Research Papers

A Three-Dimensional Conjugate Approach for Analyzing a Double-Walled Effusion-Cooled Turbine Blade

[+] Author and Article Information
Gladys C. Ngetich

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: gladys.ngetich@oriel.ox.ac.uk

Alexander V. Murray

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: alexander.murray@eng.ox.ac.uk

Peter T. Ireland

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: peter.ireland@eng.ox.ac.uk

Eduardo Romero

Rolls-Royce Plc.,
Bristol BS34 7QE, UK
e-mail: eduardo.romero@rolls-royce.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 20, 2018; final manuscript received August 29, 2018; published online October 17, 2018. Editor: Kenneth Hall.

J. Turbomach 141(1), 011002 (Oct 17, 2018) (10 pages) Paper No: TURBO-18-1168; doi: 10.1115/1.4041379 History: Received July 20, 2018; Revised August 29, 2018

A double-wall cooling scheme combined with effusion cooling offers a practical approximation to transpiration cooling which in turn presents the potential for very high cooling effectiveness. The use of the conventional conjugate computational fluid dynamics (CFD) for the double-wall blade can be computationally expensive and this approach is therefore less than ideal in cases where only the preliminary results are required. This paper presents a computationally efficient numerical approach for analyzing a double-wall effusion cooled gas turbine blade. An existing correlation from the literature was modified and used to represent the two-dimensional distribution of film cooling effectiveness. The internal heat transfer coefficient was calculated from a validated conjugate analysis of a wall element representing an element of the aerofoil wall and the conduction through the blade solved using a finite element code in ANSYS. The numerical procedure developed has permitted a rapid evaluation of the critical parameters including film cooling effectiveness, blade temperature distribution (and hence metal effectiveness), as well as coolant mass flow consumption. Good agreement was found between the results from this study and that from literature. This paper shows that a straightforward numerical approach that combines an existing correlation for film cooling from the literature with a conjugate analysis of a small wall element can be used to quickly predict the blade temperature distribution and other crucial blade performance parameters.

