Investigation of the Unsteady Rotor Aerodynamics in a Transonic Turbine Stage

[+] Author and Article Information
R. Dénos, T. Arts, G. Paniagua

Von Karman Institute for Fluid Dynamics, Rhode Saint Genèse, Belgium

V. Michelassi

Department of Mechanical and Industrial Engineering, University of Rome, Tre, Italy

F. Martelli

Energetics Department “Sergio Stecco,” University of Florence, Florence, Italy

J. Turbomach 123(1), 81-89 (Feb 01, 2000) (9 pages) doi:10.1115/1.1314607 History: Received February 01, 2000
Copyright © 2001 by ASME
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Grahic Jump Location
Rotor/stator position at phase 0; schematic of the vane shock and wake system for a stator–rotor spacing of 0.35 cs,ax
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Phase-locked average and rms of the measured rotor relative inlet total pressure: influence of trailing edge coolant ejection
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Computed isentropic Mach number distribution on the vane (6500 rpm, 0.35 cs,ax,mc=3 percent)
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Computed rotor inlet flow angle
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Influence of: (a) rotational speed (0.35 cs,ax,ṁc=3 percent), and (b) stator–rotor spacing (6500 rpm, mc=3 percent) on measured relative inlet total pressure fluctuations
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Time-averaged values of measured and computed rotor blade pressure (0.35 cs,ax,ṁc=3 percent)
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Pressure fluctuations from measurements and computations (6500 rpm, 0.35 cs,ax,ṁc=3 percent): (a) gages 5–13, (b) gages 15–4, (c) gages 24–16
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Computed shock function in the stage with schematic of expansion waves (blue lines) and compression waves (red lines); the phases of rotor blades 2, 3, 4, and 5 are 0.17, 0.83, 0.49, and 0.17, respectively
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Schematic showing the vane trailing edge shock as it sweeps the blade front suction side
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(a) Minimum, maximum of mean period; (b) time-averaged rms; and (c) correlation coefficient of the experimental pressure traces for spacings 0.35 cs,ax and 0.50 cs,ax (6500 rpm, ṁc=3 percent)
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The rms traces (6500 rpm, 0.35 cs,ax,ṁc=3 percent) in the blade nose region; propagation directions at v,v+a,v−a for a perturbation injected at point 14 at φ=0.15
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Unsteady blade force modulus and angle (0.35 cs,ax,ṁc=3 percent) from experiments at 6000, 6500, and 6800 rpm and computations at 6500 rpm
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Unsteady velocity and static pressure field in the rotor passage



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