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Research Papers

Heat Transfer Performance of a Showerhead and Shaped Hole Film Cooled Vane at Transonic Conditions

[+] Author and Article Information
S. Xue

e-mail: xuesnong@vt.edu

A. Newman

e-mail: newman.ands@gmail.com

W. Ng

e-mail: wng@vt.edu
Mechanical Engineering,
Virginia Polytechnic Institute and State University,
Blacksburg, VA 24060

H. K. Moon

e-mail: Moon_Hee_Koo_X@solarturbines.com

L. Zhang

e-mail: zhang_luzeng_j@solarturbines.com
Solar Turbines Incorporated,
San Diego, CA 92186

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 29, 2011; final manuscript received December 12, 2011; published online March 25, 2013. Editor: David Wisler.

J. Turbomach 135(3), 031007 (Mar 25, 2013) (9 pages) Paper No: TURBO-11-1250; doi: 10.1115/1.4006666 History: Received November 29, 2011; Revised December 12, 2011

An experimental study was performed to measure surface Nusselt number and film cooling effectiveness on a film cooled first stage nozzle guide vane (NGV) at high freestream turbulence, using a transient thin film gauge (TFG) technique. The information presented attempts to further characterize the performance of shaped hole film cooling by taking measurements on a row of shaped holes downstream of leading edge showerhead injection on both the pressure and suction surfaces (hereafter PS and SS) of a first stage NGV. Tests were performed at engine representative Mach and Reynolds numbers and high inlet turbulence intensity and large length scale at the Virginia Tech 2D Linear Transonic Cascade facility. Three exit Mach/Reynolds number conditions were tested: 1.0/1,400,000, 0.85/1,150,000, and 0.60/850,000 where Reynolds number is based on exit conditions and vane chord. At Mach/Reynolds numbers of 1.0/1,450,000 and 0.85/1,150,000, three blowing ratio conditions were tested: BR = 1.0, 1.5, and 2.0. At a Mach/Reynolds number of 0.60/850,000, two blowing ratio conditions were tested: BR = 1.5 and 2.0. All tests were performed at inlet turbulence intensity of 12% and length scale normalized by the cascade pitch of 0.28. Film cooling effectiveness and heat transfer results compared well with previously published data, showing a marked effectiveness improvement (up to 2.5×) over the showerhead-only NGV and also agreement with published showerhead-shaped hole data. Net heat flux reduction (NHFR) was shown to increase substantially (average 2.6 × ) with the addition of shaped holes with an increase (average 1.6×) in required coolant mass flow. Based on the heat flux data, the boundary layer transition location was shown to be within a consistent region on the suction side regardless of blowing ratio and exit Mach number.

