scholarly journals Airfoil Design and Optimization Using Multi-Fidelity Analysis and Embedded Inverse Design

2006 ◽  
Author(s):  
Thomas Barrett ◽  
Neil Bressloff ◽  
Andy Keane
Keyword(s):  
Inverse Design ◽  
Design And Optimization

Inverse Design and Active Control Concepts in Strong Unsteady Heat Conduction

1988 ◽  
Vol 41 (6) ◽  
pp. 270-277 ◽  
Author(s):  
George S. Dulikravich
Keyword(s):  
Thermal Conditions ◽  
Coolant Flow ◽  
Geometric Constraints ◽  
Inverse Design ◽  
Optimal Time ◽  
Design And Optimization ◽  
Design Engineers ◽  
Thermal Boundary Conditions ◽  
Internally Cooled ◽  
Unsteady Heat Conduction

A summary of recent research in the field of inverse design and optimization of coolant flow passages in the internally cooled configurations is presented. The methodology allows design engineers to prescribe desired surface temperature and heat flux distributions and to fix portions of the multiply connected realistically shaped configurations. The shapes of the resulting coolant flow passages can be arbitrarily or circularly shaped with a capability to maintain certain manufacturing geometric constraints. Unsteady cooling of organs and tissues in bioengineering is demonstrated by determining optimal time variation of thermal boundary conditions on the walls of the cooling container while maintaining the geometry and size of the configuration. Another concept suggests that components subjected to strong unsteady cooling or heating can be optimized for the desired time dependent overspecified surface thermal conditions by determining the corresponding instantaneous temperatures of the coolant flow passages. This effect can be achieved by applying optimal control of distributed coolant flow rates in each flow passage.

Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor

2004 ◽  
Vol 126 (5) ◽  
pp. 799-806 ◽  
Author(s):  
A´rpa´d Veress ◽  
Rene´ Van den Braembussche
Keyword(s):  
Design Method ◽  
Design Procedure ◽  
Leading Edge ◽  
Secondary Flows ◽  
Inverse Design ◽  
Navier Stokes ◽  
Design And Optimization ◽  
The Cross ◽  
Return Channel ◽  
The Impact

The design and optimization of a multistage radial compressor vaneless diffuser, cross-over and return channel is presented. An analytical design procedure for 3D blades with prescribed load distribution is first described and illustrated by the design of a 3D return channel vane with leading edge upstream of the cross-over. The analysis by means of a 3D Navier–Stokes solver shows a substantial improvement of the return channel performance in comparison with a classical 2D channel. Most of the flow separation inside and downstream of the cross-over could be avoided in this new design. The geometry is further improved by means of a 3D inverse design method to smooth the Mach number distribution along the vanes at hub and shroud. The Navier–Stokes analysis shows a rather modest impact on performance but the calculated velocity distribution indicates a more uniform flow and hence a larger operating range can be expected. The impact of vane lean on secondary flows is investigated and further performance improvements have been obtained with negative lean.

On the Coupling of Inverse Design and Optimization Techniques for Turbomachinery Blade Design

2006 ◽  
Author(s):  
Duccio Bonaiuti ◽  
Mehrdad Zangeneh
Keyword(s):  
Mechanical Design ◽  
Design Method ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Optimization Techniques ◽  
Operating Conditions ◽  
Inverse Design ◽  
Design Parameters ◽  
Optimization Strategy ◽  
Design And Optimization

Optimization strategies have been used in recent years for the aerodynamic and mechanical design of turbomachine components. One crucial aspect in the use of such methodologies is the choice of the geometrical parameterization, which determines the complexity of the objective function to be optimized. In the present paper, an optimization strategy for the aerodynamic design of turbomachines is presented, where the blade parameterization is based on the use of a three-dimensional inverse design method. The blade geometry is described by means of aerodynamic parameters, like the blade loading, which are closely related to the aerodynamic performance to be optimized, thus leading to a simple shape of the optimization function. On the basis of this consideration, it is possible to use simple approximation functions for describing the correlations between the input design parameters and the performance ones. The Response Surface Methodology coupled with the Design of Experiments (DOE) technique was used for this purpose. CFD analyses were run to evaluate the configurations required by the DOE to generate the database. Optimization algorithms were then applied to the approximated functions in order to determine the optimal configuration or the set of optimal ones (Pareto front). The method was applied for the aerodynamic redesign of two different turbomachine components: a centrifugal compressor stage and a single-stage axial compressor. In both cases, both design and off-design operating conditions were analyzed and optimized.

scholarly journals Multiplexed supercell metasurface design and optimization with tandem residual networks

Nanophotonics ◽  
2021 ◽  
Vol 10 (3) ◽  
pp. 1133-1143
Author(s):  
Christopher Yeung ◽  
Ju-Ming Tsai ◽  
Brian King ◽  
Benjamin Pham ◽  
David Ho ◽  
...  
Keyword(s):  
Inverse Design ◽  
Training Dataset ◽  
Structure Property ◽  
Broadband Absorption ◽  
Design And Optimization ◽  
Optical Responses ◽  
Wide Range ◽  
Metal Insulator Metal ◽  
Material Choice ◽  
Nanophotonic Structures

Abstract Complex nanophotonic structures hold the potential to deliver exquisitely tailored optical responses for a range of applications. Metal–insulator–metal (MIM) metasurfaces arranged in supercells, for instance, can be tailored by geometry and material choice to exhibit a variety of absorption properties and resonant wavelengths. With this flexibility, however, comes a vast space of design possibilities that classical design paradigms struggle to effectively navigate. To overcome this challenge, here, we demonstrate a tandem residual network approach to efficiently generate multiplexed supercells through inverse design. By using a training dataset with several thousand full-wave electromagnetic simulations in a design space of over three trillion possible designs, the deep learning model can accurately generate a wide range of complex supercell designs given a spectral target. Beyond inverse design, the presented approach can also be used to explore the structure–property relationships of broadband absorption and emission in such supercell configurations. Thus, this study demonstrates the feasibility of high-dimensional supercell inverse design with deep neural networks, which is applicable to complex nanophotonic structures composed of multiple subunit elements that exhibit coupling.

scholarly journals Airfoil Shape Design and Optimization Using Multifidelity Analysis and Embedded Inverse Design

AIAA Journal ◽  
2006 ◽  
Vol 44 (9) ◽  
pp. 2051-2060 ◽  
Author(s):  
Thomas R. Barrett ◽  
Neil W. Bressloff ◽  
Andy J. Keane
Keyword(s):  
Inverse Design ◽  
Shape Design ◽  
Design And Optimization

Research on Inverse Design and Optimization in Germany

1988 ◽  
Vol 41 (6) ◽  
pp. 239-246 ◽  
Author(s):  
Helmut Sobieczky
Keyword(s):  
Aerospace Industry ◽  
Theoretical Models ◽  
Optimization Methods ◽  
Inverse Design ◽  
Computational Tools ◽  
Design And Optimization ◽  
Knowledge Based ◽  
Industry Applications ◽  
Aircraft Aerodynamics ◽  
Operational Methods

This article tries to illustrate efforts to develop and apply design and optimization methods in German universities, research institutes and the aerospace industry. Applications are shown solely in turbomachinery and aircraft aerodynamics. With restriction to aerodynamic problems, it is shown that efforts to improve theoretical models to become knowledge-based computational tools overlap with operational methods based on the designer’s experience but resulting in hardware concepts for next generation aircraft components.

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