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TECHNICAL PAPERS

Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades

[+] Author and Article Information
Aaron R. Byerley

Department of Aeronautics, USAF Academy, Colorado Springs, CO 80840

Oliver Störmer, Jörg List

Bundesamt fur Wehrtechnik und Beschaffung, Manching, Germany

James W. Baughn

Mechanical and Aeronautical Engineering, University of California, Davis, CA

Terrence W. Simon

Department of Mechanical Engineering, University of Minnesota, Minneapolis, MN

Kenneth W. Van Treuren

Department of Engineering, Baylor University, Waco, TX

J. Turbomach 125(1), 114-120 (Jan 23, 2003) (7 pages) doi:10.1115/1.1518701 History: Received January 29, 2002; Online January 23, 2003
Copyright © 2003 by ASME
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References

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Baughn, J. W., Butler, R. J., Byerley, A. R., and Rivir, R. B., 1995, “An Experimental Investigation of Heat Transfer, Transition and Separation on Turbine Blades at Low Reynolds Number and High Turbulence Intensity,” ASME Paper 95-WA/HT-25.
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Figures

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Laser thermal tuft for attached flow (downstream is to the right)
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Profile loss measurement details
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Evidence of boundary layer separation at Re=28×103 without Gurney flaps. Pressure coefficient and laser thermal tuft eccentricity distributions.
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Laser tufts on the suction surface of the cascade blade for different sizes of Gurney flaps
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Effect of Gurney flap diameter on boundary layer separation as indicated by laser tuft eccentricity (positive values of e indicate attached flow)
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Effect of Gurney flaps on wall static pressure—(a) (Re=28×103), (b) (Re=65×103), (c) (Re=167×103)
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Effect of Gurney flaps on profile loss—(a) (Re=28×103), (b) (Re=65×103), (c) (Re=167×103)
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Effect of Gurney flaps on average profile loss as a function of Reynolds number
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Effect of Gurney flaps on exit angle

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