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References

Goldstein, R. J., Lau, K. Y., and Leung, C. C., 1983, “Velocity and Turbulence Measurements in Combustion Systems,” Exp. Fluids, 1, pp. 93–99. [CrossRef]
Koutmos, P., and McGuirk, J. J., 1989, “Isothermal Flow in a Gas Turbine Combustor A Benchmark Experimental Study,” Exp. Fluids, 7, pp. 344–354. [CrossRef]
Reiss, H., and Bölcs, A., 2000, “The Influence of the Boundary Layer State and Reynolds Number on Film Cooling and Heat Transfer on a Cooled Nozzle Guide Vane,” IGTI Turbo Expo, Berlin, ASME Paper No. GT-2000-205.
Ames, F. E., 1998, “Aspects of Vane Film Cooling With High Turbulence: Part I— Heat Transfer,” ASME J. Turbomach., 120, p. 768–776. [CrossRef]
Guo, S. M., Oldfield, M. L. G., and Rawlinson, A. J., 2002, “Influence of Discrete Pin Shaped Surface Roughness (P-Pins) on Heat Transfer and Aerodyanmics of Film Cooled Aerofoil,” Proceedings of ASME Turbo Expo, Paper No. GT-2002-30179.
Cutbirth, J. M., and Bogard, D. G., 2002, “Evaluation of Pressure Side Film Cooling With Flow and Thermal Field Measurement, Part II: Turbulence Effects,” Proceedings of ASME Turbo Expo, Paper No. GT-2002-30175.
Ou, S., Rivir, R., Meininger, M., Soechting, F., and Tabbita, M., 2000, “Transient Liquid Crystal Measurement of Leading Edge Film Cooling Effectiveness and Heat Transfer with High Free Stream Turbulence,” Proceedings of ASME Turbo Expo, Paper No. GT-2000-245.
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, pp. 595–607. [CrossRef]
Schmidt, D., Sen, B., and Bogard, D., 1996, “Film Cooling with Compound Angle Holes: Adiabatic Effectiveness,” ASME J. Turbomach., 118, pp. 807–813. [CrossRef]
Gritsch, M., Schulz, A., and Wittig, S., 1998, “Heat Transfer Coefficients Measurements of Film-Cooling Holes With Expanded Exits,” IGTI Conference, Stockholm, ASME Paper No. 98-GT-28.
Yu, Y., Yen, C. H., Shih, T. I. P., Chyu, M. K., and Gogineni, S., 2002, “Film Cooling Effectiveness and Heat Transfer Coefficient Distributions Around Diffusion Shaped Holes,” ASME J. Heat Transfer, 124, pp. 820–827. [CrossRef]
Bell, C. M., Hamakawa, H., and Ligrani, P. M., 2000, “Film Cooling From Shaped Holes,” ASME J. Heat Transfer, 122, pp. 224–232. [CrossRef]
Dittmar, J., Schulz, A., and Wittig, S., 2003, “Assessment of Various Film-Cooling Configurations Including Shaped and Compound Angle Holes Based on Large-Scale Experiments,” ASME J. Turbomach., 125, pp. 57–64. [CrossRef]
Yuen, C. H. N., Martinez-Botas, R. F., and Whitelaw, J. H., 2001, “Film Cooling Effectiveness Downstream of Compound and Fan-Shaped Holes,” IGTI Turbo Expo, New Orleans, ASME Paper No. 2001-GT-0131.
Lu, Y., Dhungel, A., Ekkad, S. V., and Bunker, R. S., 2009, “Effect of Trench Width and Depth on Film Cooling from Cylindrical Holes Embedded in Trenches,” ASME J. Turbomach., 131, No. 011003. [CrossRef]
Dhungel, A., Lu, Y., Phillips, W., Ekkad, S. V., and Heidmann, J., 2009, “Film Cooling From a Row of Holes Supplemented with Antivortex Holes,” ASME J. Turbomach., 131, No. 021007. [CrossRef]
Wittig, S., Schulz, A., Gritsch, M., and Thole, K. A., 1996, “Transonic Film-Cooling Investigations: Effects of Hole Shapes and Orientations,” IGTI Turbo Expo, Birmingham, UK, ASME Paper No. 1996-GT-222.
Thole, K. A., Gritsch, M., Schulz, A., and Wittig, S., 1998, “Flowfield Measurements for Film-Cooling Holes With Expanded Exits,” ASME J. Turbomach., 120, pp. 327–336. [CrossRef]
Saumweber, C., and Schulz, A., 2004, “Interaction of Film Cooling Rows: Effects of Hole Geometry and Row Spacing on the Cooling Performance Downstream of the Second Row of Holes,” ASME J. Turbomach., 126, pp. 237–246. [CrossRef]
Saumweber, C., and Schulz, A., 2003, “Interaction of Film Cooling Rows: Effects of Hole Geometry and Row Spacing on the Cooling Performance Downstream of the Second Row of Holes” IGTI Turbo Expo, Atlanta, ASME Paper No. GT2003-38195.
Colban, W., Gratton, A., Thole, K. A., and Haendler, M., 2005, “Heat Transfer and Film-Cooling Measurements on a Stator Vane with Fan-Shaped Cooling Holes,” IGTI Turbo Expo, Reno-Tahoe, ASME Paper No. GT2005-68258.
