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TECHNICAL PAPERS

Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade

[+] Author and Article Information
Heinz-Adolf Schreiber, Wolfgang Steinert

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

Bernhard Küsters

Siemens AG, Power Generation (KWU), 45466 Mülheim a.d. Ruhr, Germany

J. Turbomach 124(1), 1-9 (Feb 01, 2000) (9 pages) doi:10.1115/1.1413471 History: Received February 01, 2000
Copyright © 2002 by ASME
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References

Figures

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Typical blade chord Reynolds number of a heavy-duty gas turbine compressor
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Influence of Reynolds number and free-stream turbulence on suction side transition onset (MISES simulation)
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Acceleration parameter for suction and pressure side for two different Reynolds numbers
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Test section of the DLR Transonic Cascade Tunnel
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Photograph of cascade and endwalls
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Oil streak lines on suction side, M1=0.6,Re=0.8×106
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Mach number distribution and oil streak lines at Re=0.7×106 and Tu≈2.5–3 percent, 1 tick approximately 10 percent of chord
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Mach number distribution and oil streak lines at Re=2.1×106 and Tu≈3 percent, 1 tick approximately 10 percent of chord
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Predicted blade Mach number distribution and calculated adiabatic wall temperature on suction side
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Simulated surface temperature distribution on blade suction side, influence of free-stream turbulence on temperature discontinuity near transition for M1=0.6 and Re=2.6×106
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Mach number distribution and liquid crystal picture of suction side at Re=0.9×106 and Tu≈0.7 percent showing laminar separation and turbulent reattachment
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Mach number distribution and liquid crystal picture of suction surface at Re=2.2×106 and Tu≈0.7 percent (no screen)
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Mach number distribution and liquid crystal picture of suction surface at Re=2.0×106 and Tu≈2.5–3 percent (screen 1.9)
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Liquid crystal picture of suction surface at Re=2.0×106 and Tu≈3–3.5 percent (screen 1.9+4)
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Liquid crystal picture of suction surface at Re≈2.0×106 and Tu≈4–5 percent (screen 2.6)
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Liquid crystal picture of suction surface at M1=0.7,Re=3.1×106 and Tu≈3–3.5 percent
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Experimental (shaded area) and predicted (solid line) suction side transition onset at Re=2×106
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Momentum thickness Reynolds number Reθ calculated for three different roughness heights in comparison to Reθ transition (dashed line from 20) against the roughness parameter θ/kS

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