A Study of Optimization of Blade Section Shape for a Steam Turbine

Chung, Kyung-Nam; Kim, Yang-Ik; Sung, Ju-Heon; Chung, I.S.; Shin, Sang-Beom

doi:10.1115/fedsm2005-77385

Cited by 5 publications

(3 citation statements)

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“…Several other studies on shape optimization of turbomachinery blades have been undertaken, with specific emphases on maximum camber [7], camber line [8][9], airfoil thickness [10], thickness location [11], trailing edge (TE) radius [12], and others.…”

Section: Introductionmentioning

confidence: 99%

Performance enhancement of axial fan blade through multi-objective optimization techniques

et al. 2010

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This paper presents an axial fan blade design optimization method incorporating a hybrid multi-objective evolutionary algorithm (hybrid MOEA). In flow analyses, Reynolds-averaged Navier-Stokes (RANS) equations were solved using the shear stress transport turbulence model. The numerical results for the axial and tangential velocities were validated by comparing them with experimental data. Six design variables relating to the blade lean angle and the blade profile were selected through Latin hypercube sampling of design of experiments (DOE) to generate design points within the selected design space. Two objective functions, namely, total efficiency and torque, were employed, and multi-objective optimization was carried out, to enhance the performance. A surrogate model, Response Surface Approximation (RSA), was constructed for each objective function based on the numerical solutions obtained at the specified design points. The Non-dominated Sorting of Genetic Algorithm (NSGA-II) with local search was used for multi-objective optimization. The Pareto-optimal solutions were obtained, and a trade-off analysis was performed between the two conflicting objectives in view of the design and flow constraints. It was observed that, by the process of multi-objective optimization, the total efficiency was enhanced and the torque reduced. The mechanisms of these performance improvements were elucidated by analysis of the Pareto-optimal solutions.

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Section: Introductionmentioning

confidence: 99%

Performance enhancement of axial fan blade through multi-objective optimization techniques

et al. 2010

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“…Liu et al [4] have studied the influence ofairfoil thickness on the fan performance and C. Sarrafetal [5] have studied blade thickness effects on the overall and localperformances of a Controlled Vortex Designed axial-flow fan.In aeronautics and in the automotive industry, changing theblade thickness has been used for many years as an efficient wayto modify the lift and drag characteristics and the boundary layersdetachment process [6,7]. Several other studies on shape optimization of turbomachinery blades have been undertaken, with specific emphases on maximum camber [8], camber line [9,10], airfoil thickness [11], thickness location [12], trailing edge (TE) radius [13], and others.…”

Section: Introductionmentioning

confidence: 99%

Effect of Different Airfoils on Performance of Axial Fan

Zhou

Yuan

et al. 2014

AMR

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Airfoil has great influence on the performance of axial fan. In order to study performance of axial fan. Four kinds of airfoils have been applied to optimize the impeller of axial fan. The 3D internal flows of the axial fan under different operating conditions were simulated based on a steady numerical method in ANSYS CFX 14.5. The results show that the curve of total pressure of the fan with LS airfoil blades is slightly steeper, and that of the fan with CLARK-Y(C=11.7%) (C is the blade thickness ratio) airfoil blades is relatively flat. The total pressure of the axial fan with CLARK-Y(C=11.7%) blades is highest among others. While achieving the highest efficiency in all the operating conditions except the lowest flow rate. Moreover, the blades loading of the CLARK-Y(C=11.7%) airfoil blades fan is entirely more uniform than that in others. The turbulent kinetic energy distribution on the leading edge of blades shows that the axial fan with CLARK-Y(C=11.7%) airfoil blades fan can improve the turbulent kinetic energy effectively.

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“…Cubic spline and Bazier curve based parameterizations have helped to reduce the design variables to modify the camber line and aerofoil profiles [30][31][32][33][34][35][36][37][38][39].…”

Section: Objective Functions and Design Variablesmentioning

confidence: 99%

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

Samad¹,

Kim²

2009

International Journal of Fluid Machinery and Systems

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Recent development of high speed computers and use of optimization techniques have given a big momentum of turbomachinery design replacing expensive experimental cost as well as trial and error approaches. The surrogate based optimization techniques being used for aerodynamic turbomachinery designs coupled with Reynolds-averaged NavierStokes equations analysis involve single-and multi-objective optimization methods. The objectives commonly tried to improve were adiabatic efficiency, pressure ratio, weight etc. Presently coupling the fluid flow and structural analysis is being tried to find better design in terms of weight, flutter and vibration, and turbine life. The present article reviews the surrogate based optimization techniques used recently in turbomachinery shape optimizations.

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A Study of Optimization of Blade Section Shape for a Steam Turbine

Cited by 5 publications

References 0 publications

Performance enhancement of axial fan blade through multi-objective optimization techniques

Performance enhancement of axial fan blade through multi-objective optimization techniques

Effect of Different Airfoils on Performance of Axial Fan

Surrogate Based Optimization Techniques for Aerodynamic Design of Turbomachinery

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