Surrogate Modeling for Optimization of a Centrifugal Compressor Impeller

Kim, Jin‐Hyuk; Choi, Jae-Ho; Kim, Kwang‐Yong

doi:10.5293/ijfms.2010.3.1.029

Cited by 37 publications

(17 citation statements)

References 14 publications

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“…(Each design based on DOE had a different element size, even though the size factor was "1", owing to different geometries of the blade). An H/J/C/L grid hexahedral mesh type was used for the inducer (inlet), vaneless diffuser, and other regions, while the O-grid mesh type was used for the nearby LE and other blade surface regions [7,8] (Figure 5). Owing to periodicity, these meshes were applied only for one blade passage consisting of one main blade and one splitter blade to reduce computational time.…”

Section: Design Parameters Boundary Valuesmentioning

confidence: 99%

“…Thus, isentropic efficiency was improved by 1.8% considering optimization of the beta distribution on the main blade. The baseline and optimized impeller were compared at several off-design points [7,8]. To do so, flow simulations were carried out at an additional five mass flow rates for reference, and the optimized impeller and results are shown in Figure 12.…”

Section: Comparison Of the Baseline (Base Main-base Splitter) And Optmentioning

confidence: 99%

“…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%

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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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Section: Design Parameters Boundary Valuesmentioning

confidence: 99%

Section: Comparison Of the Baseline (Base Main-base Splitter) And Optmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

Atac

Yun

Noh³

2018

Energies

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“…Then, a first approximation of the geometry of these components is parametrically generated and a relatively elaborate optimization process is carried out with the objective of attaining maximum efficiency within the selected parameterization, the assigned requirements and the relevant operational constraints. More recently, numerical optimization strategies based on the Radial Basis Neural Network (RBNN) have been applied by many researches 4,5,6,7,8 . Other systematic numerical optimization approaches are based on mean streamline flow analyses 9 , three-dimensional inverse methods coupled with optimization algorithms 10 , and numerical flow simulation 11 .…”

Section: Introductionmentioning

confidence: 99%

Experimental Validation of a Reduced Order for Radial Turbopump Design

Valentini

Pasini

Pace

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The paper illustrates the experimental validation of the reduced order model recently developed at Alta, Pisa (Italy), for the simultaneous and preliminary geometrical definition and non-cavitating performance prediction of centrifugal turbopumps. The proposed model has been employed to size and design the test machine, named VAMPIRE and equipped with a six-bladed radial impeller, a vaneless diffuser and a single-spiral volute. The pumping and suction performance of the machine have been determined in a series of tests in Alta's Cavitating Pump Rotordynamic Test Facility (CPRTF). The measured pumping characteristic proved to be in excellent agreement with the model predictions, thus effectively validating the design model. In addition, the experimental determination of the pump's cavitation characteristic is fully consistent with the expected suction performance of comparable machines, confirming the capability of the proposed model to generate hydrodynamically efficient turbopump designs. Nomenclatureb blade height c blade chord % c tip clearance/mean blade height ratio % m c h δ = m h mean blade height ( ) 1 2 2 m h b b = + N number of blades p , t p static and total pressures r radial coordinate, radius S r specific radius Re Reynolds number 2 Re 2 T r Ω ν = T temperature V volumetric flow rate z axial coordinate γ blade angle from axial direction ρ flow density σ blade solidity =; cavitation number ( ) 2 2 1 0.5 v T p p r σ ρΩ = − ϕ flow angle w.r.t. the radial direction Φ flow coefficient: ( ) 3 2 V r Φ Ω = ɺ χ backsweep angle from radial direction Ω impeller rotational speed

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“…Other objective functions are also used for optimization. For example, Kim et al [11] enhanced the total-to-total pressure ratio of an impeller with four design variables by constructing the curves of the shroud and the hub by Bezier curves. Samad et al [12] demonstrated the advantage of using multiple surrogates in the shape optimization of a transonic axial compressor blade and selected adiabatic efficiency, total pressure, and total temperature as objective functions.…”

Section: Introductionmentioning

confidence: 99%

Axial-Flow Ventilation Fan Design Through Multi-Objective Optimization to Enhance Aerodynamic Performance

Kim

2011

Journal of Fluids Engineering

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This paper presents an optimization procedure for axial-flow ventilation fan design through a hybrid multiobjective evolutionary algorithm (MOEA) coupled with a response surface approximation (RSA) surrogate model. Numerical analysis of a preliminary fan design is conducted by solving three-dimensional (3-D) Reynolds-averaged Navier-Stokes (RANS) equations with the shear stress transport (SST) turbulence model. The multiobjective optimization processes are performed twice to understand the coupled effects of diverse variables. The first multiobjective optimization process is conducted with three design variables defining stagger angles at the hub, mid-span, and tip, and the second is conducted with five design variables defining hub-to-tip ratio, hub cap installation distance, hub cap ratio, and the stagger angles at the mid-span and tip. Two aerodynamic performance parameters, the total efficiency and total pressure rise, are selected as the objective functions for optimization. These objective functions are numerically assessed through 3-D RANS analysis at design points sampled by Latin hypercube sampling in the design space. The optimization yields a maximum increase in efficiency of 1.8% and a 31.4% improvement in the pressure rise. The off-design performance is also improved in most of the optimum designs except in the region of low flow rate.

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Surrogate Modeling for Optimization of a Centrifugal Compressor Impeller

Cited by 37 publications

References 14 publications

Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger

Experimental Validation of a Reduced Order for Radial Turbopump Design

Axial-Flow Ventilation Fan Design Through Multi-Objective Optimization to Enhance Aerodynamic Performance

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