Aerodynamic optimization of turbomachinery cascades using Euler/boundary-layer coupled genetic algorithms

Öksüz, Özhan; Akmandor, I. Sinan

doi:10.2514/6.2001-2577

Cited by 3 publications

(1 citation statement)

References 7 publications

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“…Fujita (1996) employed genetic algorithm-based optimization to estimate the optimal solution to the planning problem observed in energy plant configurations. Genetic algorithm was used by Oksuz (2001) to estimate the optimum aerodynamic performance of a turbine cascade. Results from the author's work show that the highest tangential force was actualized for a higher flow turning, a wider pitch, and a thicker cascade.…”

Section: Introductionmentioning

confidence: 99%

The Impact of Compressor Degradation on The Optimized Fleet Compositions, Optimized Thermal Efficiencies, and The Operations & Maintenance Cost of Fleets of a Reheat Engine Running on Associated Gas Fuel

Obhuo

Okuma²,

Aziaka

2023

JAETS

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Associated gas is a viable source of fuel for industrial gas turbines. Flaring of this fuel resource has not only resulted in environmental pollution and deterioration but also huge energy and economic loss. TURBOMATCH, a Cranfield University performance simulation software was used in modeling a hypothetical but realistic 296MW reheat gas turbine engine.The study was carried out using one clean fleet and three degraded fleets – the optimistic, medium, and pessimistic. Optimization of the fleet compositions and thermal efficiencies were achieved using Genetic algorithm. Detailed operations and maintenance costs analysis for the various fleets were carried out. .Results from the optimization show the optimized fleet compositions, from the various fleets and their turbine entry temperatures for 20 years life span of the project. the result from the 11th to the 20th year of the project, only one unit of engine was left due to engine divestment. Results of the optimized efficiencies for all the fleets show a gradual reduction in optimized efficiencies over the years of the project. Similarly, for all the scenarios considered, from the 11th to the 20th year of the project, with only one unit of engine left, the optimized efficiency trend is observed to be Clean > Optimistic > Medium > Pessimistic.Results from the fleets operations and maintenance costs show that the clean, optimistic, medium, and pessimistic degraded fleets have total operations and maintenance costs to be 1.224, 1.242, 1.265, and 1.297 billion US dollars respectively. Engine degradation resulted to 1.4%, 3.3%, and 5.9% increase in the operations and maintenance costs of the optimistic, medium, and pessimistic degraded fleets respectively.The results, approach and methodology presented in this paper would be a very useful decision-making tool for investors and governments who would want to invest in the economic utilization of associated gas using gas turbines.

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Section: Introductionmentioning

confidence: 99%

The Impact of Compressor Degradation on The Optimized Fleet Compositions, Optimized Thermal Efficiencies, and The Operations & Maintenance Cost of Fleets of a Reheat Engine Running on Associated Gas Fuel

Obhuo

Okuma²,

Aziaka

2023

JAETS

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Numerical Modeling and Research of 3D Turbine Stage

Ilieva

2014

Advanced Structured Materials

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Multi-Objective Aerodynamic Optimization of Axial Turbine Blades Using a Novel Multilevel Genetic Algorithm

Öksüz

Akmandor

2010

Journal of Turbomachinery

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In this paper, a new multiploid genetic optimization method handling surrogate models of the CFD solutions is presented and applied for a multi-objective turbine blade aerodynamic optimization problem. A fast, efficient, robust, and automated design method is developed to aerodynamically optimize 3D gas turbine blades. The design objectives are selected as maximizing the adiabatic efficiency and torque so as to reduce the weight, size, and cost of the gas turbine engine. A 3D steady Reynolds averaged Navier–Stokes solver is coupled with an automated unstructured grid generation tool. The solver is verified using two well-known test cases. The blade geometry is modeled by 36 design variables plus the number of blade variables in a row. Fine and coarse grid solutions are respected as high- and low-fidelity models, respectively. One of the test cases is selected as the baseline and is modified by the design process. It was found that the multiploid multi-objective genetic algorithm successfully accelerates the optimization and prevents the convergence with local optimums.

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Aerodynamic optimization of turbomachinery cascades using Euler/boundary-layer coupled genetic algorithms

Cited by 3 publications

References 7 publications

The Impact of Compressor Degradation on The Optimized Fleet Compositions, Optimized Thermal Efficiencies, and The Operations & Maintenance Cost of Fleets of a Reheat Engine Running on Associated Gas Fuel

The Impact of Compressor Degradation on The Optimized Fleet Compositions, Optimized Thermal Efficiencies, and The Operations & Maintenance Cost of Fleets of a Reheat Engine Running on Associated Gas Fuel

Numerical Modeling and Research of 3D Turbine Stage

Multi-Objective Aerodynamic Optimization of Axial Turbine Blades Using a Novel Multilevel Genetic Algorithm

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