Research Papers

Multiconfiguration Shape Optimization of Internal Cooling Systems of a Turbine Guide Vane Based on Thermomechanical and Conjugate Heat Transfer Analysis

[+] Author and Article Information
Bingxu Wang, Yingjie Xu, Manyu Xiao

Engineering Simulation
and Aerospace Computing (ESAC),
Northwestern Polytechnical University,
P.O. Box 552,
Xi'an, Shaanxi 710072, China

Weihong Zhang

Engineering Simulation
and Aerospace Computing (ESAC),
Northwestern Polytechnical University,
P.O. Box 552,
Xi'an, Shaanxi 710072, China
e-mail: zhangwh@nwpu.edu.cn

Gongnan Xie

Engineering Simulation
and Aerospace Computing (ESAC),
Northwestern Polytechnical University,
P.O. Box 552,
Xi'an, Shaanxi 710072, China
e-mail: xgn@nwpu.edu.cn

1Corresponding author.

Manuscript received March 27, 2014; final manuscript received August 1, 2014; published online March 17, 2015. Assoc. Editor: Giulio Lorenzini.

J. Heat Transfer 137(6), 061004 (Jun 01, 2015) (8 pages) Paper No: HT-14-1154; doi: 10.1115/1.4029852 History: Received March 27, 2014; Revised August 01, 2014; Online March 17, 2015

This study concerns optimization of shapes, locations, and dimensions of internal cooling passages within a turbine vane under severe environments. The basic aim is to achieve a design that minimizes the average temperature and ensures the structural strength. Considering the prohibitive computational cost of 3D models, numerical optimization process is performed based on 2D cross-sectional models with available experimental temperature data as boundary conditions of thermomechanical analysis. To model the cooling channels, three kinds of shape configurations, i.e., circle, superellipse, and near-surface holes, are taken into account and compared. Optimization results of 2D models are obtained by using a globally convergent method of moving asymptotes (GCMMA). Furthermore, full conjugate heat transfer (CHT) analyses are made to obtain temperature distributions of 3D models extruded from 2D ones by means of shear stress transport (SST) k-ω turbulence model. It is shown that optimization of cooling passages effectively improves the thermomechanical performances of turbine vanes in comparison with those of initial C3X vane. The maximum temperature of optimized vane could be reduced up to 50 K without degrading mechanical strength.

