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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Goldstein, R., Eckert, E., and Burggraf, F., 1994. “Effects of Hole Geometry and Density on Three-Dimensional Film Cooling,” Int. J. Heat Mass Transf., pp. 595–606.
Papell, S., 1984, “Vortex Generating Flow Passage Design for Increased Film Cooling Effectiveness and Surface Coverage,” ASME Paper No. 84-HT-22.
Makki, Y. H., and Jakubowski, G. S., 1986, “An Experimental Study of Film Cooling from Diffused Trapezoidal Shaped Holes,” AIAA Paper No. AIAA-86-1326.
Schmidt,  D., Sen,  B., and Bogard,  D., 1996, “Film Cooling With Compound Angle Holes: Adiabatic Effectiveness,” ASME J. Turbomach., 118, pp. 807–813.
Sen,  B., Schmidt,  D., and Bogard,  D., 1996, “Film Cooling With Compound Angle Holes: Heat Transfer,” ASME J. Turbomach., 118, pp. 800–806.
Thole,  K., Gritsch,  M., Schulz,  A., and Wittig,  S., 1998, “Flowfield Measurements for Film-Cooling Holes With Expanded Exits,” ASME J. Turbomach., 120, pp. 327–336.
Haven, B. A., and Kurosaka, M., 1996. “The Effect of Hole Geometry on Lift-Off Behavior of Coolant Jets,” AIAA Paper No. 96-0618.
Hyams, D., McGovern, K., and Leylek, J., 1996, “Effects of Geometry on Slot-Jet Film Cooling Performance,” ASME Paper No. 96-GT-187.
Wittig, S., Schulz, A., Gritsch, M., and Thole, K. A., 1996, “Transonic Film-Cooling Investigations: Effects of Hole Shapes and Orientations,” ASME Paper No. 96-GT-222.
Walters,  D., and Leylek,  J., 1997, “A Systematic Computational Methodology Applied to a Three-Dimensional Film-Cooling Flowfield,” ASME J. Turbomach., 119, pp. 777–785.
Farmer, J. P., Seager, D. J., and Liburdy, J. A., 1997, “The Effect of Shaping Inclined Slots on Film Cooling Effectiveness and Heat Transfer Coefficient,” ASME Paper No. 97-GT-339.


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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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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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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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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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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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