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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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Figures

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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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