scholarly journals Applications of an Improved Aerodynamic Optimization Method on a Low Reynolds Number Cascade

Processes ◽  
2020 ◽  
Vol 8 (9) ◽  
pp. 1150 ◽  
Author(s):  
Shuyi Zhang ◽  
Bo Yang ◽  
Hong Xie ◽  
Moru Song
Keyword(s):  
Reynolds Number ◽  
Simulated Annealing Algorithm ◽  
Design Method ◽  
Incidence Angle ◽  
Thickness Distribution ◽  
Low Reynolds Number ◽  
Pressure Coefficient ◽  
Optimization Method ◽  
Aerodynamic Optimization ◽  
Low Reynolds

The effect of cascade aerodynamic optimization on turbomachinery design is very significant. However, for most traditional cascade optimization methods, aerodynamic parameters are considered as boundary conditions and rarely directly used as the optimization variables to realize optimization. Given this problem, this paper proposes an improved cascade aerodynamic optimization method in which an incidence angle and nine geometric parameters are used to parameterize the cascade and one modified optimization algorithm is adopted to find the cascade with the optimal aerodynamic performance. The improved parameterization approach is based on the Non-Uniform Rational B-Splines (NURBS) method, the camber line superposing thickness distribution molding (CLSTDM) method, and the plane cascade design method. To rapidly and effectively find the cascade with the largest average lift-drag ratio within a certain range of incidence angles, modified particle swarm optimization combined with the modified very fast simulated annealing algorithm (PSO-MVFSA) is adopted. To verify the feasibility of the method, a cascade with NACA4412 and a practical cascade are optimized. It is found that the average lift-drag ratios of two optimal performance cascades are respectively increased by 13.38% and 15.21% in comparison to those of two original cascades. Meanwhile, through optimizing the practical cascade of the Blade D500, under different volume flow rates, the pressure coefficient of the optimized cascade is increased by an average of more than 6.12% compared to that of the prototype, and the average efficiency is increased by 11.15%. Therefore, this improved aerodynamic optimization method is reliable and feasible for the performance improvement of cascades with a low Reynolds number.

Evolutionary Algorithm Based Multi-Objective Aerodynamics Optimization Method for Low Reynolds Number Airfoil

2014 ◽  
Vol 660 ◽  
pp. 487-491 ◽  
Author(s):  
Lavi R. Zuhal ◽  
Yohanes Bimo Dwianto ◽  
Pramudita Satria Palar
Keyword(s):  
Reynolds Number ◽  
Aerodynamic Characteristic ◽  
Low Reynolds Number ◽  
Optimization Method ◽  
Aerodynamic Characteristics ◽  
Population Based ◽  
Nsga Ii ◽  
Multi Objective ◽  
Low Reynolds ◽  
Low Reynolds Number Airfoil

This paper presents the development of multi-objective population-based optimization method, called Non-dominated Sorting Genetic Algorithm II (NSGA-II), to optimize the aerodynamic characteristic of a low Reynolds number airfoil. The optimization is performed by changing the shape of the airfoil to obtain geometry with the best aerodynamic characteristics. The results of the study show that the developed optimization tool, coupled with modified PARSEC parameterization, has yielded optimum airfoils with better aerodynamic characteristics compared to original airfoil. Additionally, it is found that the developed method has better performance compared to similar methods found in literature.

Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition: Part 2 — Experimental and Numerical Analysis

2003 ◽  
Author(s):  
Heinz-Adolf Schreiber ◽  
Wolfgang Steinert ◽  
Toyotaka Sonoda ◽  
Toshiyuki Arima
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Guide Vane ◽  
Incidence Angle ◽  
Low Reynolds Number ◽  
Aerodynamic Characteristics ◽  
Low Loss ◽  
Design And Optimization ◽  
Negative Effect ◽  
Low Reynolds

