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TECHNICAL PAPERS

The Effects of Wake-Passing Unsteadiness Over a Highly Loaded Compressor-Like Flat Plate

[+] Author and Article Information
Xavier Ottavy, Stephane Vilmin, Howard Hodson

Whittle Laboratory, Cambridge University, Trumpington Street, Cambridge CB2 1PZ, UK

Simon Gallimore

Rolls-Royce plc, Moor Lane, Derby DE24 8BJ, UK

J. Turbomach 126(1), 13-23 (Mar 26, 2004) (11 pages) doi:10.1115/1.1643384 History: Received December 01, 2001; Revised March 01, 2002; Online March 26, 2004
Copyright © 2004 by ASME
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References

Schulte,  V., and Hodson,  H. P., 1998, “Prediction of the Becalmed Region for LP Turbine Profile Design,” ASME J. Turbomach., 120, pp. 839–845.
Howell, R. J., Hodson, H. P., Schulte, V., Schiffer, H.-P., Haselbach, F., and Harvey, N. W., 2001, “Boundary Layer Development in the BR710 and BR715 LP Turbines—The Implementation of High Lift and Ultra High Lift Concepts,” ASME Paper 2001-GT-0441.
Halstead, D. E., Wisler, D. C., Okiishi, T. H., Walker, G. J., Hodson, H. P., and Shin, H., 1995, “Boundary Layer Development in Axial Compressors and Turbines Part 1 of 4: Composite Picture,” ASME Paper 95-GT-461.
Schulte, V., and Hodson, H. P., 1996, “Unsteady Wake-Induced Boundary Layer Transition in High Lift LP Turbines,” ASME Paper 96-GT-486.
Howell, R. J., 1999, “Wake—Separation Bubble Interactions in Low Reynolds Number Turbomachinery,” Ph.D. dissertation, Cambridge University, Cambridge, UK.
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Mayle, R. E., 1991, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines,” ASME Paper 91-GT-261.
Emmons,  H. W., 1951, “The Laminar-Turbulent Transition in a Boundary Layer—Part 1,” J. Aerosp. Sci., 18(7), pp. 490–498.
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Figures

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Tested velocity distributions
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View of the “wood box” with the plate and the polystyrene walls
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View of the two-dimensional mesh. 6156 nodes.
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Measured and simulated steady flow for shape 02, Re=350,000 PS means pressure side, SS means suction side
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Experimental Cp distributions with incoming wakes for Re=350,000 and Re=500,000—shape 02
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Hot film data, nondimensional quasi shear stress on the plate—Re=350,000 and fred=0.75—shape 02
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Hot-film data, nondimensional quasi shear stress on the plate—Re=350,000 and fred=1.5—shape 02
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Boundary layer velocity profile as a function of time—Re=350,000—fred=0.75 and fred=1.5—shape 02
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Hot-wire data at 97.5% of Smax. Re=350,000 and fred=0.75—shape 02. Left: variance; center: evolution of displacement thickness (black) and momentum thickness (gray) for two wake periods; right: shape factor.
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Hot-wire data at 97.5% of Smax. Re=350,000 and fred=1.50—shape 02. Left: variance; center: evolution of displacement thickness (black) and momentum thickness (gray) for two wake periods; right: shape factor.
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Measured and predicted flow with forced transition at 10% Smax, Re=350,000—shape 02
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Summary of the experimental results. Left: results in terms of loss and lift; right: results in terms of loss and local diffusion factor (D). 1, 2, 3, 4 for shapes 01, 02, 03, 04, ★ for shape 02 “highly loaded” with Re=350,000 and fred=1.5.

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