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Han, J.-C. , 2013, Gas Turbine Heat Transfer and Cooling Technology, CRC Press/Taylor & Francis, Boca Raton, FL.
Andersson, B. , Andersson, R. , Håkansson, L. , Mortensen, M. , Sudiyo, R. , and van Wachem, B. , 2011, Computational Fluid Dynamics for Engineers, Cambridge University Press, Cambridge, UK.
Laschet, G. , Rex, S. , Bohn, D. , and Moritz, N. , 2002, “ 3-D Conjugate Analysis of Cooled Coated Plates and Homogenization of Their Thermal Properties,” Numer. Heat Transfer: Part A, 42(1–2), pp. 91–106. [CrossRef]
Laschet, G. M. , Rex, S. , Bohn, D. , and Moritz, N. , 2003, “ Homogenization of Material Properties of Transpiration Cooled Multilayer Plates,” ASME Paper No. GT2003-38439.
Laschet, G. , Krewinkel, R. , Hul, P. , and Bohn, D. , 2013, “ Conjugate Analysis and Effective Thermal Conductivities of Effusion-Cooled Multi-Layer Blade Sections,” Int. J. Heat Mass Transfer, 57(2), pp. 812–821. [CrossRef]
Zecchi, S. , Arcangeli, L. , Facchini, B. , and Coutandin, D. , 2004, “ Features of a Cooling System Simulation Tool Used in Industrial Preliminary Design Stage,” ASME Paper No. GT2004-53547.
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/Detroit Diesel Allison; Indianapolis, IN, Technical Report No. NASA CR 168015. https://ntrs.nasa.gov/search.jsp?R=19830020105
Heidmann, J. D. , Kassab, A. J. , Divo, E. A. , Rodriguez, F. , and Steinthorsson, E. , 2003, “ Conjugate Heat Transfer Effects on a Realistic Film-Cooled Turbine Vane,” ASME Paper No. GT2003-38553.
Kassab, A. , Divo, E. , Heidmann, J. , Steinthorsson, E. , and Rodriguez, F. , 2003, “ BEM/FVM Conjugate Heat Transfer Analysis of a Three-Dimensional Film Cooled Turbine Blade,” Int. J. Heat Fluid Flow, 13(5), pp. 581–610. [CrossRef]
Rigby, D. L. , Heidmann, J. D. , Ameri, A. A. , and Garg, V. K. , 2001, “ Improved Modeling Capabilities in Glenn-HT—The NASA Glenn Research Center General Multi-Block Navier–Stokes Heat Transfer Code,” Cleveland, OH, NASA Report No. 20020073073. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20020073073.pdf
Mendez, S. , Nicoud, F. , and Poinsot, T. , “ Large-Eddy Simulation of a Turbulent Flow around a Multi-Perforated Plate,” Complex Effects in Large Eddy Simulations, Kassinos S. C., Langer C. A., Iaccarino G., Moin P., eds., Vol. 56. Springer, Berlin, Heidelberg.
Amaral, S. , Verstraete, T. , Van den Braembussche, R. , and Arts, T. , 2010, “ Design and Optimization of the Internal Cooling Channels of a High Pressure Turbine Blade—Part I: Methodology,” ASME J. Turbomach., 132(2), p. 021013. [CrossRef]
Bonini, A. , Andreini, A. , Carcasci, C. , Facchini, B. , Ciani, A. , and Innocenti, L. , 2012, “ Conjugate Heat Transfer Calculations on GT Rotor Blade for Industrial Applications—Part I: Equivalent Internal Fluid Network Setup and Procedure Description,” ASME Paper No. GT2012-69846.
Andreini, A. , Bonini, A. , Da Soghe, R. , Facchini, B. , Ciani, A. , and Innocenti, L. , “ Conjugate Heat Transfer Calculations on GT Rotor Blade for Industrial Applications—Part II: Improvement of External Flow Modeling,” ASME Paper No. GT2012-69849.
Colban, W. F. , Thole, K. A. , and Bogard, D. , 2010, “ A Film-Cooling Correlation for Shaped Holes on a Flat-Plate Surface,” ASME J. Turbomach., 133(1), p. 011002. [CrossRef]
L'Ecuyer, M. R. , and Soechting, F. O. , 1985, “ A Model for Correlating Flat Plate Film Cooling Effectiveness for Rows of Round Holes,” AGARD Heat Transfer and Cooling in Gas Turbine, West Palm Beach, FL, p. 12.
Sellers, J. P. , 1963, “ Gaseous Film Cooling With Multiple Injection Stations,” AIAA J., 1(9), pp. 2154–2156. [CrossRef]
Andrei, L. , Andreini, A. , Facchini, B. , and Winchler, L. , 2014, “ A Decoupled CHT Procedure: Application and Validation on a Gas Turbine Vane With Different Cooling Configurations,” Energy Procedia, 45, pp. 1087–1096. [CrossRef]
Baldauf, S. , Scheurlen, M. , Schulz, A. , and Wittig, S. , 2002, “ Correlation of Film-Cooling Effectiveness From Thermographic Measurements at Engine-like Conditions,” ASME Paper No. GT2002-30180.
Baldauf, S. , Schulz, A. , Wittig, S. , and Scheurlen, M. , 1997, “ An Overall Correlation of Film Cooling Effectiveness From One Row of Holes,” ASME Paper No. 97-GT-079.
Murray, A. V. , Ireland, P. T. , Wong, T. H. , Tang, S. W. , and Rawlinson, A. J. , 2018, “ High Resolution Experimental and Computational Methods for Modelling Multiple Row Effusion Cooling Performance,” Int. J. Turbomach., Propul. Power, 3(1), p. 4. [CrossRef]
Goldstein, R. J. , 1971, “ Film Cooling,” Advances in Heat Transfer, Elsevier, New York, pp. 321–379.
Murray, A. V. , Ireland, P. T. , and Rawlinson, A. J. , 2017, “ An Integrated Conjugate Computational Approach for Evaluating the Aerothermal and Thermomechanical Performance of Double-Wall Effusion Cooled Systems,” ASME Paper No. GT2017-64711.
Gurram, N. , Ireland, P. T. , Wong, T. H. , and Self, K. P. , 2016, “ Study of Film Cooling in the Trailing Edge Region of a Turbine Rotor Blade in High Speed Flow Using Pressure Sensitive Paint,” ASME Paper No. GT2016-57356.
Colladay, R. S. , 1972, “ Analysis and Comparison of Wall Cooling Schemes for Advanced Gas Turbine Applications,” NASA/Lewis Research Center, Cleveland, OH, Report Nos. NASA-TN-D-6633. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720007291.pdf
Lee, T. W. , 2013, Aerospace Propulsion, Wiley, West Sussex, UK.
Baldauf, S. , Schulz, A. , and Wittig, S. , 1999, “ High-Resolution Measurements of Local Effectiveness From Discrete Hole Film Cooling,” ASME J. Turbomach., 123(4), pp. 758–765. [CrossRef]
Holland, M. J. , and Thake, T. F. , 1980, “ Rotor Blade Cooling in High Pressure Turbines,” J. Aircr., 17(6), pp. 412–418. [CrossRef]
Kays, W. M. , and Crawford, M. E. , 1993, Convective Heat and Mass Transfer, McGraw-Hill, New York.
Mayle, R. E. , Blair, M. F. , and Kopper, F. C. , 1979, “ Turbulent Boundary Layer Heat Transfer on Curved Surfaces,” ASME J. Heat Transfer, 101(3), pp. 521–525. [CrossRef]
Chowdhury, N. H. K. , Zirakzadeh, H. , and Han, J.-C. , 2017, “ A Predictive Model for Preliminary Gas Turbine Blade Cooling Analysis,” ASME J. Turbomach., 139(9), p. 091010. [CrossRef]
Andrews, G. E. , Asere, A. A. , Mkpadi, M. C. , and Tirmahi, A. , 1986, “ Transpiration Cooling: Contribution of Film Cooling to the Overall Cooling Effectiveness,” ASME Paper No. 86-GT-136.


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Fig. 1

Features of a double-walled effusion cooled concept turbine blade

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Fig. 2

Features of a double-walled effusion cooled concept turbine blade including leading edge showerhead cooling holes, pin-fin bank, TE slots and the flow direction

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Fig. 3

CFD results of flow velocity contour distribution in the unit cell from Murray et al. [23]

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Fig. 4

Double-wall blade with the unit wall element showing the definition of the geometrical parameters

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Fig. 5

Outer skin of the blade where numerical analysis is performed

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Fig. 6

ηc−Re characteristics compared to that of three simple duct cooling systems, characterized by L/Dh = 20, 40 and 60

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Fig. 7

Steps in the iterative code used to determine aerofoil wall temperature

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Fig. 8

Model setup in ansys steady-state thermal module

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Fig. 9

(a) Film cooling effectiveness on the blade and (b) its corresponding adiabatic wall temperature at Po,c=40 bar

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Fig. 10

Nondimensional film flow rate per hole, film cooling effectiveness, metal effectiveness and dimensionless external heat transfer coefficient as a function of the blade's dimensionless streamwise location

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Fig. 11

A graph of effectiveness as a function of nondimensional coolant mass flow, m* from this study



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