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TECHNICAL PAPERS

1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part II: Experimental and Theoretical Analysis

[+] Author and Article Information
Bernhard Küsters, Heinz-Adolf Schreiber

German Aerospace Center, Institute of Propulsion Technology, D-51170 Köln, Germany

Ulf Köller, Reinhard Mönig

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

J. Turbomach 122(3), 406-414 (Feb 01, 1999) (9 pages) doi:10.1115/1.1302321 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Experimental and numerical design Mach number distributions of the four test cascades
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Cross section of the DLR Transonic Cascade Tunnel
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Photograph of the test section
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Predicted performance at different Reynolds numbers, cascade C
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Experimental (shaded area) and calculated (solid line) suction side transition onset for the profile shown in Fig. 14
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Suction side transition visualized by liquid crystals, influence of turbulence level at Re=2×106
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Calculated adiabatic wall temperature on suction side and corresponding isentropic Mach number distribution
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Oil streak lines on the suction side of cascade D,i=+9 deg, flow direction from top to bottom
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Numerical separation behavior of cascade D, including MISES separation onset
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Experimental performance data compared to MISES and Navier–Stokes calculations, cascade B,M1=0.607, AVDR=1.05
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Experimental and numerical Mach number distributions of test cascade D
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Loss over incidence at design Mach number, experimental and MISES data, Re=0.9–0.7×106,Tu≤1 percent, experimental and design (in brackets) flow angle range
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Boundary layer form factor at different Reynolds numbers, cascade C,M1=0.556,β1=147.3 deg
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Boundary layer thickness at different Reynolds numbers, cascade C,M1=0.556,β1=147.3 deg
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Isentropic Mach number distribution at different Reynolds numbers, cascade C

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