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

Abstract

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.

Shape optimization of turbine blade cooling system using topological sensitivity analysis method

“…In order to improve the behavior of this cooling system, a considerable effort has been devoted to optimize size, location, and shape of the created holes. Various approaches and techniques have been developed and exploited to address this issue [1][2][3].…”

“…3. The variation of the cost function with respect to a small topological perturbation of the domain is computed and Figure 1 The turbine blade vane with cooling holes (see [1])…”

Constructal design for gas-turbine blade based on minimization of maximum thermal resistance

“…The optimization of GTB's cooling problem was also studied by using constructal theory [10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25]. Bejan and Lorente (Ref.…”

Analysis of a Coupled Micro- and Triple- Impingement Cooling Configuration in the C3X Vane

“…The edges most often focused on are the leading and the trailing edges of the airfoil, the tip, and the end walls of the turbine. To accomplish the desired increase of temperature in a turbine to produce the most desirable turbine system, the temperature and stress of the blade need to be taken into account simultaneously (Wang, 2015). One way to incorporate these new challenges can be seen by numerous cooling configurations, optimization methods, and extensive conjugate heat transfer (CHT) analyses that have been implemented to test the overall cooling capabilities of heat transfer in turbine blades (Wang, 2015).…”

“…To accomplish the desired increase of temperature in a turbine to produce the most desirable turbine system, the temperature and stress of the blade need to be taken into account simultaneously (Wang, 2015). One way to incorporate these new challenges can be seen by numerous cooling configurations, optimization methods, and extensive conjugate heat transfer (CHT) analyses that have been implemented to test the overall cooling capabilities of heat transfer in turbine blades (Wang, 2015). The overall need of cooling of the turbine region is displayed by the direct forms of cooling techniques utilized in industry such as, impingement cooling, pin-fin cooling, film cooling, and transpiration cooling configurations.…”