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TECHNICAL PAPERS

Experimental Study of the Effect of Periodic Unsteady Wake Flow on Boundary Layer Development, Separation, and Reattachment Along the Surface of a Low Pressure Turbine Blade

[+] Author and Article Information
M. T. Schobeiri, B. Öztürk

Turbomachinery Performance and Flow Research Laboratory, Texas A&M University, College Station, Texas 77843-3123

J. Turbomach 126(4), 663-676 (Dec 29, 2004) (14 pages) doi:10.1115/1.1791646 History: Online December 29, 2004
Copyright © 2004 by ASME
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References

Pfeil, H., and Herbst R., 1979, “Transition Procedure of Instationary Boundary Layers,” ASME Paper No. 79_GT_128.
Pfeil,  H., Herbst,  R., and Schröder,  T., 1983, “Investigation of the Laminar Turbulent Transition of Boundary Layers Disturbed by Wakes,” ASME J. Eng. Power, 105, pp. 130–137.
Orth,  U., 1993, “Unsteady Boundary Layer Transition in Flow Periodically Disturbed by Wakes,” ASME J. Turbomach., 115, pp. 707–713.
Schobeiri, M. T., and Radke, R. E., 1994, “Effects of Periodic Unsteady Wake Flow and Pressure Gradient on Boundary Layer Transition Along the Concave Surface of a Curved Plate,” ASME Paper 94-GT-327, presented at the International Gas Turbine and Aero-Engine Congress and Exposition, The Hague, Netherlands, June 13–16, 1994.
Schobeiri,  M. T., Read,  K., and Lewalle,  J., 2003, “Effect of Unsteady Wake Passing Frequency on Boundary Layer Transition, Experimental Investigation and Wavelet Analysis,” ASME J. Fluids Eng., 125, pp. 251–266.
Wright,  L., and Schobeiri,  M. T., 1999, “The Effect of Periodic Unsteady Flow on Boundary Layer and Heat Transfer on a Curved Surface,” ASME Trans. J. Heat Transfer, 120, pp. 22–33.
Chakka,  P., and Schobeiri,  M. T., 1999, “Modeling of Unsteady Boundary Layer Transition on a Curved Plate Under Periodic Unsteady Flow Condition: Aerodynamic and Heat Transfer Investigations,” ASME Trans. J. Turbomach.,121, pp. 88–97.
Liu,  X., and Rodi,  W., 1991, “Experiments on Transitional Boundary Layers With Wake-Induced Unsteadiness,” J. Fluid Mech., 231, pp. 229–256.
Schobeiri, M. T., Pappu, K., and Wright, L., 1995, “Experimental Sturdy of the Unsteady Boundary Layer Behavior on a Turbine Cascade,” ASME 95-GT-435, presented at the International Gas Turbine and Aero-Engine Congress and Exposition, Houston, Texas, June 5–8, 1995.
Schobeiri,  M. T., John,  J., and Pappu,  K., 1997, “Experimental Study on the Effect of Unsteadiness on Boundary Layer Development on a Linear Turbine Cascade,” J. Exp. Fluids,23, pp. 303–316.
Schobeiri,  M. T., and Wright,  L., 2003, “Advances in Unsteady Boundary Layer Transition Research,” Int. J. Rotating Mach., 9(1), pp. 1–22.
Schobeiri,  M. T., and Chakka,  P., 2002, “Prediction of Turbine Blade Heat Transfer and Aerodynamics Using Unsteady Boundary Layer Transition Model,” Int. J. Heat Mass Transfer, 45, pp. 815–829.
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Cardamone, P., Stadtmüller P., Fottner, L., and Schiffer, H.-P., 2000, “Numerical Investigation of the Wake-Boundary Layer Interaction on a Highly Loaded LP Turbine Cascade Blade,” ASME 2002-GT-30367, presented at the International Gas Turbine and Aero-Engine Congress and Exposition, Amsterdam, Netherlands, June 3–6, 2002.
Schulte, V., and Hodson, H. P., 1996, “Unsteady Wake-Induced Boundary Layer Transition in High Lift LP Turbines,” ASME Paper No. 96-GT-486.
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Lou, W., and Hourmouziadis, J., 2000, “Separation Bubbles Under Steady and Periodic Unsteady Main Flow Conditions,” ASME Paper 200-GT-270.
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Figures

Grahic Jump Location
Turbine cascade research facility with the components and the adjustable test section
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Ensemble-averaged relative momentum thickness distribution along the suction surface for different streamwise positions for (a) and (b) at Ω=1.59 (SR=160 mm), (c) and (d) at Ω=3.18 (SR=80 mm)
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Ensemble-averaged relative shape factor distribution along the suction surface for different streamwise positions for (a) and (b) at Ω=1.59 (SR=160 mm), (c) and (d) at Ω=3.18 (SR=80 mm)
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Static pressure distributions at Re=110,00 and reduced frequencies Ω=0, 1.59, 3.18 (SR=:,SR=160 mm, 80 mm)
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Time-averaged velocity profiles along the suction surface of the blade at Ω=1.59 (SR=160 mm), Re=110,000 (the numbers represent local s/s0)
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Time-averaged velocity profiles along the suction surface of the blade at Ω=3.18 (SR=80 mm), Re=110,000 (the numbers represent local s/s0)
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Time-averaged turbulent intensity profiles along the suction surface of the blade at Ω=1.59 (SR=160 mm), Re=110,000 (the numbers represent local s/s0)
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Time-averaged turbulent intensity profiles along the suction surface of the blade at Ω=3.18 (SR=80 mm), Re=110,000 (the numbers represent local s/s0)
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Change of separation bubble height under the influence of different reduced frequencies of Ω=0, 1.59, 3.18 (SR=∞,SR=160 mm, 80 mm)
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Ensemble-averaged velocity contours along the suction surface for different s/s0 with time t/τ as parameter for Ω=1.59 (SR=160 mm), Re=110,000 (time-averaged separation bubble for Ω=1.59 marked red)
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Ensemble-averaged velocity contours along the suction surface for different s/s0 with time t/τ as parameter for Ω=3.18 (SR=80 mm), Re=110,000 (time-averaged separation bubble for Ω=3.18 marked red)
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Ensemble-averaged rms fluctuation velocity in the temporal-spatial domain at different y positions for Ω=1.59 (SR=160 mm), and Ω=3.18 (SR=80 mm)
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Time averaged (a) boundary layer thickness, (b) displacement thickness, (c) momentum deficiency thickness and (d) shape factor for three different reduced frequency of Ω=0, 1.59, 3.18 (SR=∞,SR=160 mm, 80 mm), Re=110,000, ss=starting point of separation zone, smd=location of maximum separation bubble height

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