Part 1 of this paper describes the design and optimization of two high turning subsonic compressor cascades operating as an outlet guide vane (OGV) behind a single stage low pressure turbine at low Reynolds number condition (Re = 1.3×105). In the numerical optimization algorithm, the design point and off-design performance has been considered in an objective function to achieve a wide low loss incidence range. The objective of the present paper is to examine some of the characteristics describing the new airfoils as well as to prove the reliability of the design process and the applied flow solver. Some aerodynamic characteristics for the two new airfoils and a conventional controlled diffusion airfoil (CDA), have been extensively investigated in the cascade wind tunnel of DLR Cologne. For an inlet Mach number of 0.6 the effect of Reynolds number and incidence angle on each airfoil performance is discussed, based on experimental and numerical results. For an interpretation of the airfoil boundary layer behavior, results of some boundary layer calculations are compared to oil flow visualization pictures. The design goal of an increased low loss incidence range at low Reynolds number condition could be confirmed without having a negative effect on the high Reynolds number region.

Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition—Part I: Design and Optimization

2004 ◽  
Vol 126 (3) ◽  
pp. 350-359 ◽  
Author(s):  
Toyotaka Sonoda ◽  
Yoshihiro Yamaguchi ◽  
Toshiyuki Arima ◽  
Markus Olhofer ◽  
Bernhard Sendhoff ◽  
...  
Keyword(s):  
Reynolds Number ◽  
High Performance ◽  
Guide Vane ◽  
Incidence Angle ◽  
Low Reynolds Number ◽  
Three Dimensional ◽  
Optimization Methods ◽  
Superior Performance ◽  
Experimental Investigations ◽  
Low Reynolds

High performance compressor airfoils at a low Reynolds number condition at Re=1.3×105 have been developed using evolutionary algorithms in order to improve the performance of the outlet guide vane (OGV), used in a single low pressure turbine (LPT) of a small turbofan engine for business jet aircrafts. Two different numerical optimization methods, the evolution strategy (ES) and the multi-objective genetic algorithm (MOGA), were adopted for the design process to minimize the total pressure loss and the deviation angle at the design point at low Reynolds number condition. Especially, with respect to the MOGA, robustness against changes of the incidence angle is considered. The optimization process includes the representation of the blade geometry, the generation of a numerical grid and a blade-to-blade analysis using a quasi-three-dimensional Navier-Stokes solver with a k-ω turbulence model including a newly implemented transition model to evaluate the performance. Overall aerodynamic performance and boundary layer properties for the two optimized blades are discussed numerically. The superior performance of the two optimized airfoils is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which are presented in Part II of this paper.

Advanced High-Turning Compressor Airfoils for Low Reynolds Number Condition—Part II: Experimental and Numerical Analysis

2004 ◽  
Vol 126 (4) ◽  
pp. 482-492 ◽  
Author(s):  
Heinz-Adolf Schreiber ◽  
Wolfgang Steinert ◽  
Toyotaka Sonoda ◽  
Toshiyuki Arima
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Guide Vane ◽  
Incidence Angle ◽  
Low Reynolds Number ◽  
Aerodynamic Characteristics ◽  
Low Loss ◽  
Design And Optimization ◽  
Negative Effect ◽  
Low Reynolds

Part I of this paper describes the design and optimization of two high turning subsonic compressor cascades operating as an outlet guide vane (OGV) behind a single stage low pressure turbine at low Reynolds number condition Re=1.3×105. In the numerical optimization algorithm, the design point and off-design performance has been considered in an objective function to achieve a wide low loss incidence range. The objective of the present paper is to examine some of the characteristics describing the new airfoils as well as to prove the reliability of the design process and the applied flow solver. Some aerodynamic characteristics for the two new airfoils and a conventional controlled diffusion airfoil (CDA), have been extensively investigated in the cascade wind tunnel of DLR Cologne. For an inlet Mach number of 0.6 the effect of Reynolds number and incidence angle on each airfoil performance is discussed, based on experimental and numerical results. For an interpretation of the airfoil boundary layer behavior, results of some boundary layer calculations are compared to oil flow visualization pictures. The design goal of an increased low loss incidence range at low Reynolds number condition could be confirmed without having a negative effect on the high Reynolds number region.

scholarly journals Convective heat transfer characteristics of low Reynolds number nanofluid flow around a circular cylinder

