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TECHNICAL PAPERS

3-D Transonic Flow in a Compressor Cascade With Shock-Induced Corner Stall

[+] Author and Article Information
Anton Weber, Heinz-Adolf Schreiber, Reinhold Fuchs, Wolfgang Steinert

German Aerospace Center (DLR), Institute of Propulsion Technology, 51170 Köln, Germany

J. Turbomach 124(3), 358-366 (Jul 10, 2002) (9 pages) doi:10.1115/1.1460913 History: Received October 02, 2000; Online July 10, 2002
Copyright © 2002 by ASME
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References

Weingold,  H. D., Neubert,  R. J., Behlke,  R. F., and Potter,  G. E., 1997, “Bowed Stators: An Example of CFD Applied to Improve Multistage Compressor Efficiency,” ASME J. Turbomach., 119, pp. 161–168.
Gümmer, V., Wenger, U., and Kau, H. P., 2001, “Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors,” ASME J. Turbomach., 12 , Paper No. 2000-GT-491.
Fottner, L., 1990, “Test Cases for Computation of Internal Flows in Aero Engine Components,” AGARD-AR-275.
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Osborne,  D. J., Ng,  W. F., and Tweedt,  D. L., 1998, “Studies of Secondary Flow at Endwall of a Supersonic Compressor Cascade,” AIAA J., 36, No. 2, pp. 128–133.
Steinert, W., Schreiber, H. A., and Weber, A., 1996, “Experimente am transsonischen Verdichtergitter DLR-TSG-89-5 bei M1=0.90 und M1=1.09,” DLR-IB-325-10-96, DLR Köln, Germany.
Fuchs, R., Steinert, W., and Starken, H., 1993, “Transonic Compressor Rotor Cascade with Boundary-Layer Separation: Experimental and Theoretical Results,” ASME Paper No. 93-GT-12-405.
Weber, A., and Nicke, E., 1997, “A Study of Sweep on the Performance of a Transonic Cascade with and without Endwall Influence,” Proc., 13th Int. Symp. Air Breathing Engines, ISABE, Chattanooga, TN, Vol. 2, pp. 877-888.
Weber, A., Schreiber, H. A., Fuchs, R., and Steinert, W., 2000, “Räumliche Strömungen in transsonischen Verdichtergittern sehr hoher Belastung,” Abschlußbericht zum HTGT-Turbotech Vorhaben 1.131 der Arbeitsgemeinschaft Hochtemperatur-Gasturbine (AG-Turbo), DLR Köln, Germany.
Stark, U., and Bross, S., 1996, “Endwall Boundary Layer Separations and Loss Mechanisms in Two Compressor Cascades of Different Stagger Angle,” AGARD-CP-571, Paper No. 1.
Vogel, D. T., 1994, “Navier-Stokes Calculation of Turbine Flows with Film Cooling,” 19th Congress of the International Council of the Aeronautical Sciences, ICAS-94-12-253.
Vogel, D. T., 1999, “A Simulation Package for Turbomachinery Components,” Proc. First ONERA-DLR Aerospace Symposium, Paris, France.
Kügeler, E., 2000, “Numerische Untersuchung der Filmkühlung aus einer Reihe von Fan-shaped Bohrungen auf der Saugseite einer Turbinenschaufel und Vergleich mit Experimenten,” DGLR Jahrestagung 2000, Leipzig, DGLR-JT2000-139, Bonn, Germany.
Kügeler, E., Weber, A., and Lisiewicz, S., 2001, “Combination of a Transition Model with a Two-Equation Turbulence Model and Comparison with Experimental Results,” Proc. 4th European Turbomachinery Conference, Florence, Italy, Paper No. ATI-CST-076/01.
Eulitz, F., Engel, K., Nürnberger, D., Schmitt, S., and Yamamoto, K., 1998, “On Recent Advances of a Parallel Time-Accurate Navier-Stokes Solver for Unsteady Turbomachinery Flow,” Computational Fluid Dynamics ’98, Proc., 4th ECCOMAS, eds., Papailiou et al., Vol. 1, Part 1, pp. 252–258, John Wiley & Sons, New York, NY.
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Figures

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Test section of DLR transonic cascade wind tunnel
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Schlieren photo at M1=1.09,β1=147.1 deg
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Computational grid (50 percent blade span, skip=2), inlet plane: x/cax=−0.81, outlet plane: x/cax=1.59, and simulated surface iso-Mach contours at test conditions
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Oil streak lines on sidewall (top) and suction surface (bottom, left) and TRACE simulation, M1=1.09,β1=147.1 deg
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Interpretation of oil streak lines
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Achieved overall pressure ratio and midspan total pressure losses for crucial code development steps, M1≅1.09.
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Simulated near-wall streamlines on suction surface and sidewall—bottom left: calculated structure of reverse flow
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Measured and simulated incoming sidewall boundary layer profiles ahead of the cascade at x/cax=−0.25. 3-D-NS simulation: pitchwise averaged, M1=1.09,β1=147.1 deg.
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Isentropic profile Mach number distribution in 4 spanwise cuts. Top: averaged data at midspan; center: near-wall and midspan distributions; bottom: spanwise development in experiment and 3-D simulation.
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Isentropic Mach number. Top: distribution near SS and PS sidewall/corner (full symbols in pressure tap locations); center right: experimental contours from sidewall pressure taps; bottom: 3-D simulation at midspan and sidewall.
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Development of total pressure in streamwise direction and extension of reverse flow region (dotted line), left 3-D simulation, right experiment (Pitot probe)   Fig. 11. Development of secondary velocity in streamwise direction, right-hand side: five-hole probe experiment
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Pitchwise distribution of total pressure and flow angles β and γ inside the blade passage (x/c=0.86) at four spanwise positions. 3-D-simulation compared to experimental data from 5 hole probe (hollow) and extra Pitot readings (solid symbols).
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Spanwise distributions in exit plane at x/cax=1.43, pitchwise averaged. Coarse grid: standard k-ε model with wall functions; fine grid: low Reynolds k-ω model.
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Simulated surface streak lines on blade and sidewall

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