Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade

Talya, Shashishekara S.; Chattopadhyay, Aditi; Rajadas, John

doi:10.1080/03052150210917

Cited by 32 publications

(18 citation statements)

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“…the outflow of the coolant from a single passage in film cooling. Talya et al (2002) took film cooling into consideration in the process of the profile shape optimization, but its structure was fixed and so were the inner channels, which were only scaled according to the size and shape of the profile. For several years now Dulikravich and his team (Martin and Dulikravich 2001, Jeong et al 2003, Dennis et al 2003a have been doing research on various problems concerning optimization of turbine blade cooling with focus on flow, thermal and strength criteria.…”

Section: G Nowakmentioning

confidence: 99%

Optimization of an airfoil cooling system using a Pareto dominance approach

Nowak

2010

Engineering Optimization

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The article deals with the optimization of the airfoil internal cooling system in order to find the most efficient distribution of passages to reduce thermal stress and, at the same time, retain the temperature at a permissible level. Another objective is to carry out the task with as little coolant as possible. The optimization is approached with the evolutionary algorithm, and thermo-mechanical FEM simulations are used for the assessment of the particular cooling system candidates. Since the optimization involves several criteria, the multi-objective approach needs to be applied. The optimization process may focus either on the scaled function solution or on finding the front of optimal solutions (Pareto optimal). In this article the latter approach is implemented and compared to the scaled function solution.

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Section: G Nowakmentioning

confidence: 99%

Optimization of an airfoil cooling system using a Pareto dominance approach

Nowak

2010

Engineering Optimization

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“…Today, computational fluid dynamics (CFD) techniques are widely used to capture more detailed flow physics and design more efficient gas turbine engine components (Talya et al 2002, Gorell et al 2006, Chen et al 2008. However, in flow fields sensitive to turbulence properties, such as film cooling or heat transfer rates (Dornberger et al 2000), CFD provides diverse results depending on the turbulence model used.…”

Section: Introductionmentioning

confidence: 99%

Design of a 160% pitch passage for cascade experiments using optimization methods

Cho

Kim

et al. 2010

Engineering Optimization

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A linear turbine cascade experimental apparatus often consists of only a few cascade blades. Advantages to this arrangement are increased from using larger cascade blades and easier optical access. However, fewer cascade blades in the cascade row make it difficult to establish periodic flow conditions between blades. In this study, a 160% pitch passage for cascade experiments with a single blade is designed to satisfy infinite cascade flow conditions without any flow control or tailboards. Fourteen geometric design variables are applied to the design of a 160% pitch passage by using a gradient-based optimization method and a genetic algorithm. Flow structures within a passage designed with a genetic algorithm are closer to the infinite cascade flow conditions than those obtained with a gradient-based method. The results show that infinite cascade flow conditions can be obtained by modifying only the passage walls of the cascade experimental apparatus.

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“…Today, computational fluid dynamics (CFD) techniques are widely used to capture more detailed flow physics and design more efficient gas turbine engine components [4][5][6][7]. However, in flow fields sensitive to turbulence properties such as film cooling or heat transfer rates [8], CFD provides diverse results depending on the turbulence model used.…”

Section: Introductionmentioning

confidence: 99%

One-pitch passage designed inversely with a single blade for cascade experiments

et al. 2010

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A linear cascade experimental apparatus often consists of only a few cascade blades. Advantages to this experimental arrangement are increased by the use of larger cascade blades, a lower mass flow rate, a corresponding decrease in required power, and easier optical access within the cascade passage. However, fewer cascade blades in the cascade row make it difficult to establish periodic flow conditions between blades compared to infinite cascade model experiments. Generally, removing fluid from the cascade walls or adjusting tailboards located downstream of the cascade are common methods to establish periodic flow conditions through the cascade blades. In this study, a passage for cascade experiments is designed to satisfy infinite cascade flow conditions without any flow control or tailboards. A one-pitch at cascade row is adopted as its width and only a single cascade blade is installed within the passage. The surface isentropic Mach number distribution on the blade is chosen for the existence of infinite cascade flow conditions, and 14 geometric design variables related to the passage shape are applied to the design of a one-pitch passage by using a genetic algorithm. Flow structures within a passage designed using a genetic algorithm match with those obtained with the infinite cascade flow condition. Computed results obtained with a single cascade blade show that infinite cascade flow conditions can be obtained by modifying only the passage walls of the cascade experimental apparatus.

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Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade

Cited by 32 publications

References 0 publications

Optimization of an airfoil cooling system using a Pareto dominance approach

Optimization of an airfoil cooling system using a Pareto dominance approach

Design of a 160% pitch passage for cascade experiments using optimization methods

One-pitch passage designed inversely with a single blade for cascade experiments

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