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
Your Session has timed out. Please sign back in to continue.


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.
Dunham, J., 1998, “CFD Validation for Propulsion System Components,” AGARD-AR-355.
Kang, S., and Hirsch, Ch., 1991, “Three Dimensional Flow in a Linear Compressor Cascade at Design Conditions,” ASME Paper No. 91-GT-114, Orlando, FL.
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.
Yamamoto, K., and Engel, K., 1997, “Multiblock Grid Generation Using an Elliptic Differential Equation,” AIAA Paper No. 97-0201, 35th Aerospace Sciences Meeting & Exhibit, Reno, NV.
Hah,  C., and Loellbach,  J., 1999, “Development of Hub Corner Stall and Its Influence on the Performance of Axial Compressor Blade Rows,” ASME J. Turbomach., 121, pp. 67–77.
Schulz, H. D., Gallus, H. E., and Lakshminarayana, B., 1989, “Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction—Part I: Quasi-Steady Flow Field and Comparison with Steady-State Data,” ASME Paper No. 89-GT-76.
Weber, A., Steinert, W., Fuchs, R., and Schreiber, H. A., 1999, “3D Flow in a Transonic Compressor Cascade (DLR TSG-97),” DLR-IB-325-06-99.


Grahic Jump Location
Test section of DLR transonic cascade wind tunnel
Grahic Jump Location
Schlieren photo at M1=1.09,β1=147.1 deg
Grahic Jump Location
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
Grahic Jump Location
Oil streak lines on sidewall (top) and suction surface (bottom, left) and TRACE simulation, M1=1.09,β1=147.1 deg
Grahic Jump Location
Interpretation of oil streak lines
Grahic Jump Location
Achieved overall pressure ratio and midspan total pressure losses for crucial code development steps, M1≅1.09.
Grahic Jump Location
Simulated near-wall streamlines on suction surface and sidewall—bottom left: calculated structure of reverse flow
Grahic Jump Location
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.
Grahic Jump Location
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.
Grahic Jump Location
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.
Grahic Jump Location
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
Grahic Jump Location
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).
Grahic Jump Location
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.
Grahic Jump Location
Simulated surface streak lines on blade and sidewall




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In