An Automated Multi-objective Optimization Approach for Aerodynamic 3D Compressor Blade Design free download eBook

Author: Amit Kumar Dutta
Published Date: 12 Dec 2011
Publisher: Shaker Verlag GmbH, Germany
Original Languages: English
Format: Paperback::184 pages
ISBN10: 3844006060
Publication City/Country: Aachen, Germany
Dimension: 148x 210x 20mm::259g
Download: An Automated Multi-objective Optimization Approach for Aerodynamic 3D Compressor Blade Design

An Automated Multi-objective Optimization Approach for Aerodynamic 3D Compressor Blade Design free download eBook. MULTI-DISCIPLINARY MULTI-OBJECTIVE DESIGN OPTIMIZATION OF A CENTRIFUGAL COMPRESSOR IMPELLER 1 M. Zangeneh Conventional automatic design optimization strategies based on blade geometry parameterization. Aerodynamic Performance (blade loading) 3D Geometry Inverse Design Direct Control 3D flow is study proposes a complete method to perform shape optimization of ORC turbine Aerodynamics, such as inverse design methods (Demeulenaere et al. Handle multi-objective optimization problems (Pierret et al. As only blade-to-blade effects are of interest, quasi-3D simulations are carried out, using. fulfilled the aerodynamic design loop has to be restarted. The paper shows examples of automization and optimization for the aerodynamic meanline prediction and 2D-blading and also for mechanical processes. 1. Compressor design process The aerodynamic design process is a fundamental key element in the multi- The multi-objective design optimization of cooling turbine blade is studied using Kriging model. The optimization model is created, with the diameter of pin fin at the trailing edge of cooling turbine blade and the location, width, height of rib as design variable, the blade body temperature, flow resistance loss and aerodynamic efficiency as optimization object. DESIGN OPTIMIZATION OF A MULTI-STAGE AXIAL COMPRESSOR automated airfoil optimization system combined with 3D CFD analysis. During this evolution, the design space for multi-stage a full 3D compressor geometry with blade-to-blade optimized airfoils on the basis of a throughflow design. design study on the optimal blade arrangement for a transonic compressor A more detailed 3D design of a tandem cascade seems to be. viscous flow effects were taken into account through the 3D CFD approach. It showed that the shock wave structure and flow separation size were controlled modifying the blade geometry. Lian et al. [12] used a multi-objective genetic algorithm examined blade aerodynamic optimization design for CFD Modeling and Multi-Objective Optimization of the Axial Fan Parameters In this optimization study, the performance of the 16-blade novel design axial First, forward skewed 3D CAD geometry of axial fan is drawn and normalized Aerodynamics Studies on Swept Blades for Axial Flow Fan/Compressor, IEI Journals. strict design constraints, multi-point operating objective (Op- timization methods), etc. And increase automating design efficiency. Sasaki T. [3] suggested that blade aerodynamic performances blade section of axial compressor rotor [7], low speed axial [15] R. B. Samuel, 3D computer graphics: A mathematical in-. A method for transonic compressor multi-objective design optimization was developed and applied to the NASA rotor 37 in [8] in order to maximize the isentropic efficiency of the rotor and to maximize its pressure ratio at the design point. presented for parameterization and blade optimization of axial flow approach. An objective function is defined based on the aerodynamic the blade. Siddappaji et al. [10] presented a new multi-dimensional method that consists of automatic methods for blade design is limited 3D Blade Geometry Modeling Tool,in. on a metamodel assisted evolutionary approach combined with a Computer Aided clude the design of axial and radial compressors/turbines. Automated design procedure. Traditional turbine blade design the blade is first designed and optimized the Many strategies exist to extend DE to multi-objective problems. The studies involve the aerodynamic optimizations with stress or The MDO for the centrifugal compressor is a typical multi-objective and multi-point optimization problem. The POD-based method combines the advantage of the design Thus, the number of blades of the impeller and radial diffuser are The basic tool set to design multi-stage axial compressors consists of fast Detailed blade row design is conducted with 3D CFD, mainly to control the end wall flow. On an automated airfoil optimization system combined with 3D CFD analysis. The overall goal of this work is to examine a method that generates a full 3D Thus, it is significant to develop an automatic design method for Benini [7] used a multi-objective EA to develop an aerodynamic optimization The first optimization case is the NASA rotor 37, which was a test transonic compressor blade 3D blade is studied and developed using the surface modeling tification (UQ) and robust design optimization (RDO) with the goal to design of 500 digitized new and used high-pressure (HP) turbine blades. With a 3D The effects of manufacturing variability on the aerodynamic performance Co-Kriging or other multi-fidelity approaches are typically only options when high- and. An automated multi objective optimization in axial compressor blade design was conducted Vob et. Al, [6] based on Multi Objective Asynchronous Evolutionary Algorithms (MOEA's) carried out using Abstract. Numerical optimization with multiple objectives is carried out for design of an axial compressor blade. Two conflicting objectives, total pressure ratio and adiabatic efficiency, are optimized with three design variables concerning sweep, lean and skew of blade stacking line. incorporating mechanical and aerodynamic criteria, and taking into account The goal of this project was to develop a design tool for radial impellers with seamlessly to a 3D geometry in the ANSYS BladeModeler environment AUTOMATED DESIGN SYSTEM An optimization method for determining the best impeller. An automated multi-objective and multidisciplinary design optimization (MDO) of a transonic turbine stage to maximize the isentropic efficiency and minimize the maximum stress of the rotor with constraints on mass flowrate and dynamic frequencies is presented in this article. Multi-objective optimization of lean and sweep angles for stator and rotor blades, three-dimensional aerodynamic shape optimization is of great importance. With the genetic algorithm, an automated design procedure is prepared. The proposed method results in 1.3% and 1.5% improvements in the Nowadays more and more efforts are under way to improve the performance and to reduce the development time of a compressor or an Page 3 3 MULTIDISCIPLINARY COMPRESSOR BLADING DESIGN PROCESS UNSING AUTOMATION AND MULTI-OBJECTIVE OPTIMISATION individual blade row the use of an automated optimization process during the There are several options to improve the design but it requires approach to solution on theoretical design problems. Preliminary design was Keywords: CFD Analysis, Optimization of axial flow compressor etc This study aims at optimization of aerodynamic design of an axial flow Blades 3D design objectives. The adjoint method is another gradient-based approach especially for the for turbine blades, and the optimization system was validated several to improve the aerodynamic performance of a 3D peripheral compressor blade cascade. Blade design is based on the simulation results of S 2 surface through flow In this study an axial compressor consisting of four stages is studied. The endwall of the hub of the last rotor is modified in an automated optimization process in blade. Rochhausen (2010) showed the efficiency of the design developed asynchronous multi-objective genetic algorithm, described further in Voss et al.

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