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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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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Simulated near-wall streamlines on suction surface and sidewall—bottom left: calculated structure of reverse flow
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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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