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TECHNICAL PAPERS

Numerical Simulation of Unsteady Wake/Blade Interactions in Low-Pressure Turbine Flows Using an Intermittency Transport Equation

[+] Author and Article Information
Y. B. Suzen, P. G. Huang

 Department of Mechanical Engineering, University of Kentucky, 151 RGAN Building, Lexington, KY 40506-0503

J. Turbomach 127(3), 431-444 (Mar 01, 2004) (14 pages) doi:10.1115/1.1860375 History: Received October 01, 2003; Revised March 01, 2004

An extensive computational investigation of the effects of unsteady wake/blade interactions on transition and separation in low-pressure turbines has been performed by numerical simulations of two recent sets of experiments using an intermittency transport equation. The experiments considered have been performed by Kaszeta and Simon and Stieger in order to investigate the effects of periodically passing wakes on laminar-to-turbulent transition and separation in low-pressure turbines. The test sections were designed to simulate unsteady wakes in turbine engines for studying their effects on boundary layers and separated flow regions over the suction surface. The numerical simulations of the unsteady wake/blade interaction experiments have been performed using an intermittency transport model. The intermittent behavior of the transitional flows is taken into account and incorporated into computations by modifying the eddy viscosity, with the intermittency factor. Turbulent quantities are predicted by using Menter’s two-equation turbulence model (SST). The intermittency factor is obtained from the transport equation model, which can produce both the experimentally observed streamwise variation of intermittency and a realistic profile in the cross-stream direction. Computational results are compared to the experiments. Overall, general trends are captured and prediction capabilities of the intermittency transport model for simulations of unsteady wake/blade interaction flowfields are demonstrated.

Copyright © 2005 by American Society of Mechanical Engineers
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References

Figures

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Figure 4

Bar-passing cascade facility consisting of wake generator and cascade (11)

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Figure 5

Details of the bar-passing cascade (11)

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Figure 6

Locations of the 25 measurement stations on the suction side of the blade (11)

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Figure 7

Multiblock grid system used for simulating experiment of Kaszeta (2,34), (a) (top) 43 zone multiblock grid for the computational domain, (b) (bottom left) close-up view of rod grid, and (c ) (bottom right) close-up view of blade grid

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Figure 8

Computed vorticity contours for experiment of Kaszeta (2,34). (a) (left) instantaneous vorticity and (b) (right) phase-averaged vorticity.

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Figure 9

Velocity at the midpoint between the leading edges of the pressure and suction surfaces for the reduced wake passing frequency case

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Figure 14

Comparison of computed and experimental phase-averaged velocity distributions (m∕s) at various streamwise stations on the suction surface of the blade for the reduced wake frequency experiments of Kaszeta (2,34). Horizontal axis: Phase angle (0–360 deg). Vertical axis: Wall normal distance (0–1.4 cm).

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Figure 15

Comparison of computed and experimental mean velocity profiles at various streamwise stations on the suction surface of the blade for the reduced frequency experiments of Kaszeta (2,34)

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Figure 16

Comparison of computed and experimental pressure coefficient distributions on the suction surface of the blade for the reduced frequency experiments of Kaszeta (2,34)

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Figure 17

Multi-block grid system used in simulations of experiments of Stieger (11)

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Figure 18

Computed vorticity contours for experiment of Stieger (11); (a) (top) instantaneous vorticity contours and (b) (bottom) phase-averaged vorticity contours

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Figure 1

Cross-sectional view of the wake generator passage (2)

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Figure 2

PAK-B airfoil geometry (2)

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Figure 3

Locations of experimental measurement stations on PAK-B Blade

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Figure 10

Comparison of computed and experimental phase-averaged velocity distributions (m∕s) at various streamwise stations on the suction surface of the blade for the high wake frequency case of Kaszeta (2,34). Horizontal axis: Phase angle (0–360 deg). Vertical axis: Wall normal distance (0–1.4 cm).

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Figure 11

Comparison of computed and experimental mean velocity profiles at various streamwise stations on the suction surface of the blade for the high wake frequency case of Kaszeta (2,34)

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Figure 12

Comparison of computed and experimental pressure coefficient distributions on the suction surface of the blade for the high wake frequency experiments of Kaszeta (2,34)

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Figure 13

Computed phase-averaged pressure coefficient distribution on the suction surface for the high wake frequency case

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Figure 19

Comparison of computational and experimental wake velocity profiles before the blade leading edge for the experiments of Stieger (11)

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Figure 20

Comparison of computational and experimental pressure coefficient distributions for the experiments of Stieger (11)

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Figure 21

Comparison of computational and experimental phase-averaged pressure coefficient distributions on the suction surface of the blade for the experiments of Stieger (11)

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Figure 23

Comparison of computational and experimental mean velocity profiles at various streamwise locations on the suction surface of the blade for the experiments of Stieger (11)

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