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TECHNICAL PAPERS

Pressure Surface Separations in Low-Pressure Turbines—Part 2: Interactions With the Secondary Flow

[+] Author and Article Information
Michael J. Brear, Howard P. Hodson

Whittle Laboratory, Cambridge University, Cambridge, UK

Paloma Gonzalez

Industria de Turbo Propulsores, S.A., Madrid, Spaine-mail: paloma.gonzalez@itp.es

Neil W. Harvey

Rolls-Royce, plc, Derby, UKe-mail: neil.harvey@rolls-royce.com

J. Turbomach 124(3), 402-409 (Jul 10, 2002) (8 pages) doi:10.1115/1.1450765 History: Received October 20, 2000; Online July 10, 2002
Copyright © 2002 by ASME
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References

Brear,  M. J., Hodson,  H. P., and Harvey,  N. W., 2001, “Pressure Surface Separations in Low-Pressure Turbines—Part 1: Midspan Behavior,” ASME J. Turbomach., 124, pp. –.
Hodson,  H. P., and Dominy,  R. G., 1987, “Three-Dimensional Flow in a Low-Pressure Turbine Cascade at Its Design Condition,” ASME J. Turbomach., 109, pp. 177–185.
Hodson,  H. P., and Dominy,  R. G., 1987, “The off-design performance of a low-pressure turbine cascade,” ASME J. Turbomach., 109, pp. 201–209.
Yamamoto, A., Tominaga, J., Matsunuma, T., and Outa E., 1994, “Detailed Measurements of Three-Dimensional Flows and Losses Inside an Axial Turbine Rotor,” ASME Paper No. 94-GT-348.
Curtis,  E. M., Hodson,  H. P., Banieghbal,  M. R., Denton,  J. D., Howell,  R. J., and Harvey,  N. W., 1996, “Development of Blade Profiles for Low Pressure Turbine Applications,” ASME J. Turbomach., 119, pp. 531–538.
Brear, M. J., 2000, “Pressure surface separations in low pressure turbines,” Ph. D dissertation, Cambridge University, Cambridge, UK.
Dominy,  R. G., and Hodson,  H. P., 1993, “An investigation of factors influencing the calibration of five-hole probes for three-dimensional flow measurements,” ASME J. Turbomach., 115, pp. 513–519.
Langston,  L., and Boyle,  M. T., 1982, “A New Surface-Streamline Flow-Visualisation Technique,” J. Fluid Mech., 125, pp. 53–57.
Denton,  J. D., 1992, “The Calculation of Three-Dimensional Viscous Flow Through Multistage Turbomachines,” ASME J. Turbomach., 114, pp. 18–26.
Hildebrant,  T., and Fottner,  L., 1999, “A Numerical Study of the Influence of Grid Refinement and Turbulence Modelling on the Flow Field Inside a Highly Loaded Turbine Cascade,” ASME J. Turbomach., 121, pp. 709–716.
Duden,  A., Raab,  I., and Fottner,  L., 1998, “Controlling the Secondary Flow in a Turbine Cascade by 3-D Airfoil Design and Endwall Contouring,” ASME J. Turbomach., 121, pp. 191–199.
Halstead,  D. E., Wisler,  D. C., Okiishi,  T. H., Walker,  G. J., Hodson,  H. P., and Shin,  H. W., 1997, “Boundary Layer Development in Axial Flow Compressors and Turbines—Part 3: LP turbines,” ASME J. Turbomach., 119, pp. 225–237.
Denton,  J. D., 1993, “Loss Mechanisms in Turbomachines,” ASME J. Turbomach., 115, pp. 621–656.
Weiss,  A. P., and Fottner,  L., 1995, “The Influence of Load Distribution on Secondary Flow in Straight Turbine Cascades,” ASME J. Turbomach., 117, pp. 133–141.

Figures

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Endwall and sectional profiles of blades A, B, C, and D
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Predicted streamlines at midspan for blades A and D
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Pitchwise mass-averaged (a) stagnation pressure loss (experiment), (b) stagnation pressure loss (predicted), (c) exit yaw angle (experiment), and (d) exit yaw angle (predicted) for blades A, B, C, and D at 125 percent Cx
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Contours of loss coefficient (Y) at 125 percent Cx for (a) blade A (experiment), (b) blade A (predicted), (c) blade D (experiment), and (d) blade D (predicted) (contour level=0.025)
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Schematic of the regions defined in the entropy generation rate analysis
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Predicted dissipation coefficient for 0 to 10 percent span on blades A and D
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Experimental flow visualization on the pressure surfaces of blades A and D
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Predicted flow on the pressure surfaces of blades A, B, C, and D
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Experimental flow visualization on the endwalls of blades A and D
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Predicted flow on the endwalls of blades A, B, C, and D
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Experimental flow visualization on the suction surfaces of blades A and D
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Predicted streamlines close to the endwall on blade A
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Experimental and predicted isentropic velocity distributions of blades A, B, C, and D at (a) midspan, and (b) 1 percent span

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