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TECHNICAL PAPERS

Analysis of the Interrow Flow Field Within a Transonic Axial Compressor: Part 1—Experimental Investigation

[+] Author and Article Information
Xavier Ottavy, Isabelle Trébinjac, André Vouillarmet

Ecole Centrale de Lyon, Laboratoire de Mécanique des Fluides et d’Acoustique, UMR CNRS 5509/ECL/UCB Lyon I, 69131 Ecully Cedex, France

J. Turbomach 123(1), 49-56 (Feb 01, 2000) (8 pages) doi:10.1115/1.1328085 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Burnes, T., Ottenberger, D. B., and Elliot, M., 1998, “F/A-18 E/F Aircraft Engine (F414-GE-400),” in: Blade Row Interference Effects in Axial Turbomachinery Stages, Von Karman Institute for Fluid Dynamics, LS 1998-02.
Fritsch,  G., and Giles,  M. B., 1995, “An Asymptotic Analysis of Mixing Loss,” ASME J. Turbomach., 117, pp. 367–374.
Wisler, D. C., 1998, “The Technical and Economic Relevance of Understanding Blade Row Interaction Effects in Turbomachinery,” in: Blade Row Interference Effects in Axial Turbomachinery Stages, Von Karman Institute for Fluid Dynamics, LS 1998-02.
Beversdorff,  M., Matziol,  L., and Blaha,  C., 1998, “Application of 3D-Laser Two Focus Velocimetry in Turbomachine Investigations,” AGARD Conf. Proc., 598, pp. 13.1–13.7.
Förster, W., Schodl, R., and Rijmenants, E., 1990, “Design and Experimental Verification of the 3D Velocimeters Based on the L2F Technique,” Proc. 5th International Symposium on Application of Laser Anemometry to Fluid Mechanics, Lisbon.
Tisserand,  D., and Breugelmans,  F. A. E., 1997, “Rotor Blade-to-Blade Measurements Using Particle Image Velocimetry,” ASME J. Turbomach., 119, pp. 176–181.
Wernet,  M. P., 1998, “Demonstration of PIV in a Transonic Compressor,” AGARD Conf. Proc., 598, pp. 51.1–51.13.
Roehle,  I., and Schodl,  R., 1998, “Applications of Three Dimensional Doppler Global Velocimetry to Turbo Machinery and Wind Tunnel Flows,” AGARD Conf. Proc., 598, pp. 52.1–52.10.
Escuret, J. F., Veysseyre, P., Villain, M., Savarese, S., Bois, G., and Navière, H., 1997, “Effect of a Mismatch Between the Buttons of Variable Stator Vanes and the Flow Path in a Highly Loaded Transonic Compressor Stage,” ASME Paper No. 97-GT-471.
Hathaway,  M. D., Chriss,  R. M., Wood,  J. R., and Strazisar,  A. J., 1993, “Experimental and Computational Investigation of the NASA Low Speed Centrifugal Compressor Flow Field,” ASME J. Turbomach., 115, pp. 527–542.
Doukelis, A., Founti, M., Mathioudakis K., and Papailiou, K., 1996, “Evaluation of Beam Refraction Effects in a 3D Laser Doppler Anemometry System for Turbomachinery Applications,” in: Measurement Science and Technology, Vol. 7, pp. 922–931.
Durrett,  R. P., Gould,  R. D., Stevenson,  W. H., and Thompson,  H. D., 1985, “A Correction Lens for Laser Doppler Velocimeter Measurements in a Cylindrical Tube,” AIAA J., 23, No. 9, pp. 1387–1391.
Ottavy,  X., Trébinjac,  I., and Vouillarmet,  A., 1998, “Treatment of L2F Anemometer Measurement Volume Distortions Created by Curved Windows for Turbomachinery Application,” Meas. Sci. Technol., 9, pp. 1511–1521.
Schodl, R., 1986, “Laser Two Focus Velocimetry,” AGARD CP 399 Paper.
Vouillarmet, A., and Trébinjac, I., 1998, “Improvement in L2F Anemometry Technique for Inter-Blade Investigations in High-Speed Turbomachinery,” ASME Paper No. 98-GT-157.
Melling, A., 1986, “Seeding Gas Flows for Laser Anemometry,” AGARD CP 399.

Figures

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Sketch of ECL4 compressor stage
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Schematic arrangement of optical setup
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Optical distortions of a laser cone passing through windows
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Comparison of measured optical depths of field of anemometer with and without windows
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Experimental mesh of surfaces A and B
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Contour maps in section A of the absolute velocity V for four different positions of rotor blade row
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Contour maps in section A of absolute angle α for four different positions of rotor blade row
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Contour maps in section A of velocity standard deviation σV for four different positions of rotor blade row
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Comparison of time-averaged absolute velocity fields obtained in section A with L2F and “three-hole” pressure probe
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Comparison of time-averaged absolute angle fields obtained in section A with L2F and “three-hole” pressure probe
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Contour maps on surface B of the absolute velocity V for four different relative positions of rotor blade row
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Contour maps on surface B of the absolute angle α for four different relative positions of rotor blade row
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Contour maps on surface B of the standard deviation σV for four different relative positions of rotor blade row
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Flow deceleration through shock in section A, for different blade pitch partitions
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Time evolutions of mean absolute velocity and standard deviation at a point located on surface B, in a wake-free region, 5 percent of rotor chord upstream of leading edge of rotor

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