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TECHNICAL PAPERS

Thermal Field and Flow Visualization Within the Stagnation Region of a Film-Cooled Turbine Vane

[+] Author and Article Information
J. Michael Cutbirth, David G. Bogard

Mechanical Engineering Department, University of Texas at Austin, Austin, TX 78712

J. Turbomach 124(2), 200-206 (Apr 09, 2002) (7 pages) doi:10.1115/1.1451086 History: Received October 03, 2000; Online April 09, 2002
Copyright © 2002 by ASME
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References

Figures

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Comparison of laterally averaged adiabatic effectiveness for the showerhead region with Tu=20 percent
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Effect of mainstream turbulence level on adiabatic effectiveness contours for Msh=1.5 and DR=1.8. (a) Tu=0.5 percent, and (b) Tu=20 percent
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Flow visualization of the Stag row (x/d=0) for Msh=1.5 and Tu=20 percent—(a) time-averaged, and (b) instantaneous images
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Relationship of the thermal and velocity fields at z/p=7.2 for blowing ratios (a) Msh=0.0, (b) Msh=1.0, and (c) Msh=1.5
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Showerhead adiabatic effectiveness contours for Tu=0.5 percent, DR=1.8 and blowing ratios (a) Msh=1.0, and (b) Msh=1.5
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Comparison of laterally averaged adiabatic effectiveness for the showerhead region with Tu=0.5 percent.
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Effect of the blowing ratio on the film cooling jet for the Stag row of holes (x/d=0.0). Profiles at z/p=7.2 and with Tu=0.5 percent.
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Flow visualization of showerhead film cooling holes at x/d=0.0 and with Tu=0.5 percent. (images averaged over 1 second at 8 frames/s)
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Thermal profiles above the surface and along the PS2 row of holes showing the build-up effect for Msh=1.5
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Thermal profiles above the surface and along the Stag row of holes (x/d=0.0) showing the build-up effect for Msh=1.5
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Film cooling hole configuration and location of measurement planes (dashed lines)
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Turbine vane test section

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