Optimization procedure for improved sonic boom and aerodynamic performance using a multiobjective formulation technique

1995 ◽  
Author(s):  
J Narayan ◽  
A Chattopadhyay ◽  
N Pagaldipti ◽  
S Cheung
Keyword(s):  
Optimization Procedure ◽  
Aerodynamic Performance ◽  
Sonic Boom

Optimization procedure for reduced sonic boom in high speed flight

1995 ◽  
Author(s):  
A Chattopadhyay ◽  
J Narayan ◽  
N Pagaldipti ◽  
X Wensheng ◽  
S Cheung
Keyword(s):  
High Speed ◽  
Optimization Procedure ◽  
Sonic Boom

Multi-Disciplinary Optimization of a Centrifugal Compressor for Micro-Turbine Applications

2016 ◽  
Author(s):  
Andrea Perrone ◽  
Luca Ratto ◽  
Gianluca Ricci ◽  
Francesca Satta ◽  
Pietro Zunino
Keyword(s):  
Mechanical Behavior ◽  
Centrifugal Compressor ◽  
Transport Model ◽  
Three Dimensional ◽  
Optimization Procedure ◽  
Aerodynamic Performance ◽  
Multidisciplinary Optimization ◽  
Navier Stokes ◽  
Phase Lag ◽  
High Rotational Speed

The present paper presents the multi-disciplinary optimization of a centrifugal compressor for a 100kW micro gas turbine. The high rotational speed fixed by the cycle optimization (75,000 rpm) required a simultaneous analysis of flow aerodynamics and mechanical behavior to account for the high centrifugal stresses the blades are subjected to, while maximizing the aerodynamic performance. A commercial 3D (three dimensional) computational fluid dynamics (CFD) solver adopted for the aerodynamic computations and an open source finite element FEM code for the mechanical integrity calculations have been coupled with metamodels to speed up the optimization process. Home-made scripting modules, which manage multidisciplinary optimization, mesh generation, geometry parameterization and result post-processing have been written and utilized. A sample data-base has been generated on the basis of the parameters selected to describe aerodynamic and mechanical constraints, and an optimization procedure based on a genetic algorithm has been performed. A RANS (Reynold Averaged Navier Stokes) steady approach with a two-equation SST (Shear Stress Transport) model has been adopted for the aerodynamic computations during the optimization procedure. The optimized compressor so achieved showed an important boost in aerodynamic performance, without any penalty in the mechanical behavior, as compared with the preliminary design. The optimized configuration has been tested also by means of URANS (Unsteady Reynolds Averaged Navier Stokes) phase-lag investigations, which confirmed the aerodynamic performance increase predicted by steady RANS calculations.

Optimization procedure with analytical aerodynamic sensitivity for reduced sonic boom design

1996 ◽  
Vol 33 (6) ◽  
pp. 1123-1130 ◽  
Author(s):  
N. S. Pagaldipti ◽  
J. N. Rajadas ◽  
A. Chattopadhyay
Keyword(s):  
Optimization Procedure ◽  
Sonic Boom

scholarly journals Low-speed airfoil optimization using constrained differential evolution

2020 ◽  
Vol 12 (4) ◽  
pp. 83-94
Author(s):  
Mihai-Vladut HOTHAZIE ◽  
Matei MIRICA
Keyword(s):  
Evolutionary Algorithm ◽  
Lift Coefficient ◽  
Optimization Procedure ◽  
Aerodynamic Performance ◽  
Optimum Shape ◽  
Design Problems ◽  
Airfoil Optimization ◽  
Engineering Design Problems ◽  
Wide Range ◽  
Differential Evolutionary Algorithm

Nowadays, algorithms designed to optimize the shape of an airfoil are being developed by many researchers. In this paper, to achieve an optimum shape configuration, a methodology based on an evolutionary algorithm is proposed. The main objective is to find the optimum shape of a known airfoil that gives the best aerodynamic performance for a fixed lift coefficient. For the airfoil parametrization, the class-shape method is used to develop a well-behaved geometry. The paper underlines the implementation of a constrained differential evolutionary algorithm using the free penalty scheme by varying the coefficients of the shape parametrization function. The aim is to obtain a better aerodynamic performance for a predetermined lift coefficient by imposing a fixed maximum airfoil thickness interval. The method is a general optimization procedure and can be implemented in a wide range of engineering design problems.

Dimensioning a recovery boiler furnace using mathematical optimization

TAPPI Journal ◽  
2015 ◽  
Vol 14 (2) ◽  
pp. 119-129 ◽  
Author(s):  
VILJAMI MAAKALA ◽  
PASI MIIKKULAINEN
Keyword(s):  
Radial Basis Function Network ◽  
High Capacity ◽  
Mathematical Optimization ◽  
Optimization Procedure ◽  
Optimization Method ◽  
Performance Criteria ◽  
Boiler Furnace ◽  
Starting Point ◽  
Recovery Boiler ◽  
Base Design

Capacities of the largest new recovery boilers are steadily rising, and there is every reason to expect this trend to continue. However, the furnace designs for these large boilers have not been optimized and, in general, are based on semiheuristic rules and experience with smaller boilers. We present a multiobjective optimization code suitable for diverse optimization tasks and use it to dimension a high-capacity recovery boiler furnace. The objective was to find the furnace dimensions (width, depth, and height) that optimize eight performance criteria while satisfying additional inequality constraints. The optimization procedure was carried out in a fully automatic manner by means of the code, which is based on a genetic algorithm optimization method and a radial basis function network surrogate model. The code was coupled with a recovery boiler furnace computational fluid dynamics model that was used to obtain performance information on the individual furnace designs considered. The optimization code found numerous furnace geometries that deliver better performance than the base design, which was taken as a starting point. We propose one of these as a better design for the high-capacity recovery boiler. In particular, the proposed design reduces the number of liquor particles landing on the walls by 37%, the average carbon monoxide (CO) content at nose level by 81%, and the regions of high CO content at nose level by 78% from the values obtained with the base design. We show that optimizing the furnace design can significantly improve recovery boiler performance.

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

Optimization Procedure for Improvement of Thermal Interruption Capability of Tandem-puffer Interrupting Chamber

2010 ◽  
Vol 130 (9) ◽  
pp. 819-825 ◽  
Author(s):  
Takeshi Shinkai ◽  
Keisuke Udagawa ◽  
Hiroshi Furuta ◽  
Akira Shimamura
Keyword(s):  
Optimization Procedure

Numerical Study of the Roughness Influence on NACA 63-430 Profile Aerodynamic Performance

2016 ◽  
Vol 10 (4) ◽  
pp. 231
Author(s):  
Abdekarim Tebbal ◽  
Fethi Saidi ◽  
Boualem Noureddine ◽  
Bachir Imine ◽  
Benameur Hamoudi
Keyword(s):  
Numerical Study ◽  
Aerodynamic Performance

MODELING OF SONIC BOOM WAVE PROPAGATION THROUGH TURBULENCE

2011 ◽  
Vol 42 (3) ◽  
pp. 275-288
Author(s):  
Sergei L. Chernyshev
Keyword(s):  
Wave Propagation ◽  
Sonic Boom
Sign in / Sign up

Export Citation Format

Share Document