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Research Papers

Film Cooling Using Antikidney Vortex Pairs: Effect of Blowing Conditions and Yaw Angle on Cooling and Losses

[+] Author and Article Information
Lars Gräf

e-mail: graef@ifd.mavt.ethz.ch

Leonhard Kleiser

e-mail: kleiser@ifd.mavt.ethz.ch
Institute of Fluid Dynamics,
Department of Mechanical
and Process Engineering,
ETH Zurich, Sonneggstrasse 3,
Zurich 8092, Switzerland

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received June 29, 2012; final manuscript received May 4, 2013; published online September 20, 2013. Assoc. Editor: Je-Chin Han.

J. Turbomach 136(1), 011008 (Sep 20, 2013) (8 pages) Paper No: TURBO-12-1103; doi: 10.1115/1.4024648 History: Received June 29, 2012; Revised May 04, 2013

A film-cooling configuration generating an antikidney vortex pair is studied. The configuration features cylindrical cooling holes inclined at an angle of α=35  deg and arranged in two spanwise rows with row-wise alternating yaw angles ±β. Results of several large-eddy simulations are presented with varying blowing conditions and yaw angles. The effects on the achieved cooling and the generated losses are studied. The film-cooling Reynolds number (based on the fully turbulent hot boundary layer along a flat plate and the cooling hole diameter) is 6570 and the Mach number is 0.2. The density as well as mass-flux ratios (DR and M) range from 1 to 2 and the yaw angles from β=±30  deg to ±60  deg. We identify scaling parameters and explain relevant mechanisms. Moreover, the flow field is subdivided into three regions featuring different physical mechanisms: the single-jet, the jet-interaction, and the diffusion region. A strong antikidney vortex pair occurs for high momentum ratios I. For the highest ratio, I = 2.3, our configuration may provide even better effectiveness than cooling with particular fan-shaped holes.

