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Research Papers

Conjugate Heat Transfer Measurements and Predictions of a Blade Endwall With a Thermal Barrier Coating

[+] Author and Article Information
Amy Mensch

Department of Mechanical
and Nuclear Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: aem277@psu.edu

Karen A. Thole

Department of Mechanical
and Nuclear Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: kthole@psu.edu

Brent A. Craven

Department of Mechanical
and Nuclear Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: bac207@psu.edu

Contributed by the International Gas Turbine Institute (IGTI) Division of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 7, 2014; final manuscript received July 21, 2014; published online August 26, 2014. Editor: Ronald Bunker.

J. Turbomach 136(12), 121003 (Aug 26, 2014) (11 pages) Paper No: TURBO-14-1119; doi: 10.1115/1.4028233 History: Received July 07, 2014; Revised July 21, 2014

Multiple thermal protection techniques, including thermal barrier coatings (TBCs), internal cooling and external cooling, are employed for gas turbine components to reduce metal temperatures and extend component life. Understanding the interaction of these cooling methods, in particular, provides valuable information for the design stage. The current study builds upon a conjugate heat transfer model of a blade endwall to examine the impact of a TBC on the cooling performance. The experimental data with and without TBC are compared to results from conjugate computational fluid dynamics (CFD) simulations. The cases considered include internal impingement jet cooling and film cooling at different blowing ratios with and without a TBC. Experimental and computational results indicate the TBC has a profound effect, reducing scaled wall temperatures for all cases. The TBC effect is shown to be more significant than the effect of increasing blowing ratio. The computational results, which agree fairly well to the experimental results, are used to explain why the improvement with TBC increases with blowing ratio. Additionally, the computational results reveal significant temperature gradients within the endwall, and information on the flow behavior within the impingement channel.

