Automated Design Optimization of a Three-Dimensional S-Shaped Subsonic Diffuser

2002 ◽  
Vol 18 (4) ◽  
pp. 913-921 ◽  
Author(s):  
Sophia Lefantzi ◽  
Doyle D. Knight
2011 ◽  
Vol 27 (4) ◽  
pp. 838-846 ◽  
Author(s):  
Aniket Aranake ◽  
Jin Gyu Lee ◽  
Doyle Knight ◽  
Russell M. Cummings ◽  
John Cox ◽  
...  

2000 ◽  
Vol 16 (6) ◽  
pp. 1132-1140 ◽  
Author(s):  
Wei-Li Zhang ◽  
Doyle D. Knight ◽  
Don Smith

2005 ◽  
Author(s):  
Ramakanth Munipalli ◽  
Kamesh Subbarao ◽  
Shashi Aithal ◽  
Donald R. Wilson ◽  
Jennifer D. Goss

Author(s):  
E. Sandgren ◽  
S. Venkataraman

Abstract A design optimization approach to robot path planning in a two dimensional workplace is presented. Obstacles are represented as a series of rectangular regions and collision detection is performed by an operation similar to clipping in computer graphics. The feasible design space is approximated by a discrete set of robot arm and gripper positions. Control is applied directly through the angular motion of each link. Feasible positions which are located between the initial and final robot link positions are grouped into stages. A dynamic programming algorithm is applied to locate the best state within each stage which minimizes the overall path length. An example is presented involving a three link planar manipulator. Extensions to three dimensional robot path planning and real time control in a dynamically changing workplace are discussed.


Author(s):  
Hashem Ashrafiuon

Abstract Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the individual mounts to minimize the transmitted forces from the engine to the base. Meanwhile, the mounts have to be stiff enough not allowing engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when mount orientation angles are also treated as design variables. The optimization problems are solved using a Constraint Variable Metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to achieve a more effective optimization search technique.


2020 ◽  
Vol 86 (2) ◽  
Author(s):  
Jim-Felix Lobsien ◽  
Michael Drevlak ◽  
Thomas Kruger ◽  
Samuel Lazerson ◽  
Caoxiang Zhu ◽  
...  

Following up on earlier work which demonstrated an improved numerical stellarator coil design optimization performance by the use of stochastic optimization (Lobsien et al., Nucl. Fusion, vol. 58 (10), 2018, 106013), it is demonstrated here that significant further improvements can be made – lower field errors and improved robustness – for a Wendelstein 7-X test case. This is done by increasing the sample size and applying fully three-dimensional perturbations, but most importantly, by changing the design sequence in which the optimization targets are applied: optimization for field error is conducted first, with coil shape penalties only added to the objective function at a later step in the design process. A robust, feasible coil configuration with a local maximum field error of 3.66 % and an average field error of 0.95 % is achieved here, as compared to a maximum local field error of 6.08 % and average field error of 1.56 % found in our earlier work. These new results are compared to those found without stochastic optimization using the FOCUS and ONSET suites. The relationship between local minima in the optimization space and coil shape penalties is also discussed.


Author(s):  
Chan-Sol Ahn ◽  
Kwang-Yong Kim

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.


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