Effects of Shock Waves on Aerodynamic Instability of Annular Cascade Oscillation in a Transonic Flow

[+] Author and Article Information
H. Kobayashi

National Aerospace Laboratory, Chofu, Tokyo, Japan

J. Turbomach 111(3), 222-230 (Jul 01, 1989) (9 pages) doi:10.1115/1.3262259 History: Received January 04, 1988; Online November 09, 2009


The effects of shock waves on the aerodynamic instability of annular cascade oscillation were examined for rows of both turbine and compressor blades, using a controlled-oscillating annular cascade test facility and a method for accurately measuring time-variant pressures on blade surfaces. The nature of the effects and blade surface extent affected by shock waves were clarified over a wide range of Mach number, reduced frequency, and interblade phase angle. Significant unsteady aerodynamic forces were found generated by shock wave movement, which markedly affected the occurrence of compressor cascade flutter as well as turbine cascade flutter. For the turbine cascade, the interblade phase angle significantly controlled the effect of force, while for the compressor cascade the reduced frequency controlled it. The chordwise extent of blade surface affected by shock movement was estimated to be approximately 6 percent chord length.

Copyright © 1989 by ASME
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