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References

Padture, N. P., Gell, M., and Jordan, E. H., 2002, “Thermal Barrier Coatings for Gas-Turbine Engine Applications,” Science, 296(5566), pp. 280–284. [CrossRef] [PubMed]
Mensch, A., and Thole, K. A., 2014, “Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling,” ASME J. Eng. Gas Turbines Power, 136(3), p. 031901. [CrossRef]
Albert, J. E., Bogard, D. G., and Cunha, F., 2004, “Adiabatic and Overall Effectiveness for a Film Cooled Blade,” ASME Paper No. GT2004-53998. [CrossRef]
Hylton, L. D., Mihelc, M. S., Turner, E. R., Nealy, D. A., and York, R. E., 1983, “Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surfaces of Turbine Vanes,” NASA Lewis Research Center, Cleveland, OH, Report No. NASA-CR-168015.
Hylton, L. D., Nirmalan, V., Sultanian, B. K., and Kauffman, R. M., 1988, “The Effects of Leading Edge and Downstream Film Cooling on Turbine Vane Heat Transfer,” NASA, Washington, DC, Report No. NASA-CR-182133.
Turner, E. R., Wilson, M. D., Hylton, L. D., and Kauffman, R. M., 1985, “Turbine Vane External Heat Transfer. Volume 1: Analytical and Experimental Evaluation of Surface Heat Transfer Distributions With Leading Edge Showerhead Film Cooling,” NASA Lewis Research Center, Cleveland, OH, Report No. NASA-CR-174827.
Kang, M. B., and Thole, K. A., 2000, “Flowfield Measurements in the Endwall Region of a Stator Vane,” ASME J. Turbomach., 122(3), pp. 458–466. [CrossRef]
Lynch, S. P., Thole, K. A., Kohli, A., and Lehane, C., 2011, “Computational Predictions of Heat Transfer and Film-Cooling for a Turbine Blade With Nonaxisymmetric Endwall Contouring,” ASME J. Turbomach., 133(4), p. 041003. [CrossRef]
Maikell, J., Bogard, D., Piggush, J., and Kohli, A., 2011, “Experimental Simulation of a Film Cooled Turbine Blade Leading Edge Including Thermal Barrier Coating Effects,” ASME J. Turbomach., 133(1), p. 011014. [CrossRef]
Davidson, F. T., Kistenmacher, D. A., and Bogard, D. G., 2014, “Film Cooling With a Thermal Barrier Coating: Round Holes, Craters, and Trenches,” ASME J. Turbomach., 136(4), p. 041007. [CrossRef]
Na, S., Williams, B., Dennis, R. A., Bryden, K. M., and Shih, T. I.-P., 2007, “Internal and Film Cooling of a Flat Plate With Conjugate Heat Transfer,” ASME Paper No. GT2007-27599. [CrossRef]
Panda, R. K., and Prasad, B. V. S. S. S., 2012, “Conjugate Heat Transfer From a Flat Plate With Combined Impingement and Film Cooling,” ASME Paper No. GT2012-68830. [CrossRef]
Dobrowolski, L. D., Bogard, D. G., Piggush, J., and Kohli, A., 2009, “Numerical Simulation of a Simulated Film Cooled Turbine Blade Leading Edge Including Conjugate Heat Transfer Effects,” ASME Paper No. IMECE2009-11670. [CrossRef]
Ravelli, S., Dobrowolski, L., and Bogard, D. G., 2010, “Evaluating the Effects of Internal Impingement Cooling on a Film Cooled Turbine Blade Leading Edge,” ASME Paper No. GT2010-23002. [CrossRef]
Mouzon, B. D., Terrell, E. J., Albert, J. E., and Bogard, D. G., 2005, “Net Heat Flux Reduction and Overall Effectiveness for a Turbine Blade Leading Edge,” ASME Paper No. GT2005-69002. [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 Paper No. GT2011-46616. [CrossRef]
Dees, J. E., Bogard, D. G., Ledezma, G. A., and Laskowski, G. M., 2013, “Overall and Adiabatic Effectiveness Values on a Scaled Up, Simulated Gas Turbine Vane,” ASME J. Turbomach., 135(5), p. 051017. [CrossRef]
Dyson, T. E., Bogard, D. G., and Bradshaw, S. D., 2012, “Evaluation of CFD Simulations of Film Cooling Performance on a Turbine Vane Including Conjugate Heat Transfer Effects,” ASME Paper No. GT2012-69107. [CrossRef]
Williams, R. P., Dyson, T. E., Bogard, D. G., and Bradshaw, S. D., 2014, “Sensitivity of the Overall Effectiveness to Film Cooling and Internal Cooling on a Turbine Vane Suction Side,” ASME J. Turbomach., 136(3), p. 031006. [CrossRef]
Ni, R. H., Humber, W., Fan, G., Johnson, P. D., Downs, J., Clark, J. P., and Koch, P. J., 2011, “Conjugate Heat Transfer Analysis for a Film-Cooled Turbine Vane,” ASME Paper No. GT2011-45920. [CrossRef]
Ni, R. H., Humber, W., Fan, G., Clark, J. P., Anthony, R. J., and Johnson, J. J., 2013, “Comparison of Predictions From Conjugate Heat Transfer Analysis of a Film-Cooled Turbine Vane to Experimental Data,” ASME Paper No. GT2013-94716. [CrossRef]
Lynch, S. P., Thole, K. A., Kohli, A., and Lehane, C., 2011, “Heat Transfer for a Turbine Blade With Nonaxisymmetric Endwall Contouring,” ASME J. Turbomach., 133(1), p. 011019. [CrossRef]
Hollworth, B. R., and Dagan, L., 1980, “Arrays of Impinging Jets With Spent Fluid Removal Through Vent Holes on the Target Surface—Part 1: Average Heat Transfer,” ASME J. Eng. Power, 102(4), pp. 994–999. [CrossRef]
Kistenmacher, D. A., 2013, “Experimental Investigation of Film Cooling and Thermal Barrier Coatings on a Gas Turbine Vane With Conjugate Heat Transfer Effects,” M.S. thesis, University of Texas at Austin, Austin, TX.
Bunker, R. S., 2009, “The Effects of Manufacturing Tolerances on Gas Turbine Cooling,” ASME J. Turbomach., 131(4), p. 041018. [CrossRef]
Feuerstein, A., Knapp, J., Taylor, T., Ashary, A., Bolcavage, A., and Hitchman, N., 2008, “Technical and Economical Aspects of Current Thermal Barrier Coating Systems for Gas Turbine Engines by Thermal Spray and EBPVD: A Review,” J. Therm. Spray Technol., 17(2), pp. 199–213. [CrossRef]
Soechting, F. O., 1999, “A Design Perspective on Thermal Barrier Coatings,” J. Therm. Spray Technol., 8(4), pp. 505–511. [CrossRef]
Moffat, R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1(1), pp. 3–17. [CrossRef]
Praisner, T. J., Allen-Bradley, E., Grover, E. A., Knezevici, D. C., and Sjolander, S. A., 2007, “Application of Non-Axisymmetric Endwall Contouring to Conventional and High-Lift Turbine Airfoils,” ASME Paper No. GT2007-27579. [CrossRef]
Knezevici, D. C., Sjolander, S. A., Praisner, T. J., Allen-Bradley, E., and Grover, E. A., 2010, “Measurements of Secondary Losses in a Turbine Cascade With the Implementation of Nonaxisymmetric Endwall Contouring,” ASME J. Turbomach., 132(1), p. 011013. [CrossRef]
Praisner, T. J., Grover, E. A., Knezevici, D. C., Popovic, I., Sjolander, S. A., Clark, J. P., and Sondergaard, R., 2008, “Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space,” ASME Paper No. GT2008-50898. [CrossRef]
Lake, J., King, P., and Rivir, R., 1999, “Reduction of Separation Losses on a Turbine Blade With Low Reynolds Numbers,” AIAA Paper No. 99-0242. [CrossRef]
Murawski, C. G., and Vafai, K., 2000, “An Experimental Investigation of the Effect of Freestream Turbulence on the Wake of a Separated Low-Pressure Turbine Blade at Low Reynolds Numbers,” ASME J. Fluids Eng., 122(2), pp. 431–433. [CrossRef]
Mahallati, A., McAuliffe, B. R., Sjolander, S. A., and Praisner, T. J., 2007, “Aerodynamics of a Low-Pressure Turbine Airfoil at Low-Reynolds Numbers: Part 1—Steady Flow Measurements,” ASME Paper No. GT2007-27347. [CrossRef]
Zoric, T., Popovic, I., Sjolander, S. A., Praisner, T., and Grover, E., 2007, “Comparative Investigation of Three Highly Loaded LP Turbine Airfoils: Part I—Measured Profile and Secondary Losses at Design Incidence,” ASME Paper No. GT2007-27537. [CrossRef]
Popovic, I., Zhu, J., Dai, W., Sjolander, S. A., Praisner, T., and Grover, E., 2006, “Aerodynamics of a Family of Three Highly Loaded Low-Pressure Turbine Airfoils: Measured Effects of Reynolds Number and Turbulence Intensity in Steady Flow,” ASME Paper No. GT2006-91271. [CrossRef]
Lawson, S. A., Lynch, S. P., and Thole, K. A., 2013, “Simulations of Multiphase Particle Deposition on a Nonaxisymmetric Contoured Endwall With Film-Cooling,” ASME J. Turbomach., 135(3), p. 031032. [CrossRef]
ANSYS, 2010, ANSYS FLUENT, version 13.0.0, ANSYS, Inc., Cannonsburg, PA.
Menter, F. R., 1994, “Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications,” AIAA J., 32(8), pp. 1598–1605. [CrossRef]
Schwänen, M., and Duggleby, A., 2009, “Identifying Inefficiencies in Unsteady Pin Fin Heat Transfer,” ASME Paper No. GT2009-60219. [CrossRef]
Snedden, G., Dunn, D., Ingram, G., and Gregory-Smith, D., 2009, “The Application of Non-Axisymmetric Endwall Contouring in a Single Stage, Rotating Turbine,” ASME Paper No. GT2009-59169. [CrossRef]
Crawford, M. E., 2009, “TEXSTAN (academic version),” University of Texas, Austin, TX.
Pointwise, 2013, version 17.1r3, Pointwise, Inc., Fort Worth, TX.
Marcum, D., and Gaither, J., 1999, “Mixed Element Type Unstructured Grid Generation for Viscous Flow Applications,” AIAA Paper No. 1999–3252. [CrossRef]