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References

Goldstein, R. J., 1971, “Film Cooling,” Advances in Heat Transfer, T. F.Irvine, Jr. and J. P.Hartnett, eds., Academic, New York, pp. 321–379.
Bogard, D. G., and Thole, K. A., 2006, “Gas Turbine Film Cooling,” J. Propul. Power, 22(2), pp. 249–270. [CrossRef]
Ahn, J., Jung, I. S., and Lee, J. S., 2003, “Film Cooling From Two Rows of Holes With Opposite Orientation Angles: Injectant Behavior and Adiabatic Film Cooling Effectiveness,” Int. J. Heat Fluid Flow, 24(1), pp. 91–99. [CrossRef]
Kusterer, K., Bohn, D., Sugimoto, T., and Tanaka, R., 2007, “Double-Jet Ejection of Cooling Air for Improved Film Cooling,” ASME J. Turbomach., 129(4), pp. 809–815. [CrossRef]
Heidmann, J. D., and Ekkad, S., 2008, “A Novel Antivortex Turbine Film-Cooling Hole Concept,” ASME J. Turbomach., 130, p. 031020. [CrossRef]
Ely, M. J., and Jubran, B. A., 2009, “A Numerical Evaluation on the Effect of Sister Holes on Film Cooling Effectiveness and the Surrounding Flow Field,” Heat Mass Transfer, 45(11), pp. 1435–1446. [CrossRef]
Barthet, S., and Bario, F., 2001, “Experimental Investigation of Film Cooling Flow Induced by Shaped Holes on a Turbine Blade,” Ann. N.Y. Acad. Sci., 934, pp. 313–320. [CrossRef] [PubMed]
Mendez, S., and Nicoud, F., 2008, “Large-Eddy Simulation of a Bi-Periodic Turbulent Flow With Effusion,” J. Fluid Mech., 598, pp. 27–65. [CrossRef]
Renze, P., Schröder, W., and Meinke, M., 2008, “Large-Eddy Simulation of Film Cooling Flows at Density Gradients,” Int. J. Heat Fluid Flow, 29(1), pp. 18–34. [CrossRef]
Burdet, A., Abhari, R. S., and Rose, M. G., 2007, “Modeling of Film Cooling—Part II: Model for Use in Three-Dimensional Computational Fluid Dynamics,” ASME J. Turbomach., 129(2), pp. 221–231. [CrossRef]
Ziefle, J., and Kleiser, L., “Numerical Investigation of a Film-Cooling Flow Structure: Effect of Crossflow Turbulence,” ASME J. Turbomach, 135(4), p. 041001. [CrossRef]
Renze, P., Schröder, W., and Meinke, M., 2007, “LES of Film Cooling Efficiency for Different Hole Shapes,” Proc. 5th International Symposium on Turbulence and Shear Flow Phenomena, Munich, Germany, August 26–29, pp. 683–688.
Renze, P., Schröder, W., and Meinke, M., 2009, “Large-Eddy Simulation of Interacting Film Cooling Jets,” ASME Paper No. GT2009-5916. [CrossRef]
Sinha, A. K., Bogard, D. G., and Crawford, M. E., 1991, “Film-Cooling Effectiveness Downstream of a Single Row of Holes With Variable Density Ratio,” ASME J. Turbomach., 113(3), pp. 442–449. [CrossRef]
Goldstein, R. J., Eckert, E. R. G., and Burggraf, F., 1974, “Effects of Hole Geometry and Density on Three-Dimensional Film Cooling,” Int. J. Heat Mass Transfer, 17(5), pp. 595–607. [CrossRef]
Goldstein, R. J., and Jin, P., 2001, “Film Cooling Downstream of a Row of Discrete Holes With Compound Angle,” ASME J. Turbomach., 123(2), pp. 222–230. [CrossRef]
Ligrani, P. M., Wigle, J. M., Ciriello, S., and Jackson, S. M., 1994, “Film-Cooling From Holes With Compound Angle Orientations: Part 1—Results Downstream of Two Staggered Rows of Holes With 3d Spanwise Spacing,” ASME J. Heat Transfer, 116(2), pp. 341–352. [CrossRef]
Gräf, L., and Kleiser, L., 2011, “Large-Eddy Simulation of Double-Row Compound-Angle Film Cooling: Setup and Validation,” Comput. Fluids, 43(1), pp. 58–67. [CrossRef]
Gräf, L., and Kleiser, L., 2012, “Flow-Field Analysis of Anti-Kidney Vortex Film-Cooling,” J. Therm. Sci., 21(1), pp. 66–76. [CrossRef]
Colban, W. F., Thole, K. A., and Bogard, D., 2011, “A Film-Cooling Correlation for Shaped Holes on a Flat-Plate Surface,” ASME J. Turbomach., 133(1), p. 011002. [CrossRef]
Schlatter, P., Stolz, S., and Kleiser, L., 2004, “LES of Transitional Flows Using the Approximate Deconvolution Model,” Int. J. Heat Fluid Flow, 25(3), pp. 549–558. [CrossRef]
Bodony, D. J., 2006, “Analysis of Sponge Zones for Computational Fluid Mechanics,” J. Comput. Phys., 212(2), pp. 681–702. [CrossRef]
Jarrin, N., Benhamadouche, S., Laurence, D., and Prosser, R., 2006, “A Synthetic-Eddy-Method for Generating Inflow Conditions for Large-Eddy Simulations,” Int. J. Heat Fluid Flow, 27(4), pp. 585–593. [CrossRef]
Magagnato, F., Pritz, B., and Gabi, M., 2006, “Inflow Conditions for Large-Eddy Simulation of Compressible Flow in a Combustion Chamber,” Proc. 5th International Symposium on Turbulence, Heat and Mass Transfer, Dubrovnik, Croatia, September 25–29, Y. N. K.Hanjalić and S.Jakirlic, eds., Begell House Publishers, Reading, CT, pp. 343–346. [CrossRef]
Gräf, L., 2012, “Film Cooling Using Anti-Kidney Vortices Investigated by Large-Eddy Simulation,” Ph.D. thesis, ETH Zurich, Zurich, Switzerland.
Lee, S. W., Kim, Y. B., and Lee, J. S., 1997, “Flow Characteristics and Aerodynamic Losses of Film Cooling Jets With Compound Angle Orientations,” ASME J. Turbomach., 119(2), pp. 310–319. [CrossRef]
Aga, V., Mansour, M., and Abhari, R. S., 2009, “Aerothermal Performance of Streamwise and Compound Angled Pulsating Film Cooling Jets,” ASME J. Turbomach., 131(4), p. 041015. [CrossRef]
Gritsch, M., Colban, W., Schär, H., and Döbbeling, K., 2005, “Effect of Hole Geometry on the Thermal Performance of Fan-Shaped Film Cooling Holes,” ASME J. Turbomach., 127(4), pp. 718–725. [CrossRef]
Hartsel, J. E., 1972, “Prediction of Effects of Mass-Transfer Cooling on the Blade-Row Efficiency of Turbine Airfoils,” AIAA Paper No. 72-11. [CrossRef]
Fric, T. F., and Roshko, A., 1994, “Vortical Structure in the Wake of a Transverse Jet,” J. Fluid Mech., 279, pp. 1–47. [CrossRef]
Baldauf, S., Scheurlen, M., Schulz, A., and Wittig, S., 2002, “Correlation of Film-Cooling Effectiveness From Thermographic Measurements at Engine-Like Conditions,” ASME J. Turbomach., 124(4), pp. 686–698. [CrossRef]
Laveau, B., and Abhari, R. S., 2010, “Influence of Flow Structure on Shaped Hole Film Cooling Performance,” ASME Paper No. GT2010-23032. [CrossRef]