Colban, W., Thole, K. A., and Haendler, M., 2007, “Experimental and Computational Comparisons of Fan-Shaped Film Cooling on a Turbine Vane Surface,” ASME J. Turbomach., 129, pp. 23–31. [CrossRef]
Chappell, J., Ligrani, P., Sreekanth, S., and Lucas, T., 2008, “Suction-Side Gill-Region Film Cooling: Effects of Hole Shape and Orientation on Adiabatic Effectiveness and Heat Transfer Coefficient,” IGTI Turbo Expo, Berlin, ASME Paper No. GT2008-50798.
Furukawa, T., and Ligrani, P., 2002, “Transonic Film Cooling Effectiveness from Shaped Holes on a Simulated Turbine Airfoil,” J. Thermophys. Heat Transfer, 16, pp. 228–237. [CrossRef]
Zhang, L., and Pudupatty, R., 2000, “The Effects of Injection Angle and Hole Exit Shape on Turbine Nozzle Pressure Side Film Cooling,” IGTI Turbo Expo, Munich, ASME Paper No. 2000-GT-247.
Zhang, L., and Moon, H. K., 2008, “The Effect of Wall Thickness on Nozzle Suction Side Film Cooling,” IGTI Turbo Expo, Berlin, ASME Paper No. GT2008-50631.
Schnieder, M., Parneix, S., and von Wolfersdorf, J., 2003, “Effect of Showerhead Injection on Superposition of Multi-Row Pressure Side Film Cooling with Fan Shaped Holes,” IGTI Turbo Expo, Atlanta, ASME Paper No. GT2003-38693.
Thurman, D. R., Poinsatte, P. E., and Heidmann, J. D., 2008, “Heat Transfer Measurements for a Film Cooled Turbine Vane Cascade,” IGTI Turbo Expo, Berlin, ASME Paper No. GT2008-50651.
Guo, S. M., Lai, C. C., Jones, T. V., Oldfield, M. L. G., Lock, G. D., and Rawlinson, A. J., 1998, “The Application of Thin-Film Technology to Measure Turbine-Vane Heat Transfer and Effectiveness in a Film-Cooled, Engine-Simulated Environment,” Int. J. Heat Fluid Flow, 19, pp. 594–600. [CrossRef]
Sargison, J. E., Guo, S. M., Oldfield, M. L. G., Lock, G. D., and Rawlinson, A. J., 2002, “A Converging Slot-Hole Film-Cooling Geometry—Part 2: Transonic Nozzle Guide Vane Heat Transfer and Loss,” ASME J. Turbomach., 124, pp. 461–471. [CrossRef]
Reagle, C. J., Newman, A., Xue, S., Ng, W., Ekkad, S., Moon, H. K., and Zhang, L., 2010, “A Transient Infrared Technique for Measuring Surface and Endwall heat Transfer in a Transonic Turbine Cascade,” IGTI Turbo Expo, Glasgow, Paper No. GT2010-22975.
Bolchoz, T., Nasir, S., Reagle, C., Ng, W. F., and Moon, H. K., 2009, “An Experimental Investigation of Showerhead Film Cooling Performance In A Transonic Vane Cascade At Low and High Freestream Turbulence,” IGTI Turbo Expo, Orlando, Paper No. GT2009-59796.
Nasir, S., Carullo, J. S., Ng, W. F., Thole, K. A., Wu, H., Zhang, L. J., and Moon, H. K., 2007, “Effects of Large Scale High Freestream Turbulence, and Exit Reynolds Number on Turbine Vane Heat Transfer in a Transonic Cascade,” ASME J. Turbomach., 131, pp. 021021. [CrossRef]
Nasir, S., Bolchoz, T., Ng, W. F., Zhang, L. J., Moon, H. K., and Anthony, R. J., 2008, “Showerhead Film Cooling Performance of a Turbine Vane in a Transonic Cascade,” ASME IMECE 2008, Paper No. 66528.
Doorly, J. E., and Oldfield, M. L. G., 1987, “The Theory of Advanced Multi-Layer Thin Film Heat Transfer Gages,” Int. J. Heat Mass Transfer, 30, pp. 1159–1168. [CrossRef]
Joe, C. R., 1997, “Unsteady Heat Transfer on the Turbine Research Facility at Wright Laboratory,” Ph. D. Dissertation, Syracuse University.
Cress, R. D., 2006, “Turbine Blade Heat Transfer Measurements in a Transonic Flow Using Thin Film Gages,” Master’s Thesis, Virginia Polytechnic Institute and State University.
Popp, O., Smith, D. E., Bubb, J. V., Grabowski, H. C., Diller, T. E., Schetz, J. A., and Ng., W. F., 2000, “An Investigation of Heat Transfer in a Film Cooled Transonic Turbine Cascade, Part II: Unsteady Heat Transfer,” IGTI Turbo Expo, Berlin, Paper No. GT-2000-203.
Newman, A., 2010, “Performance of a Showerhead and Shaped Hole Film Cooled Vane at High Freestream Turbulence and Transonic Conditions,” Master’s Thesis, Virginia Polytechnic Institute and State University.
Incropera, F. P., and DeWitt, D. P., 2002, Fundamentals of Heat and Mass Transfer, 5th ed., Wiley and Sons, New York.
Blair, M. F., 1983, “Influence of Free-Stream Turbulence on Turbulent Boundary Layer Heat Transfer and Mean Profile Development, Part I—Experimental Data,” ASME J. Heat Transfer, 105, pp. 33–40. [CrossRef]