Figures

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Fig. 1

Configuration of a conjugate endwall with impingement and film cooling and TBC

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Fig. 2

Depiction of (a) the large-scale low-speed wind tunnel and (b) the test section containing the Pack-B linear blade cascade and conjugate endwall

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Fig. 3

Pack-B cascade static pressure distribution at the blade midspan compared to CFD predictions

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Fig. 4

Schematic of internal and external cooling scheme from (a) the side view and (b) the top view showing the outline of the TBC and discrete thermocouple measurements taken on the endwall in the experiments

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Fig. 5

Depiction of (a) the computational domain and boundary conditions, (b) the surface grid for the endwall and TBC, (c) the prism layer volume grid in the holes and impingement channel, and (d) the volume grid in the mainstream, channel, and plenum

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Fig. 7

Overall effectiveness contours for Mavg = 2.0 (a) measured without TBC, (b) predicted without TBC, and (c) predicted under the TBC

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Fig. 8

Comparison of overall effectiveness with and without TBC, showing measured and predicted values, along inviscid streamlines, PS (a)–(c) and SS (d)–(f)

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Fig. 9

Conjugate CFD prediction of nondimensional temperature in the fluid and the solid at different two slices (a) at the first row of impingement holes and (b) at the second row of impingement holes

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Fig. 6

Overall effectiveness contours for Mavg = 1.0 (a) measured without TBC, (b) predicted without TBC, and (c) predicted under the TBC

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Fig. 10

Measured and predicted improvement with TBC, ΔφTBC¯, and the predicted Δqr for the external endwall surface plotted as a function of Mavg

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Fig. 11

Contours of TBC effectiveness at three blowing ratios, (a) measured Mavg = 0.6, (b) measured Mavg = 1.0, (c) measured Mavg = 2.0, (d) predicted Mavg = 1.0, and (e) predicted Mavg = 2.0

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Fig. 12

Comparison of TBC effectiveness with film and impingement cooling, showing measured and predicted values, along inviscid streamlines, for (a) Mavg = 0.6, (b) Mavg = 1.0, and (c) Mavg = 2.0

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