Download or read book An Approach for Aerodynamic Optimization of Transonic Fan Blades written by Maryam Khelghatibana and published by . This book was released on 2014 with total page 97 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic design optimization of transonic fan blades is a highly challenging problem due to the complexity of flow field inside the fan, the conflicting design requirements and the high-dimensional design space. In order to address all these challenges, an aerodynamic design optimization method is developed in this study. This method automates the design process by integrating a geometrical parameterization method, a CFD solver and numerical optimization methods that can be applied to both single and multi-point optimization design problems. A multi-level blade parameterization is employed to modify the blade geometry. Numerical analyses are performed by solving 3D RANS equations combined with SST turbulence model. Genetic algorithms and hybrid optimization methods are applied to solve the optimization problem. In order to verify the effectiveness and feasibility of the optimization method, a singlepoint optimization problem aiming to maximize design efficiency is formulated and applied to redesign a test case. However, transonic fan blade design is inherently a multi-faceted problem that deals with several objectives such as efficiency, stall margin, and choke margin. The proposed multi-point optimization method in the current study is formulated as a bi-objective problem to maximize design and near-stall efficiencies while maintaining the required design pressure ratio. Enhancing these objectives significantly deteriorate the choke margin, specifically at high rotational speeds. Therefore, another constraint is embedded in the optimization problem in order to prevent the reduction of choke margin at high speeds. Since capturing stall inception is numerically very expensive, stall margin has not been considered as an objective in the problem statement. However, improving near-stall efficiency results in a better performance at stall condition, which could enhance the stall margin. An investigation is therefore performed on the Pareto-optimal solutions to demonstrate the relation between near-stall efficiency and stall margin.

Download or read book Multidisciplinary Design Optimization MDO of Transonic Fan Blade written by Saima Naz and published by . This book was released on 2014 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Shape Optimization of Axial Flow Fans written by Jason R. Bender and published by . This book was released on 1997 with total page 382 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Shape Optimization of Axial Flow Fans written by and published by . This book was released on 1908 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this work is to improve the efficiency of large scale axial flow fans through the introduction of a more uniform velocity distribution over the fan blades. This improved velocity di tribution being realized through the use of an aerodynamically optimized inlet cone. The procedure for optimization the inlet cone uses existing aerodynamic optimization methods programmed into a completely self contained FORTRAN program. The type of optimization algorithm used here is the use of design optimization to solve an inverse design problem. The different modules of the program include a surface vorticity panel method flow solver, a Bezier curve surface definition routine and a minimization method. Three different minimization methods were tested to determine the most appropriate one, this being the downhill simplex method in multidimensions. Many different sized fans and inlet cones were tested, with two different types of optimized inlet cones being discovered. Short inlet cones typically make use of avery blunt inlet cone with a slight hump or rise above the hub radius. Longer inlet cones make use of a more curved inlet cone with no hump. It was also shown that the hub-to-tip ratio of the fan has a significant impact on the velocity distribution and therefore the efficiency of the fan unit. As well, it was shown that only a small change in the length of the inlet cone could affect the velocity istribution. It was also found from this work that the relatively simple methods used can provide an adequate modeling of the problem and a easonable solution.

Download or read book Aerodynamic Shape Optimization of Fan Blades written by Timothy P. Rogalsky and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Shape Optimization of Fan Blades written by Timothy P. Rogalsky and published by . This book was released on 1999 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Shape Optimization of Fan Blades written by and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Computational Method for the Aerodynamic Design of Transonic Turbine Blades written by R. W. Paige and published by . This book was released on 1983 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book EngOpt 2018 Proceedings of the 6th International Conference on Engineering Optimization written by H.C. Rodrigues and published by Springer. This book was released on 2018-09-13 with total page 1486 pages. Available in PDF, EPUB and Kindle. Book excerpt: The papers in this volume focus on the following topics: design optimization and inverse problems, numerical optimization techniques,efficient analysis and reanalysis techniques, sensitivity analysis and industrial applications. The conference EngOpt brings together engineers, applied mathematicians and computer scientists working on research, development and practical application of optimization methods in all engineering disciplines and applied sciences.