10.30544/242 ◽  
2017 ◽  
Vol 23 (1) ◽  
pp. 83-97
Author(s):  
Yacine Khelili ◽  
Abderrazak Allali ◽  
Rafik Bouakkaz
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Fluid Flow ◽  
Volume Fraction ◽  
Low Reynolds Number ◽  
Pressure Coefficient ◽  
Flow Characteristics ◽  
Nano Particles ◽  
Low Reynolds ◽  
Energy Equations

Numerical investigation of heat transfer phenomena of low Reynolds number nano-fluid flow over an isothermal cylinder is presented in this paper. Steady state governing equations (continuity, N–S and energy equations) have been solved using finite volume method. Stationary heat transfer, and flow characteristics over the cylinder have been studied for water based copper nanofluid with different solid fraction values. The effect of volume fraction of nano- particles on the fluid flow and heat transfer were investigated numerically. It was found that at a given Nusselt number, drag coefficient, re-circulation length, and pressure coefficient increase by increasing the volume fraction of nano-particles.

scholarly journals An Inverse Design Method for Cascades for Low-Reynolds Number Flow

2012 ◽  
Vol 2012 ◽  
pp. 1-18 ◽  
Author(s):  
Martin Böhle
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Design Method ◽  
Low Reynolds Number ◽  
Design Procedure ◽  
Inverse Design ◽  
Suction Surface ◽  
Present Contribution ◽  
Reynolds Number Flow ◽  
Low Reynolds

Inverse design of cascades for low Reynolds number can be applied for the aerodynamic development of fans and compressors. The present contribution describes a complete design procedure by taking into account the transition from laminar to turbulent boundary layer flow. A shape factor distribution is prescribed along the suction surface of the blades. The inverse boundary layer calculation is performed by the application of a finite difference method. On the pressure side the velocity distribution is prescribed in such a way that the given flow angles in front of and behind the cascade are realized. An inverse calculation based on potential theory is applied in order to determine the geometry of the cascade. At the end of the present contribution a cascade is designed by the described inverse design procedure and the flow is simulated by the application of CFD.

Vortex control strategy for unsteady aerodynamic optimization of a plunging airfoil at a low Reynolds number

2021 ◽  
Vol 33 (11) ◽  
pp. 117110
Author(s):  
Lei Wang ◽  
Li-Hao Feng ◽  
Yan Liang ◽  
Yi-Long Chen ◽  
Zhen-Yao Li
Keyword(s):  
Reynolds Number ◽  
Control Strategy ◽  
Low Reynolds Number ◽  
Aerodynamic Optimization ◽  
Vortex Control ◽  
Unsteady Aerodynamic ◽  
Low Reynolds

Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition: Part 1 — Design and Optimization

2003 ◽  
Author(s):  
Toyotaka Sonoda ◽  
Yoshihiro Yamaguchi ◽  
Toshiyuki Arima ◽  
Markus Olhofer ◽  
Bernhard Sendhoff ◽  
...  
Keyword(s):  
Reynolds Number ◽  
High Performance ◽  
Guide Vane ◽  
Incidence Angle ◽  
Low Reynolds Number ◽  
Three Dimensional ◽  
Optimization Methods ◽  
Superior Performance ◽  
Experimental Investigations ◽  
Low Reynolds

A high performance compressor airfoil at a low Reynolds number condition (Re = 1.3×105) has been developed using evolutionary algorithms in order to improve the performance of the outlet guide vane (OGV), used in a single low pressure turbine (LPT) of a small turbofan engine for business jet aircrafts. Two different numerical optimization methods, the Evolution Strategy (ES) and the Multi-Objective Genetic Algorithm (MOGA), were adopted for the design process to minimize the total pressure loss and the deviation angle at the design point at low Reynolds number condition. Especially, with respect to the MOGA, robustness against changes of the incidence angle is considered. The optimization process includes the representation of the blade geometry, the generation of a numerical grid and a blade-to-blade analysis using a quasi-three-dimensional (Q3D) Navier-Stokes solver with a k-ω turbulence model including a newly implemented transition model to evaluate the performance. Overall aerodynamic performance and boundary layer properties for the two optimized blades are discussed numerically. The superior performance of the two optimized airfoils is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which are presented in Part 2 of this paper.

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