OH

G. J. Walker, J. D. Hughes

University of Tasmania, Hobart, Australia

Paper No. 98-GT-364, pp. V001T01A091; 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


Transition onset observations from a 1.5-stage axial compressor outlet stator presented in Part 1 of this paper are compared with the predictions of conventional transition correlations applied in a quasi-steady manner.

The viscous/inviscid interaction code MISES is used to predict the blade surface pressure distributions and boundary layer development. The temporal variation in transition onset is then predicted using ensemble-averaged freestream turbulence data from the compressor measurements. This simple procedure captures most significant features of the complex transition process on the compressor, and is clearly superior to fixed transition models based on long-term average freestream turbulence levels.

Parallel computations for both natural and bypass transition modes indicate that the natural transition mode tends to dominate on the compressor. This is at variance with turbine airfoil experience, where bypass transition is clearly more important.

Comparison of prediction and experiment highlights the significance of leading edge potential flow interactions in promoting periodic wake-induced transition. Viscous/inviscid interactions in the neighborhood of transition can also have an important influence on boundary layer stability and separation phenomena.

Copyright © 1998 by ASME
Topics: Compressors , Stators
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