Download or read book Aerothermodynamics of Turbomachinery written by Naixing Chen and published by John Wiley & Sons. This book was released on 2011-09-23 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computational Fluid Dynamics (CFD) is now an essential and effective tool used in the design of all types of turbomachine, and this topic constitutes the main theme of this book. With over 50 years of experience in the field of aerodynamics, Professor Naixing Chen has developed a wide range of numerical methods covering almost the entire spectrum of turbomachinery applications. Moreover, he has also made significant contributions to practical experiments and real-life designs. The book focuses on rigorous mathematical derivation of the equations governing flow and detailed descriptions of the numerical methods used to solve the equations. Numerous applications of the methods to different types of turbomachine are given and, in many cases, the numerical results are compared to experimental measurements. These comparisons illustrate the strengths and weaknesses of the methods – a useful guide for readers. Lessons for the design of improved blading are also indicated after many applications. Presents real-world perspective to the past, present and future concern in turbomachinery Covers direct and inverse solutions with theoretical and practical aspects Demonstrates huge application background in China Supplementary instructional materials are available on the companion website Aerothermodynamics of Turbomachinery: Analysis and Design is ideal for senior undergraduates and graduates studying in the fields of mechanics, energy and power, and aerospace engineering; design engineers in the business of manufacturing compressors, steam and gas turbines; and research engineers and scientists working in the areas of fluid mechanics, aerodynamics, and heat transfer. Supplementary lecture materials for instructors are available at www.wiley.com/go/chenturbo

Download or read book Structural Optimization of Rotor Blades with Integrated Dynamics and Aerodynamics written by and published by . This book was released on 1988 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Optimization of Low Pressure Axial Fans written by Konrad Bamberger and published by . This book was released on 2015 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Automated Multi objective Optimization Approach for Aerodynamic 3D Compressor Blade Design written by Amit Kumar Dutta and published by . This book was released on 2011 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Proceedings of the 6th China Aeronautical Science and Technology Conference written by Chinese Aeronautical Society and published by Springer Nature. This book was released on 2024-01-06 with total page 742 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book contains the original peer-reviewed research papers presented at the 6th China Aeronautical Science and Technology Conference held in Wuzhen, Zhejiang Province, China, in September 2023. Topics covered include but are not limited to Navigation/Guidance and Control Technology, Aircraft Design and Overall Optimisation of Key Technologies, Aviation Testing Technology, Airborne Systems/Electromechanical Technology, Structural Design, Aerodynamics and Flight Mechanics, Advanced Aviation Materials and Manufacturing Technology, Advanced Aviation Propulsion Technology, and Civil Aviation Transportation. The papers presented here share the latest findings in aviation science and technology, making the book a valuable resource for researchers, engineers and students in related fields.

Download or read book Structural Analysis and Optimization of a Composite Fan Blade for Future Aircraft Engine written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report addresses the structural analysis and optimization of a composite fan blade sized for a large aircraft engine. An existing baseline solid metallic fan blade was used as a starting point to develop a hybrid honeycomb sandwich construction with a polymer matrix composite face sheet and honeycomb aluminum core replacing the original baseline solid metallic fan model made of titanium. The focus of this work is to design the sandwich composite blade with the optimum number of plies for the face sheet that will withstand the combined pressure and centrifugal loads while the constraints are satisfied and the baseline aerodynamic and geometric parameters are maintained. To satisfy the requirements, a sandwich construction for the blade is proposed with composite face sheets and a weak core made of honeycomb aluminum material. For aerodynamic considerations, the thickness of the core is optimized whereas the overall blade thickness is held fixed so as to not alter the original airfoil geometry. Weight is taken as the objective function to be minimized by varying the core thickness of the blade within specified upper and lower bounds. Constraints are imposed on radial displacement limitations and ply failure strength. From the optimum design, the minimum number of plies, which will not fail, is back-calculated. The ply lay-up of the blade is adjusted from the calculated number of plies and final structural analysis is performed. Analyses were carried out by utilizing the OpenMDAO Framework, developed at NASA Glenn Research Center combining optimization with structural assessment. Coroneos, Rula M. Glenn Research Center STRUCTURAL ANALYSIS; FAN BLADES; PRESSURE DISTRIBUTION; HONEYCOMB STRUCTURES; POLYMER MATRIX COMPOSITES; CENTRIFUGAL FORCE; ENGINE DESIGN; AIRFOIL PROFILES