Figures

Grahic Jump Location
Fig. 1

Injection geometry and resulting vortices (from Fig. 1 of Ref. [18]). (a)–(c): Kidney-vortex pair from simple-angle injection; (d)–(f): antikidney-vortex pair; (a), (d): side; (b), (e): downstream; and (c), (f): top view.

Grahic Jump Location
Fig. 2

Comparison of experimental results on film-cooling types listed in Table 1. Black: spanwise-averaged effectiveness ⟨η⟩t,z; blue: maximum effectiveness maxz⟨η⟩t (see online version for color).

Grahic Jump Location
Fig. 3

Computational domain (Fig. 2 and case 3 of Ref. [18]) and flow regions. : Inflow sponge; : ambient and outflow sponge; : downstream grid stretching; : wall.

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Fig. 4

(a), (c): Effectiveness and (b): efficiency for different blowing conditions. Black: spanwise-averaged; blue: maximum or red: minimum effectiveness. For symbols, see Table 2 (see online version for color).

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Fig. 8

(a): Effectiveness for different yaw angles, analog to Fig. 4. (b): Comparison of spanwise-averaged effectiveness with experimental cases L7 and L8 (both: α = 30  deg,β = 0  deg,M = 2.0,S/d = 0). L7: Cylindrical holes [31] (L/d = 6, P/d = 3, DR = 1.8); L8: fan-shaped holes [32] (L/d = 5, P/d = 4, DR = 1.7); for further symbols, see Table 3.

Grahic Jump Location
Fig. 7

Temperature for different yaw angles, analog to Fig. 5. For symbols, see Table 3.

Grahic Jump Location
Fig. 6

Loss coefficients at different blowing conditions. (a) Hot gas and (b) mixture total-pressure loss; (c) discharge loss; (d) mixture entropy generation. Black symbols: cases V2, B1, B2, and R0; gray symbols: cases I1 and I2 for comparison. For symbols, see Table 2.

Grahic Jump Location
Fig. 5

(—): Temperature isolines (colored patches online) for row-wise different blowing conditions; ( , ): antikidney vortex-pair trajectories and; (– – –): boundary-layer thickness ⟨U⟩t/U∞ = 0.95. (a)–(d): Top view of ⟨η⟩t; (e)–(h): side view of centerline ⟨Θ⟩t|z/d = 0, note the changed aspect ratio; (i)–(x): downstream view of ⟨Θ⟩t|x/d = -1,3,10,20; isolevels: 0.1, 0.2, …1.0 (see online version for color). For symbols, see Table 2.

Grahic Jump Location
Fig. 9

Loss coefficients at different yaw angles. (a): Hot gas total-pressure loss; (b): mixture entropy generation. Black symbols: cases R0, I1, and I2; gray symbols: cases V2, B1, and B2 for comparison. For symbols, see Table 3.

Grahic Jump Location
Fig. 10

Effectiveness for different resolutions and domain extents. ▪: Reference experiment L0 DR = 1, M = 1; : fine LES V1 DR = 1, M = 1; □: coarse LES V2 DR = 1, M = 1; (……), ○: coarse LES DR = 2, M = 2.1 R0, R0 with xmax/d = 28, and R0 with ymax/d = 10. Analog to Fig. 4(a); for hatching, see Fig. 3.

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