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Research Papers

Computational Predictions of Heat Transfer and Film-Cooling for a Turbine Blade With Nonaxisymmetric Endwall Contouring

[+] Author and Article Information
Stephen P. Lynch, Karen A. Thole

Department of Mechanical and Nuclear Engineering, Pennsylvania State University, University Park, PA 16802

Atul Kohli, Christopher Lehane

 Pratt & Whitney, 400 Main Street, East Hartford, CT 06108

J. Turbomach 133(4), 041003 (Apr 19, 2011) (10 pages) doi:10.1115/1.4002951 History: Received June 28, 2010; Revised June 30, 2010; Published April 19, 2011; Online April 19, 2011

Three-dimensional contouring of the compressor and turbine endwalls in a gas turbine engine has been shown to be an effective method of reducing aerodynamic losses by mitigating the strength of the complex vortical structures generated at the endwall. Reductions in endwall heat transfer in the turbine have been also previously measured and reported in literature. In this study, computational fluid dynamics simulations of a turbine blade with and without nonaxisymmetric endwall contouring were compared to experimental measurements of the exit flowfield, endwall heat transfer, and endwall film-cooling. Secondary kinetic energy at the cascade exit was closely predicted with a simulation using the SST k-ω turbulence model. Endwall heat transfer was overpredicted in the passage for both the SST k-ω and realizable k-ε turbulence models, but heat transfer augmentation for a nonaxisymmetric contour relative to a flat endwall showed fair agreement to the experiment. Measured and predicted film-cooling results indicated that the nonaxisymmetric contouring limits the spread of film-cooling flow over the endwall depending on the interaction of the film with the contour geometry.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Depictions of (a) the computational domain and boundary conditions, (b) the flat endwall grid, and (c) the contoured endwall grid

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Figure 2

Depiction of (a) the flat endwall film-cooling grid and hole nomenclature, and (b) the contoured endwall film-cooling grid

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Figure 3

Measurement (11) and predictions of the boundary layer at X/Cax=−2.33 upstream of the blade

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Figure 4

Measurements (11) and predictions of the endwall heat transfer upstream of the cascade

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Figure 5

Measured (11) and predicted blade surface static pressure at midspan

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Figure 6

Depiction of the large-scale low-speed wind tunnel, with piping for the film-cooling studies

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Figure 7

Line contours of CPtot overlaid with flood contours of CSKE at X/Cax=1.4, for the flat endwall (a)–(c) and the contoured endwall (d)–(f)

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Figure 8

Comparison of measured (7) and predicted CSKE, extracted from Fig. 7 at Y/P=0.3

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Figure 9

Comparison of measured (7) and predicted CPtot, extracted from Fig. 7 at Y/P=0.2

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Figure 10

Flat endwall heat transfer; (a) measured (11), (b) predicted with SST k-ω, and (c) predicted with realizable k-ε

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Figure 11

Endwall heat transfer augmentation; (a) measured (11), (b) predicted with SST k-ω, and (c) predicted with realizable k-ε

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Figure 12

Heat transfer augmentation for the contoured versus flat endwall, extracted along an inviscid streamline passing through 0.25P

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Figure 13

Flat endwall film-cooling effectiveness measurements (a) and (b), and predictions (c) and (d) using the SST k-ω model

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Figure 14

Maximum effectiveness downstream of Hole 3, for the flat endwall

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Figure 15

Laterally averaged effectiveness downstream of Hole 3, for the flat endwall

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Figure 16

Contoured endwall film-cooling effectiveness measurements (a) and (b) and predictions (c) and (d) using the SST k-ω model

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Figure 17

Laterally averaged effectiveness downstream of Hole 3, for the contoured versus flat endwalls

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