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RESEARCH PAPERS

Periodic Transition on an Axial Compressor Stator: Incidence and Clocking Effects: Part I—Experimental Data

[+] Author and Article Information
G. J. Walker, J. D. Hughes

School of Engineering, University of Tasmania, Hobart, Australia

W. J. Solomon

Ohio Aerospace Institute/General Electric Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 121(3), 398-407 (Jul 01, 1999) (10 pages) doi:10.1115/1.2841332 History: Received February 01, 1998; Online January 29, 2008

Abstract

Periodic wake-induced transition on the outlet stator of a 1.5-stage axial compressor is examined using hot-film arrays on both the suction and pressure surfaces. The time-mean surface pressure distribution is varied by changing the blade incidence, while the free-stream disturbance field is altered by clocking of the stator relative to an inlet guide vane row. Ensemble-averaged plots of turbulent intermittency and relaxation factor (extent of calmed flow following the passage of a turbulent spot) are presented. These show the strength of periodic wake-induced transition phenomena to be significantly influenced by both incidence and clocking effects. The nature and extent of transition by other modes (natural, bypass, and separated flow transition) are altered accordingly. Leading edge and midchord separation bubbles are affected in a characteristically different manner by changing free-stream periodicity. There are noticeable differences between suction and pressure surface transition behavior, particularly as regards the strength and extent of calming. In Part II of this paper, the transition onset observations from the compressor stator are used to evaluate the quasi-steady application of conventional transition correlations to predict unsteady transition onset on the blading of an embedded axial compressor stage.

Copyright © 1999 by The American Society of Mechanical Engineers
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