This paper describes the redesign of the HP turbine of the Rolls-Royce Trent 500 engine, making use of nonaxisymmetric end walls. The original, datum turbine used conventional axisymmetric end walls, while the vane and (shrouded) rotor aerofoil profiles were nominally the same for the two designs. Previous research on the large-scale, low-speed linear cascade at Durham University (see Hartland et al., 1998, “Non-Axisymmetric End Wall Profiling in a Turbine Cascade,” ASME 98–GT-525), had already demonstrated significant potential for reducing turbine secondary losses using nonaxisymmetric end walls-by about one third. This paper shows how a methodology was derived from the results of this research and applied to the design of the single-stage Trent 500-HP turbine (model rig). In particular, the application of a new linear design system for the parametric definition of these end wall shapes (described in Harvey et al., 1999, “Non-Axisymmetric Turbine End Wall Design: Part I Three-Dimensional Linear Design System,” ASME 99–GT-337) is discussed in detail.

Issue Section:
Technical Papers
Keywords:
gas turbines, design engineering, aircraft, boundary layer turbulence, pressure control, vortices, rotors
Topics:
Airfoils, Design, Nozzle guide vanes, Rotors, Turbines, Flow (Dynamics), Vortices, Blades, Pressure
1.
Hartland, J. C., Gregory-Smith, D. G., Harvey, N. W., and Rose, M. G., 1999, “Non-Axisymmetric Turbine End Wall Design: Part II Experimental Validation,” ASME 99-GT-338.
2.
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3.
Hodson, H. P., and Dominy, R. G., 1986, “Three-Dimensional Flow in a Low Pressure Turbine Cascade at its Design Condition,” ASME 86-GT-106.
4.
Sieverding, C. H., 1984, “Recent Progress in the Understanding of Basic Aspects of Secondary Flow in Turbine Blade Passages,” ASME 84-GT-78.
5.
Walsh, J. A., and Gregory-Smith, D. G., 1989, “Inlet Skew and the Growth of Secondary Losses and Vorticity in a Turbine Cascade,” ASME 89-GT-65.
6.
Kopper, F. C., Milano, R., and Vanco, M., 1980, “An Experimental Investigation of Endwalls Profiling in a Turbine Vane Cascade,” AIAA-80-1089.
7.
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8.
Dossena, V., Perdichizzi, A., and Savini, M., 1998, “The Influence of Endwall Contouring on the Performance of a Turbine Nozzle Guide Vane,” ASME 98-GT-71.
9.
Morris, A. W. H., and Hoare, R. G., 1975, “Secondary Loss Measurements in a Cascade of Turbine Blades with Meridional Wall Profiling,” ASME 75-WA/GT-13.
10.
Hartland, J. C., Gregory-Smith, D. G., and Rose, M. G., 1998, “Non-Axisymmetric Endwall Profiling in a Turbine Cascade,” ASME 98-GT-525.
11.
Rose, M. G., 1994, “Non-Axisymmetric Endwall Profiling in the HP NGVs of an Axial Flow Gas Turbine,” ASME 94-GT-249.
12.
Harvey, N. W., Rose, M. G., Taylor, M. D., Shahpar, S., Hartland, J., and Gregory-Smith, D. G., 1999, “Non-Axisymmetric Turbine End Wall Design: Part I Three-Dimensional Linear Design System,” ASME 99-GT-337.
13.
Shahpar, S., and Lapworth, B. L., 1998, “A Forward and Inverse Three-Dimensional Linear Design System for Turbomachinery Applications,” 4th ECCOMASS Computational Fluid Dynamics Conference, Athens, Sept. 7–11.
14.
Moore, J. G., 1985, “Calculation of 3D Flow without Numerical Mixing,” AGARD-LS-140 on 3D Computational Techniques Applied to Internal Flows in Propulsion Systems, pp. 8.1–8.15.
15.
Gregory-Smith, D., 1982, “Secondary Flow and Losses in Axial Flow Turbines,” ASME 82-GT-19.
Copyright © 2003
 by ASME
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