Reacting Navier-Stokes Nozzle Contour Design Optimization

2005 ◽  
Author(s):  
Frederick Shope ◽  
Kenneth Tatum
Keyword(s):  
Design Optimization ◽  
Navier Stokes ◽  
Nozzle Contour ◽  
Contour Design

Aerodynamic Design Optimization of an Axial Flow Compressor Rotor

2002 ◽  
Author(s):  
Chan-Sol Ahn ◽  
Kwang-Yong Kim
Keyword(s):  
Design Optimization ◽  
Response Surface ◽  
Computing Time ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Axial Flow ◽  
Navier Stokes ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Design Variables

Design optimization of a transonic compressor rotor (NASA rotor 37) using the response surface method and three-dimensional Navier-Stokes analysis has been carried out in this work. The Baldwin-Lomax turbulence model was used in the flow analysis. Three design variables were selected to optimize the stacking line of the blade. Data points for response evaluations were selected by D-optimal design, and linear programming method was used for the optimization on the response surface. As a main result of the optimization, adiabatic efficiency was successfully improved. It was found that the optimization process provides reliable design of a turbomachinery blade with reasonable computing time.

High-lift design optimization using Navier-Stokes equations

1996 ◽  
Vol 33 (3) ◽  
pp. 499-504 ◽  
Author(s):  
S. Eyi ◽  
K. D. Lee ◽  
S. E. Rogers ◽  
D. Kwak
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations

Optimal Design for Impeller of a Sludge Pump Using Design of Experiment

2019 ◽  
Author(s):  
Jeong-Min Jin ◽  
Hyo-Geun Ji ◽  
Youn-Jea Kim
Keyword(s):  
Optimal Design ◽  
Design Optimization ◽  
Design Of Experiment ◽  
Design Theory ◽  
Flow Analysis ◽  
Optimization Techniques ◽  
Navier Stokes ◽  
Pump Impeller ◽  
Computational Fluid Dynamics Cfd ◽  
Design Factors

Abstract Recently, many studies carried out to improve the performance of the pump with shape changes. In this paper, impeller optimization is performed to improve the pump performance. Design optimization techniques for the sludge pump impellers have been developed by using computational fluid dynamics (CFD) and optimal design theory. This paper describes the design optimization of a sludge pump impeller based on Response Surface Method (RSM) coupled with Navier-Stokes flow analysis. In particular, RSM which was based on the results of the design of experiment (DOE) helps to achieve the optimum point. In order to optimize the shape of the impeller, the thickness and the height of the blade were set as design factors. As a result, it was confirmed that the efficiency and the head were improved by 11.2% and 6.67%, respectively, compared to the referenced model.

Influence of Base Nozzle Contour Design on Flow Instabilities in Dual Bell Nozzle at Low Altitude Operation

2011 ◽  
Author(s):  
Koichi Yonezawa ◽  
Dzianis Proshchanka ◽  
Kasumi Araki ◽  
Hiroaki Tsukuda ◽  
Yoshinobu Tsujimoto ◽  
...  
Keyword(s):  
Flow Instabilities ◽  
Nozzle Contour ◽  
Low Altitude ◽  
Contour Design ◽  
Dual Bell

Aerodynamic design optimization of a compressor rotor with Navier—Stokes analysis

2003 ◽  
Vol 217 (2) ◽  
pp. 179-183 ◽  
Author(s):  
C-S Ahn ◽  
K-Y Kim
Keyword(s):  
Design Optimization ◽  
Response Surface ◽  
Computing Time ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Design Variables ◽  
Reliable Design

Design optimization of a transonic compressor rotor (NASA rotor 37) using the response surface method (RSM) and three-dimensional Navier-Stokes analysis has been carried out in this work. The Baldwin—Lomax turbulence model was used in the flow analysis. Three design variables were selected to optimize the stacking line of the blade. Data points for response evaluations were selected by D-optimal i design, and a linear programming method was used to optimize the response surface. As a main result of the optimization, adiabatic efficiency was successfully improved. It was found that the optimization process provides reliable design of a turbomachinery blade with reasonable computing time.

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