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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

Camp,  T. R. and Day,  I. J., 1998, “A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor,” ASME J. Turbomach., 120, pp. 393–401.
Mathioudakis, K., and Breugelmans, F. A. E., 1985, “Development of Small Rotating Stall in a Single Stage Axial Compressor,” ASME paper 85-GT-227.
Mongeau, L., 1991, “Experimental Study of the Mechanism of Sound Generation by Rotating Stall in Centrifugal Turbomachines,” Ph.D. dissertation, Pennsylvania State University.
Bent, P. H., McLaughlin, D. K., and Thompson, D. E., 1992, “The Influence of Discharge Configuration on the Generation of Broadband Noise in Centrifugal Turbomachinery,” 14th Aeroacoustics Conference, May 11–14, 1992, Aachen, Germany, DGLR/AIAA 92-02-099.
Mongeau, L., and Quinlan, D. A., 1992, “An Experimental Study of Broadband Noise Sources in Small Axial Fans,” International Symposium on Fan Noise INCE, Senlis, France, Sept. 1–3, 1992.
Kameier, F., 1994, “Experimentelle Untersuchung zur Entstehung und Min- derung des Blattspitzen-Wirbellárms axialer Strömungsmaschinen,” Fortschritt-Berichte VDI Reihe 7 Nr. 243 Düsseldorf, Germany.
Krane, M. H., Bent, B. H., and Quinlan, D. A., 1995, “Rotating Instability Waves as a Noise Source in a Ducted Axial Fan,” ASME Winter Annual Meeting, Turbomachinery Noise Symposium, San Francisco.
Kameier,  F., and Neise,  W., 1997, “Experimental Study of Tip Clearance Losses and Noise Generation in Axial Turbomachines and Their Reduction,” ASME J. Turbomach., 119, pp. 460–471.
März, J., Neuhaus, L., Neise, W., and Gui, X., 1998, “Circumferential Structure of Rotating Instability under Variation of Flow Rate and Solidity,” VDI-Tagung: Turbokompressoren im industriellen Einsatz, Oct. 6–7, Hannover, Germany.
Baumgartner, M., Kameier, F., and Hourmouziadis, J., 1995, “Non-Engine Order Blade Vibration in a High Pressure Compressor,” 12th International Symposium on Airbreathing Engines, Sept. 10–15, Melbourne, Australia.
Witte, H., and Ziegenhagen, S., 1998, “Beurteilung von strömungserregten Schaufelschwingungen eines Flugtriebwerks-Axialverdichters mitteiks statistischer Analysemethoden,” VDI-Tagung: Turbokompressoren in industriellen Einsatz, Oct. 6–7, Hannover, Germany.
Hoying, D. A., Tan, C. S., Huu Duc Vo, and Greitzer, E. M., 1998, “Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception,” ASME paper 98-GT-588.
Inoue, M., Kuroumaru, M., Tanino, T., and Furukawa, M., 1999, “Propagation of Multiple Short Length-Scale Stall Cells in an Axial Compressor Rotor.” ASME paper 99-GT-97.
Boos, P., Möckel, H., Henne, J. M., and Selmeier, R., 1996, “Flow Measurement in a Multistage Large Scale Low Speed Axial Flow Research Compressor,” Proceedings of the 43rd Gasturbine & Aeroengine Technical Congress, Exposition and Users Symposium, June 2–5, Stockholm, Sweden.
Müller, R., Mailach, R., Lehmann, I., and Sauer, H., 1999, “Flow Phenomena Inside the Rotor Blade Passages of Axial Compressors,” AIAA99-IS-084, 14th International Symposium on Airbreathing Engines, Sept. 6–10, Florence, Italy.
Mailach, R., 1999, “Experimental Investigation of Rotating Instabilities in a Low-Speed Research Compressor,” 3rd European Conference on Turbomachinery—Fluid Dynamics and Thermodynamics, March 2–5, London, GB.
Mailach, R., 1999, “Früherkennung rotierender Instabilitäten,” Abschlußbericht zum BMBF-Vorhaben 0327041L, July 1999, Dresden, Germany.
Inoue,  M., Kuroumaru,  M., 1989, “The Structure of Tip Clearance Flow in an Isolated Axial Compressor Rotor,” ASME J. Turbomach., 111, pp. 250–256.
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Figures

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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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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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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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