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Bunker, R. S., 2006, “Axial Turbine Blade Tips: Function, Design, and Durability,” AIAA J., 22(2), pp. 271–285. [CrossRef]
Hylton, L. D., Milhec, M. S., and Turner, E. R., 1983, “Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surface of Turbine Vanes,” NASA Report No. CR-168015.
Bohn, D., and Heuer, T., 2001, “Conjugate Flow and Heat Transfer Calculations of a High Pressure Turbine Nozzle Guide Vane,” AIAA Paper No. AIAA2001-3304. [CrossRef]
Facchini, B., Magi, A., and Greco, A. S. D., 2004, “Conjugate Heat Transfer Simulation of a Radially Cooled Gas Turbine Vane,” ASME Paper No. GT2004-54213. [CrossRef]
Takahashi, T., Watanabe, K., and Sakai, T., 2005, “Conjugate Heat Transfer Analysis of a Rotor Blade With Rib-Roughened Internal Cooling Passages,” ASME Paper No. GT2005-68227. [CrossRef]
Chmielniak, T., Wroblewski, W., Nowak, G., and Wecel, D., 2003, “Coupled Analysis of Cooled Gas Turbine Blades,” ASME Paper No. GT2003-38657. [CrossRef]
Dennis, B., Egorov, I., Dulicravich, G., and Yoshimura, S., 2003, “Optimization of a Large Number Coolant Passages Located Close to the Surface of a Turbine Blade,” ASME Paper No. GT2003-38051. [CrossRef]
Dulikravich, G., Martin, T., Dennis, B., and Foster, N., 1999, “Multidisciplinary Hybrid Constrained GA Optimization,” Evolutionary Algorithms in Engineering and Computer Science: Recent Advances and Industrial Applications, K.Miettinen, M. M.Makela, P.Neittaanmaki, and J.Periaux, eds., John Wiley and Sons, Jyvaskyla, Finland, Chap. 12.
Jeong, M., Dennis, B., and Yoshimura, S., 2005, “Multidimensional Clustering Interpretation and Its Application to Optimization of Coolant Passages of a Turbine Blade,” ASME J. Mech. Des., 127(2), pp. 215–221. [CrossRef]
Martin, T. J., and Dulikravich, G. S., 2001, “Aero-Thermo-Elastic Concurrent Design Optimization of Internally Cooled Turbine Blades,” Coupled Field Problems, A.Kassab, and M. H.Aliabadi, eds., WIT Press, Southampton, UK, Chap. 5.
Muller, S. D., Walther, J. H., and Koumoutsakos, P. D., 2001, “Evolution Strategies for Film Cooling Optimization,” AIAA J., 39(3), pp. 537–539. [CrossRef]
Nowak, G., Wroblewski, W., and Nowak, I., 2012, “Convective Cooling Optimization of a Blade for a Supercritical Steam Turbine,” Int. J. Heat Mass Transfer, 55(17–18), pp. 4511–4520. [CrossRef]
Nowak, G., and Wroblewski, W., 2011, “Optimization of Blade Cooling System With Use of Conjugate Heat Transfer Approach,” Int. J. Therm. Sci., 50(9), pp. 1770–1781. [CrossRef]
Nowak, G., and Nowak, I., 2012, “Shape Design of Internal Cooling Passages Within a Turbine Blade,” Eng. Optim., 44(4), pp. 449–466. [CrossRef]
Nowak, G., and Wroblewski, W., 2007, “Thermo-Mechanical Optimization of Cooled Turbine Vane,” ASME Paper No. GT2007-28196. [CrossRef]
Mangani, L., Cerutti, M., Maritano, M., and Spel, M., 2010, “Conjugate Heat Transfer Analysis of NASA C3X Film Cooled Vane With an Object-Oriented CFD Code,” ASME Paper No. GT2010-23458. [CrossRef]
Bohn, D., Ren, J., and Kusterer, K., 2003, “Conjugate Heat Transfer Analysis for Film Cooling Configurations With Different Hole Geometries,” ASME Paper No. GT2003-38369. [CrossRef]
Favaretto, C. F. F., and Funazaki, K., 2003, “Application of Genetic Algorithms to Design of an Internal Turbine Cooling System,” ASME Paper No. GT2003-38408. [CrossRef]
Talya, S. S., Chattopadhyay, A., and Rajadas, J. N., 2002, “Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade,” Eng. Optim., 34(2), pp. 175–194. [CrossRef]
Dennis, B., Egorov, I., Dulicravich, G., and Yoshimura, S., 2003, “Optimization of a Large Number Coolant Passages Located Close to the Surface of a Turbine Blade,” Proceedings of Turbo Expo 2003, Atlanta, June 16–19, Paper No. GT2003-38051. [CrossRef]
Haasenritter, A., and Weigand, B., 2004, “Optimization of the Rib Structure Inside a 2D Cooling Channel,” ASME Paper No. GT2004-53187. [CrossRef]
Kim, K. Y., and Lee, Y. M., 2007, “Design Optimization of Internal Cooling Passage With V-Shaped Ribs,” Numer. Heat Transfer –– Part A, 51(11), pp. 1103–1118. [CrossRef]
von Wolfersdorf, J., Achermann, E., and Weigand, B.,1997, “Shape Optimization of Cooling Channels Using Genetic Algorithms,” ASME J. Heat Transfer, 119(2), pp. 380–388. [CrossRef]
Ahmadi, P., Hajabdollahi, H., and Dincer, I., 2010, “Cost and Entropy Generation Minimization of a Cross-Flow Plate Fin Heat Exchanger Using Multi-Objective Genetic Algorithm,” ASME J. Heat Transfer, 133(2), p. 021801. [CrossRef]
Geb, D., Zhou, F., Demoulin, G., and Catton, I., 2013, “Genetic Algorithm Optimization of a Finned-Tube Heat Exchanger Modeled With Volume-Averaging Theory,” ASME J. Heat Transfer, 135(8), p. 082602. [CrossRef]
Svanberg, K., 1995, “A Globally Convergent Version of MMA Without Linesearch,” Proceedings of the First World Congress of Structural and Multidisciplinary Optimization, Goslar, Germany, Vol. 28, pp. 9–16.
Holman, J. P., 1997, “Heat Transfer,” Turbulent Flow in a Tube, McGraw-Hill, New York, Chap. 5.
Radovcic, Y., and Remouchamps, A., 2002, “Boss Quattro: An Open System for Parametric Design,” Struct. Multidiscip. Optim., 23(2), pp. 140–152. [CrossRef]
ANSYS Inc., 2009, ANSYS 12.1 User's Manual, Canonsburg, PA.
Dong, P., 2009, “Research on Conjugate Heat Transfer Simulation of Aeroturbine Engine Air-Cooled Vane,” Ph.D. thesis, Harbin Institute of Technology, Harbin, China.
Zheng, S. F., Song, Y. D., Xie, G. N., and Sunden, B., “An Assessment of Turbulence Models for Prediction of Conjugate Heat Transfer for a Turbine Vane With Internal Cooling Channels,” Heat Transfer Res., (in press).


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Fig. 2

Coordinate transformation from global coordinate to local coordinate

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Fig. 3

Temperature and stress contours for different cases (up: temperature distribution down: thermal stress distribution)

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Fig. 4

C3X vane work condition consisting of three computing domains: hot flow, coolant, and vane

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Fig. 5

Computing mesh of entire domains with local refinement

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Fig. 6

Predicted and measured curves of different turbulence models at the vane midspan

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Fig. 7

Contours of velocity magnitude on the midspan plane

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Fig. 8

Predicted temperature contours for different cases (up: midspan, down: 3D)

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Fig. 9

Predicted and measured temperature curves at the vane midspan of optimized configurations

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Fig. 10

Stress representations of different optimized cases by ansys and fluent

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Fig. 11

Temperature variations of different optimized cases by ANSYS and FLUENT




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