Multipoint and Multiobjective Optimization of a Centrifugal Compressor Impeller Based on Genetic Algorithm

Li, Xiaojian; Liu, Zhengxian; Lin, Yujing

doi:10.1155/2017/6263274

Cited by 24 publications

(20 citation statements)

References 26 publications

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“…The Pareto front method disregards any weighting applied to each objective and aims to achieve a set of designs located along a 'front' of best performance relative to each objective and any combination of the specified objectives. A Pareto method was successfully implemented by Li et al (2017) to optimize an impeller with focus on stall performance. In this thesis η (01−4),DP , m choke and ΔP R (01−05),stall were chosen as objectives.…”

Section: Objectivesmentioning

confidence: 99%

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Ochabski

Spuy

Hildebrandt³

2020

Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small

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A parametrization method for the simultaneous optimization of the impeller and diffuser of a mixed flow compressor stage across a wide geometrical diversity is presented. The optimization focused on determining the optimal mixed flow (meridional) angle for a predefined set of constraints. The number of parameters required to achieve the large geometric diversity associated with a variable mixed flow angle was greatly reduced by coupling the endwall and camber Bézier control points with user-defined functions. The influence of geometric features on design performance was assessed using a Pearson correlation coefficient map. It was observed that stage total-to-static pressure ratio, and efficiency, were strongly influenced by diffuser outlet passage height and diffuser vane wrap angle. This was due to these parameters’ control of flow separation magnitude at the diffuser hub in the radial-to-axial bend. The method improved design point efficiency by 4.24 percentage points (to 86.24%) and increased the operating range by 6.7% at the cost of a decreased design point pressure rise, when compared to the baseline design.

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Section: Objectivesmentioning

confidence: 99%

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Ochabski

Spuy

Hildebrandt³

2020

Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small

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“…Limited by lacking of experimental data, dozens of prewhirl compressor stages designed based on Figure 7 and validated by numerical simulations are used to check the general matching principle. The numerical method for centrifugal compressor has already been presented in authors' previous articles, 2,3 and it is not repeated here.…”

Section: Throat Area Under Prewhirlmentioning

confidence: 99%

“…Global optimization methods are now often used to find the trade-off between high performance and compactness of compressors. 2,3 A good preliminary design can help to speed up the optimizaiton of compressors. One-dimensional method is usually applied to obtain such a design.…”

Section: Introductionmentioning

confidence: 99%

A new methodology for preliminary design of centrifugal impellers with prewhirl

Zhao

Liu

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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The overall trend of centrifugal compressor design is to strive for high aerodynamic performance and high flow capacity products. A new methodology is derived to implement a preliminary design for high flow capacity centrifugal impeller with and without prewhirl. First, several new non-dimensional equations connecting impeller geometric and aerodynamic parameters are derived for the maximum flow capacity. The effects of prewhirl on mass flow function, inlet diameter ratio and work coefficient are discussed, respectively. Then, based on these equations, a series of design diagrams are drawn to extract the universal rules in centrifugal impeller design with prewhirl. Some physical limits of design maps are also discussed. Finally, the throat area of impeller is discussed under prewhirl, and the matching principle between prewhirl impeller and vaned diffuser is derived and validated. The proposed method can be used to design a new centrifugal compressor, or to evaluate the design feasibility and the challenge of a given design specification.

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“…Near-wall spacing to y + for the impeller was calculated in the TurboGrid by setting the Reynolds number of the flow. Equation (6) [24] describes the y + with respect to the Reynolds number as follows:…”

Section: Design Parameters Boundary Valuesmentioning

confidence: 99%

“…Due to their higher compression ratio in a single stage with a low mass flow rate and lower installation space requirements compared with axial compressors, centrifugal compressors have become more attractive to researchers. Therefore, several optimization techniques have been suggested to improve compressor design [1][2][3][4][5][6]. In particular, metamodel coupled optimization techniques incorporating three-dimensional Reynold-average Naver-Stokes (RANS) analyses have been suggested by several authors to enhance performance parameters such as efficiency, pressure ratio, and operation range [7][8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

Atac

Yun

Noh³

2018

Energies

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Abstract:This study presents an aerodynamic design optimization of a micro radial compressor impeller on a turbocharger used in a 0.8 L two-cylinder gasoline engine. In the conventional design optimization of the impeller, the hub and shroud curve of the main blade is commonly parameterized with a beta distribution, and splitter blades are generally considered short versions of the full blade. However, geometrical parameterizations in our study mainly focus on the beta distribution of a full blade, and it is parameterized differently from the conventional way. Eight parameters are selected as design variables for the beta distribution. To maximize the isentropic efficiency, design points that are created by Design of Experiment (DOE) are evaluated through single-objective optimization coupled with a non-parametric regression surrogate model. Furthermore, the splitter leading edge location on the meridional plane is investigated to enhance the performance of the impeller after the optimization process. The results show that total efficiency enhancement of approximately 2.2% is achieved. Furthermore, the findings show that a full blade beta distribution and the splitter leading edge location are sufficient parameters to optimize the impeller, and, with the proposed optimization, splitter blades are no longer copies of the full blade for each application.

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Multipoint and Multiobjective Optimization of a Centrifugal Compressor Impeller Based on Genetic Algorithm

Cited by 24 publications

References 26 publications

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

A new methodology for preliminary design of centrifugal impellers with prewhirl

Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

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