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TECHNICAL PAPERS

Boundary Layer Transition Induced by Periodic Wakes

[+] Author and Article Information
Xiaohua Wu, Paul A. Durbin

Center for Integrated Turbulence Simulation and Department of Mechanical Engineering, Stanford University, Building 500, Stanford, CA 94305-3030

J. Turbomach 122(3), 442-449 (Nov 01, 1998) (8 pages) doi:10.1115/1.1303076 History: Received November 01, 1998
Copyright © 2000 by ASME
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References

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 Compressors and Turbines—Part 1: Composite Picture,” ASME J. Turbomach., 119, pp. 114–127; “Boundary Layer Development in Axial Compressors and Turbines—Part 2—Compressors,” 119, pp. 128–138; “Boundary Layer Development in Axial Compressors and Turbines—Part 3—LP turbines,” 119, pp. 225–237; “Boundary Layer Development in Axial Compressors and Turbines—Part 4—Computations and Analysis,” 119, pp. 426–443.
Savill, M., 1996, “One Point Closures Applied to Transition,” in: Turbulence and Transition, Hallback et al., eds., Kluwer Press.
Kang, D. J., and Lakshminarayana, B., 1997, “Numerical Prediction for Unsteady Transitional Boundary Layer Flow Due to Rotor–Stator Interaction,” AIAA Paper No. 97–2752.
Simon, F. F., and Ashpis, D. E., 1996, “Progress in Modeling of Laminar to Turbulent Transition on Turbine Vanes and Blades,” NASA TM-107180.
Durbin, P. A., and Laurence, K., 1996, “Nonlocal Effects in Single Point Closure,” in: Advances in Turbulence Research—1996, Korea University, Seoul, Korea, pp. 109–120.
Wilcox, D. G., 1993, Turbulence Modeling for CFD, DCW Industries, Inc.
Dong,  Y., and Cumpsty,  N. A., 1990, “Compressor Blade Boundary Layers, Part 1: Test Facility and Measurements With No Incident Wakes; Part 2: Measurements With Incident Wakes,” ASME J. Turbomach., 112, pp. 222–240.
Orth,  U., 1993, “Unsteady Boundary Layer Transition in Flow Periodically Disturbed by Wakes,” ASME J. Turbomach., 115, pp. 707–713.
Hodson, H. P., 1998, “Blade Row Interactions in Low Pressure Turbines,” in: Blade Row Interference Effects in Axial Turbomachinery Stages, C. H. Sieverding and H. P. Hodson, eds., von Karman Institute for Fluid Dynamics Lecture Series 1998–02.
Liu,  X., and Rodi,  W., 1991, “Experiments on Transitional Boundary Layers With Wake Induced Unsteadiness,” J. Fluid Mech., 231, pp. 229–256.
Wu,  X., Jacobs,  R. G., Hunt,  J. C. R., and Durbin,  P. A., 1999, “Simulation of Boundary Layer Transition Induced by Periodically Passing Wakes,” J. Fluid Mech., 398, pp. 109–153.
Wu, X., and Durbin, P. A., 2000, “Numerical Simulation of Heat Transfer in a Transitional Boundary Layer With Passing Wakes,” ASME J. Heat Transfer, in press.
Spalart,  P. R., and Allmaras,  S. R., 1994, “A One-Equation Turbulence Model for Aerodynamic Flows,” La Research Aerospatiale, 1, pp. 5–21.
Durbin,  P. A., 1995, “Separated Flow Computation With the v2–f Model,” AIAA J., 33, pp. 659–664.
Baldwin, B. S., and Barth, T. J., 1991, “A One-Equation Turbulent Transport Model for High-Reynolds Number Wall Bounded Flows,” AIAA Paper No. 91-0610.
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Figures

Grahic Jump Location
(a) Instantaneous u over one x–y plane at t=32.5T in the DNS of Wu et al. 11; (b) phase-averaged 〈u〉 at ϕ=0.5 from the DNS of Wu et al. 11; (c) phase-averaged 〈u〉 at ϕ=0.5 from the present unsteady RANS using v2–f model
Grahic Jump Location
Time-averaged mean skin-friction coefficient; ○ DNS of Wu et al. 11; – unsteady RANS using v2–f model; — — unsteady RANS using S–A model; [[dotted_line]] Blasius solution without wake; (a) T=1.67; (b) T=0.4175
Grahic Jump Location
X–t diagram of the phase-averaged skin-friction coefficient 〈Cf〉 for T=1.67; (a) DNS of Wu et al. 11; (b) unsteady RANS using v2–f model; (c) unsteady RANS using S–A model
Grahic Jump Location
Phase-averaged mean skin-friction coefficient for T=1.67; symbols: DNS of Wu et al. 11; lines: present unsteady RANS using v2–f model; (a) ○ – 0.0T, ▵ — — 0.2T, + [[dotted_line]] 0.4T; (b) ○ – 0.5T, ▵ — — 0.7T, + [[dotted_line]] 0.9T; [[dashed_line]] Blasius solution
Grahic Jump Location
X–t diagram of the phase-averaged skin-friction coefficient 〈Cf〉 for T=0.4175; (a) DNS of Wu et al. 11; (b) unsteady RANS using v2–f model
Grahic Jump Location
Time-averaged mean integral parameters; symbols DNS of Wu et al. 11; – unsteady RANS using v2–f model; — — unsteady RANS using S–A model; • δ*/θ; ○ 102δ*; (a) T=1.67; (b) T=0.4175
Grahic Jump Location
Characteristics of the temporarily developing planewake used for generation of inflow profiles; lines: v2–f model at three instants; ⋄ plane cylinder wake of Schlichting 18; + Wu et al. 11 at one instant.
Grahic Jump Location
Phase-averaged mean streamwise velocity at x/L=1.0 for T=1.67; (a) DNS of Wu et al. 11; (b) unsteady RANS using v2–f model; ○ 0.0T, ⋄ 0.25T; ▵ 0.50T, + 0.75T
Grahic Jump Location
Phase-averaged mean streamwise velocity at x/L=1.5 for T=1.67; (a) DNS of Wu et al. 11; (b) unsteady RANS using v2–f model; ○ 0.0T, ⋄ 0.25T; ▵ 0.50T, + 0.75T
Grahic Jump Location
Skin friction coefficient for the T3A case; • ERCOFTAC database; – v2–f(n=1); — — v2–f(n=6)
Grahic Jump Location
(a) Layout in the experiments of Liu and Rodi 10; (b) layout in the present numerical simulation; the computational domain is defined as 0.1≤x/L≤3.5,0.0≤y/L≤0.8,0.0≤z/L≤0.2

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