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TECHNICAL PAPERS

A Detailed Analysis of Film Cooling Physics: Part III— Streamwise Injection With Shaped Holes

[+] Author and Article Information
D. G. Hyams, J. H. Leylek

Department of Mechanical Engineering, Clemson University, Clemson, SC 29634

J. Turbomach 122(1), 122-132 (Feb 01, 1997) (11 pages) doi:10.1115/1.555435 History: Received February 01, 1997
Copyright © 2000 by ASME
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References

Figures

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Schematics of the selected film hole shapes show the geometry of each configuration in three orthogonal planes
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A sketch of the computational domain shows the boundary condition scheme used for each shaped case
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A photo of the ISHAP computational grid shows typical grid quality and resolution
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Sketch of the film hole boundary layer vorticity shows the manipulation of streamwise aligned vorticity by film-hole geometry
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A validation plot of centerline effectiveness shows good agreement between computational and experimental data
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A comparison of the exit plane VR distribution shows the low-momentum content of the diffused holes
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Contours of the flow exit angle (α) at the exit plane show the various effective injection angles of each film hole shape
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Pathlines from the film-hole boundary layer show the presence or absence of a coolant wake for the REF, FDIFF, and LDIFF cases
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Centerline temperature profiles at x/D=3,x/D=6,x/D=10, and x/D=15 for the REF, FDIFF, and LDIFF cases show the overall coolant characteristics
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The streamwise-aligned vorticity distribution at the film-hole exit plane shows the potential for generating secondary flow
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A comparison of secondary flow magnitudes at x/D=2 shows the near-elimination of streamwise vortices for the diffusion film holes
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Lateral (z) vorticity profiles delineate the film-crossflow shear layer and indicate the level of transverse velocity gradients for the REF, FDIFF, and LDIFF cases
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Profiles of TL at downstream stations show the shear layer interaction between film and crossflow
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A comparison of exit planeTL (percent) for all shapes shows the reduction of film hole turbulence by inlet shaping
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Aligned vorticity contours at x/D=0 for the CUSP case show the generation of an extra pair of vorticity cores at the cusp location
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A comparison of centerline effectiveness for computed (row of jets) and measured (single jet) results for the CUSP case
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A comparison of the temperature footprints on the test plate shows the distribution of coolant on the test surface for all film hole shapes
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A comparison between predicted and measured laterally averaged adiabatic effectiveness for various shaped hole film cooling configurations
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Comparison of the laterally averaged heat transfer coefficient (W/m2 K) for various shaped hole configurations to an empirical correlation for a flat plate
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A conceptual induction lift curve shows qualitatively the importance of avoiding coolant lift by the positioning of the deposited film hole boundary layer

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