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TECHNICAL PAPERS

Rotating Instabilities in an Axial Compressor Originating From the Fluctuating Blade Tip Vortex

[+] Author and Article Information
R. Mailach, I. Lehmann, K. Vogeler

Dresden University of Technology, 01062 Dresden, Germany

J. Turbomach 123(3), 453-460 (Feb 01, 2000) (8 pages) doi:10.1115/1.1370160 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Relative flow angle in the blade tip region of the rotor blades, nominal tip clearance (s*=1.3 percent), r*=95 percent, design speed, operating point near stability limit (ξ=0.85). Dashed line: expected vortex trajectory
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Pressure difference between PS and SS of a rotor blade vs chord length, s*=4.3 percent,r*=92 percent, design speed
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Axial component of velocity and relative flow angle within the rotor blade tip clearance, large tip clearance (s*=4.3 percent),r*=97.9 percent, design speed, design point (ξ=1.0)
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Axial component of velocity and relative flow angle in the blade tip region of the rotor blades, large tip clearance (s*=4.3 percent),r*=92.0 percent, design speed, design point (ξ=1.0)
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Sectional drawing of Dresden LSRC
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Time-resolving pressure transducers on the PS of rotor blades
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Configuration C1 of microphones at the casing
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Compressor characteristic for design speed
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Frequency spectrum at the casing, design speed, ξ=0.82,s*=4.3 percent
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Propagation of RIs in circumferential direction at the casing wall, axial position at the leading edge of the rotor blades, design speed, ξ=0.82
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Mode orders of RIs design speed, ξ=0.82
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Propagation of RIs at the casing wall and circumferential pressure distribution at profile leading edge, t=const (fixed frame of reference)
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Propagation of RIs in the blade tip region, t=const (relative frame of reference)
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Propagation direction of RIs in the blade tip region, rotating system
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Pressure difference between PS and SS of a rotor blade vs chord length, s*=1.3 percent,r*=92 percent, design speed
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Relative flow angle in the blade tip region of the rotor blades, nominal tip clearance (s*=1.3 percent), r*=95 percent, design speed, design point (ξ=1.0). Dashed line: expected vortex trajectory
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Axial component of velocity and relative flow angle within the rotor blade tip clearance, large tip clearance (s*=4.3 percent), r*=97.9 percent, design speed, operating point near stability limit (ξ=0.85)
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Axial component of velocity and relative flow angle in the blade tip region of the rotor blades, large tip clearance (s*=4.3 percent), r*=92.0 percent, design speed, operating point near stability limit (ξ=0.85)
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Blockage in the blade tip region induced by the blade tip vortex, large tip clearance (s*=4.3 percent)
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Periodical influence of stator wakes on the pressure difference between PS and SS of a rotor blade (s*=4.3 percent),r*=92 percent, 10 percent chord, design speed, design point
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Pressure difference between PS and SS of a rotor blade, s*=4.3 percent,r*=92 percent, design speed, operating point near stability limit (ξ=0.83), sensors at nearly the same axial position: 20 percent chord at PS, 30 percent chord at SS
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Fluctuation of tip vortex along the blade chord, frequency spectrum of the difference of the pressure differences between PS and SS near the leading edge (10 percent chord) and the rear part (60 percent chord) of a rotor blade, r*=92 percent),s*=4.3 percent, design speed, operating point near stability limit (ξ=0.83)
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Time-dependent development of blade tip vortex, rotating system
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Blade tip vortices at different times, rotating system

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