Ledezma, G. A., Laskowski, G. M., Dees, J. E., and Bogard, D. G., 2011, “Overall and Adiabatic Effectiveness Values on a Scaled up Simulated Gas Turbine Vane: Part II Numerical Simulation,” ASME GT2011-46616.
Rigby, M. J., Johnson, A. B., and Oldfield, M. L. G., 1990, “Gas Turbine Rotor Blade Film Cooling with and without Simulated NGV Shock Waves and Wakes,” ASME 90-GT-78.
Teng, S., sohn, D. K., and Han, J.-C., 2000, “Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade”, ASME J. Turbomach., 122, pp. 340–347. [CrossRef]
Mayle, R. E., 1991, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113, pp. 509–536. [CrossRef]
Mhetras, S., Han, J.-C., and Rudolph, R., 2007, “Effect of Flow Parameter Variations on Full Coverage Film-Cooling Effectiveness for a Gas Turbine Blade,” IGTI Turbo Expo, May, 2007, Montreal, Canada, Paper No. GT2007-27071 .
Mehendale, A. B., and Han, J.-C., 1993, “Reynolds Number Effect on Leading Edge Film Effectiveness and Heat Transfer Coefficient,” Int. J. Heat Mass Transfer, 36, pp. 3723–3730. [CrossRef]
Lutum, E., von Wolfersdorf, J., Semmler, K., Naik, S., and Weigand, B., 2001, “Film Cooling on a Convex Surface: Influence of External Pressure Gradient and Mach Number on Film Cooling Performance,” Heat Mass Transfer, 38, 7-6. [CrossRef]
Liess, C., 1975, “Experimental Investigation of Fim Cooling with Ejection from a Row of Holes for the Application to Gas Turbine Blade,” J. Eng. Power97, pp. 21–27. [CrossRef]
Shantanu Mhetras, S., Han, J.-C., and Rudolph, R., 2008, “Film-Cooling Effectiveness From Shaped Film Cooling Holes for a Gas Turbine Blade,” Proceedings of ASME TURBO EXPO 2008 Power for Land, Sea and Air, Paper No. GT-2008-50916.
Abuaf, N., Bunker, R., and Lee, C. P., 1997, “Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade,” ASME J. Turbomach., 119, pp. 302–309. [CrossRef]
Arts, T., and Bourguignon, A. E., 1990, “Behavior of a Coolant Film with Two Rows of Holes Along the Pressure Side of a High Pressure Nozzle Guide Vane,” ASME J. Turbomach., 112, pp. 512–520. [CrossRef]
Ekkad, S. V., Mehendale, A. B., Han, J.-C., and Lee, C. P., 1997, “Combined Effect of Grid Turbulence and Unsteady Wake on Film Effectiveness and Heat Transfer Coefficient of a Gas Turbine Blade with Air and CO2 Film Injection,” ASME J. Turbomach., 119, pp. 594–600. [CrossRef]
Drost, U., and Bölcs, A., 1999, “Investigation of Detailed Film Cooling Effectiveness and Heat Transfer Distribution on a Gas Turbine Airfoil,” ASME J. Turbomach., 121, pp. 233–242. [CrossRef]

Figures

Grahic Jump Location
Fig. 3

Showerhead-shaped hole vane profile

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Fig. 2

Close-up of vane test section

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Fig. 1

Virginia Tech Transonic Cascade facility

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Fig. 4

PS effectiveness literature comparison

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Fig. 5

SS effectiveness literature comparison

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Fig. 6

PS Mex = 0.85 BR = 2.0 data compared with flat plate correlations

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Fig. 12

Effect of exit Mach number on Nusselt number distribution, BR = 2.0

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Fig. 13

Effect of blowing ratio on Nusselt number distribution, Mex = 0.85

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Fig. 7

SS Mex = 0.85 BR = 2.0 data compared with flat plate correlations

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Fig. 14

Comparison of NHFR from Nasir et al. [34] with the present study at Mex = 0.85, BR = 2.0

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Fig. 8

Film cooling effectiveness comparison at M = 0.85, BR = 2.0

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Fig. 9

Film cooling Nusselt number comparison, M = 0.85, BR = 2.0

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Fig. 10

Effect of exit Mach number on film effectiveness distribution, BR = 2.0

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Fig. 11

Effect of blowing ratio on film effectiveness, Mex = 0.85

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