Download or read book Structural Optimization of Rotor Blades with Integrated Dynamics and Aerodynamics written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of structural optimization of helicopter rotor blades with integrated dynamic and aerodynamic design considerations is addressed. Results of recent optimization work on rotor blades for minimum weight with constraints on multiple coupled natural flap-lag frequencies, blade autorotational inertia and centrifugal stress has been reviewed. A strategy has been defined for the ongoing activities in the integrated dynamic/aerodynamic optimization of rotor blades. As a first step, the integrated dynamic/airload optimization problem has been formulated. To calculate system sensitivity derivatives necessary for the optimization recently developed, Global Sensitivity Equations (GSE) are being investigated. A need for multiple objective functions for the integrated optimization problem has been demonstrated and various techniques for solving the multiple objective function optimization are being investigated. The method called the Global Criteria Approach has been applied to a test problem with the blade in vacuum and the blade weight and the centrifugal stress as the multiple objectives. The results indicate that the method is quite effective in solving optimization problems with conflicting objective functions. Chattopadhyay, Aditi and Walsh, Joanne L. Langley Research Center RTOP 505-63-51-10...

Download or read book A General Multidisciplinary Turbomachinery Design Optimization System Applied to a Transonic Fan written by Ahmed M. F. Nemnem and published by . This book was released on 2014 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt: The blade geometry design process is integral to the development and advancement of compressors andturbines in gas generators or aeroengines. A new airfoil section design capability has been added to an opensource parametric 3D blade design tool. Curvature of the meanline is controlled using B-splines to createthe airfoils. The curvature is analytically integrated to derive the angles and the meanline is obtained byintegrating the angles. A smooth thickness distribution is then added to the airfoil to guarantee a smoothshape while maintaining a prescribed thickness distribution. A leading edge B-spline definition has alsobeen implemented to achieve customized airfoil leading edges which guarantees smoothness with parametriceccentricity and droop. An automated turbomachinery design and optimization system has been created. An existing splitteredtransonic fan is used as a test and reference case. This design was more general than a conventional designto have access to the other design methodology. The whole mechanical and aerodynamic design loopsare automated for the optimization process. The flow path and the geometrical properties of the rotor areinitially created using the axi-symmetric design and analysis code (T-AXI). The main and splitter bladesare parametrically designed with the created geometry builder (3DBGB) using the new added features (curvature technique). The solid model creation of the rotor sector with a periodic boundaries combining themain blade and splitter is done using MATLAB code directly connected to SolidWorks including the hub, fillets and tip clearance. A mechanical optimization is performed with DAKOTA (developed by DOE) toreduce the mass of the blades while keeping maximum stress as a constraint with a safety factor. A Geneticalgorithm followed by Numerical Gradient optimization strategies are used in the mechanical optimization. The splittered transonic fan blades mass is reduced by 2.6% while constraining the maximum stress below50% material yield strength using 2D sections thickness and chord multipliers. Once the initial design was mechanically optimized, a CFD optimization was performed to maximizeefficiency and/or stall margin. The CFD grid generator (AUTOGRID) reads 3DBGB output and accountsfor hub fillets and tip gaps. Single and Multi-objective Genetic Algorithm (SOGA, MOGA) optimizationhave been used with the CFD analysis system. In SOGA optimization, efficiency was increased by 3.525%from 78.364% to 81.889% while only changing 4 design parameters. For MOGA optimization with higherweighting efficiency than stall margin, the efficiency was increased by 2.651% from 78.364% to 81.015%while the static pressure recovery factor was increased from 0.37407 to 0.4812286 that consequently increases the stall margin. The design process starts with a hot shape design, and then a hot to cold transformation process is explainedonce the optimization process ends which smoothly subtracts the mechanical deflections from thehot shape. This transformation ensures an accurate tip clearance. The optimization modules can be customized by the user as one full optimization or multiple small ones. This allows the designer not to be eliminated from the design loop which helps in taking the right choice ofparameters for the optimization and the final feasible design.