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TECHNICAL PAPERS

The Effect of Real Turbine Roughness With Pressure Gradient on Heat Transfer

[+] Author and Article Information
Jeffrey P. Bons

Department of Mechanical Engineering, Brigham Young University, Provo, UT 84602e-mail: jbons@byu.edu

Stephen T. McClain

Department of Mechanical Engineering, The University of Alabama at Birmingham, Birmingham, AL 35294e-mail: smcclain@eng.uab.edu

J. Turbomach 126(3), 385-394 (Sep 03, 2004) (10 pages) doi:10.1115/1.1738120 History: Received December 01, 2002; Revised March 01, 2003; Online September 03, 2004
Copyright © 2004 by ASME
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References

Figures

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Experimental velocity data (Ue normalized by exit velocity from stage) versus wetted surface distance for typical turbine airfoil (Fig. 5 from 19)
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Schematic of variable pressure gradient wind tunnel at AFRL
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Freestream velocity distribution for three pressure gradients in AFRL wind tunnel
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Empirical Te−Tw distributions used in St calculations (nondimensionalized by measured Te−Tw at x=1.2 m)
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Reynolds analogy predictions from So 35 compared with results using smooth-wall predictions from BLACOMP computation
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Experimental St data for six panels and three pressure gradients (Rex=9×105)
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Experimental data for five panels (Rex=9×105). Roughness-induced change in St(StRough−StSmooth) as a percent of StSmooth at matching pressure gradient.
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Experimental data for six panels (Rex=9×105). Pressure gradient induced change in St(StPG−StZPG) as a percent of StZPG for the same rough surface.
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Comparison of combined (synergistic) roughness/pressure gradient effects on St with compound and additive estimates using individual effects of roughness alone and pressure gradient alone. Data for five rough surfaces and (a) APG or (b) FPG. (Rex=9×105).
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Mean velocity profiles (U) at leading and trailing edge of smooth panels: adverse, zero, and favorable pressure gradients. (Rex=9×105).
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Comparison of experimental St data with discrete-element method prediction for three panels and three pressure gradients. (Rex=9×105).

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