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Author: Araz Arbabi Publisher: ISBN: Category : Languages : en Pages : 137
Book Description
An aerodynamic inverse shape design of turbomachinery blading in three-dimensional viscous flow is developed and implemented into a commercial CFD program, namely ANSYS-CFX. The design method is based on specifying one blade parameter, the stacking condition that is a line from hub to tip, and two other flow parameters these can be a- a target pressure distribution over the blade suction surface (or a target pressure loading) and a blade thickness distribution, b- or target pressure distributions on pressure and suction surfaces. This inverse design approach is fully consistent with the viscous flow assumption and is independent of the CFD approach taken. The blade walls are assumed to be moving with a virtual velocity that would asymptotically drive the blade to the shape that would correspond to the specified target pressure distribution. This virtual velocity distribution is computed from the difference between the computed and the target pressure distributions. The wall displacement is computed in a Junction Box Routine and communicated to ANSYS-CFX using CFX Expression Language and User Defined Functions at each design step. In ANSYS-CFX, an element based finite volume formulation is used for space discretization. The Arbitrary Lagrangian-Eulerian formulation of the unsteady Reynolds-Averaged Navier Stokes (URANS) equations is solved in a time accurate fashion with the blade motion being the source of unsteadiness. At each time step, the blade shape is modified and dynamic meshing is used to remesh the fluid flow domain. The implementation is first validated on a transonic rotor blade; the capability, robustness and accuracy of the method in satisfying the design target are then assessed on a single subsonic stator blade row, the rotor blade of an axial compressor stage and, the rotor and stator blades of an axial turbine stage where different choices of the design variables are used. The method is finally implemented to the redesign of a transonic compressor stage, a subsonic axial compressor stage and a turbine stage so as to improve their aerodynamic performance.
Author: Araz Arbabi Publisher: ISBN: Category : Languages : en Pages : 137
Book Description
An aerodynamic inverse shape design of turbomachinery blading in three-dimensional viscous flow is developed and implemented into a commercial CFD program, namely ANSYS-CFX. The design method is based on specifying one blade parameter, the stacking condition that is a line from hub to tip, and two other flow parameters these can be a- a target pressure distribution over the blade suction surface (or a target pressure loading) and a blade thickness distribution, b- or target pressure distributions on pressure and suction surfaces. This inverse design approach is fully consistent with the viscous flow assumption and is independent of the CFD approach taken. The blade walls are assumed to be moving with a virtual velocity that would asymptotically drive the blade to the shape that would correspond to the specified target pressure distribution. This virtual velocity distribution is computed from the difference between the computed and the target pressure distributions. The wall displacement is computed in a Junction Box Routine and communicated to ANSYS-CFX using CFX Expression Language and User Defined Functions at each design step. In ANSYS-CFX, an element based finite volume formulation is used for space discretization. The Arbitrary Lagrangian-Eulerian formulation of the unsteady Reynolds-Averaged Navier Stokes (URANS) equations is solved in a time accurate fashion with the blade motion being the source of unsteadiness. At each time step, the blade shape is modified and dynamic meshing is used to remesh the fluid flow domain. The implementation is first validated on a transonic rotor blade; the capability, robustness and accuracy of the method in satisfying the design target are then assessed on a single subsonic stator blade row, the rotor blade of an axial compressor stage and, the rotor and stator blades of an axial turbine stage where different choices of the design variables are used. The method is finally implemented to the redesign of a transonic compressor stage, a subsonic axial compressor stage and a turbine stage so as to improve their aerodynamic performance.
Author: Rene Van den Braembussche Publisher: John Wiley & Sons ISBN: 1119424097 Category : Technology & Engineering Languages : en Pages : 418
Book Description
A comprehensive overview of fluid dynamic models and experimental results that can help solve problems in centrifugal compressors and modern techniques for a more efficient aerodynamic design. Design and Analysis of Centrifugal Compressors isacomprehensive overview of the theoretical fluid dynamic models describing the flow in centrifugal compressors and the modern techniques for the design of more efficient centrifugal compressors. The author — a noted expert in the field, with over 40 years of experience — evaluates relevant numerical and analytical prediction models for centrifugal compressors with special attention to their accuracy and limitations. Relevant knowledge from the last century is linked with new insights obtained from modern CFD. Emphasis is to link the flow structure, performance and stability to the geometry of the different compressor components. Design and Analysis of Centrifugal Compressors is an accessible resource that combines theory with experimental data and previous research with recent developments in computational design and optimization. This important resource Covers the basic information concerning fluid dynamics that are specific for centrifugal compressors and clarifies the differences with axial compressors Provides an overview of performance prediction models previously developed in combination with extra results from research conducted by the author Describes helpful numerical and analytical models for the flow in the different components in relation to flow stability, operating range and performance Includes the fundamental information for the aerodynamic design of more efficient centrifugal compressors Explains the use of computational fluid dynamics (CFD) for the design and analysis of centrifugal compressors Written for engineers, researchers and designers in industry as well as for academics specializing in the field, Design and Analysis of Centrifugal Compressors offers an up to date overview of the information needed for the design of more effective centrifugal compressors.
Author: Robin Elder Publisher: John Wiley & Sons ISBN: 9781860583537 Category : Science Languages : en Pages : 258
Book Description
In the past Computational Fluid Dynamics (CFD) was confined to large organisations capable of developing and supporting their own codes. But recently there has been a rapid increase in the availability of reasonably priced commercial codes, and many more industrial organisations are now able to routinely use CFD. Advances of CFD in Fluid Machinery Design provide the perfect opportunity to find out what industry is doing and this book addresses how CFD is now being increasingly used in the design process, rather than as a post-design analysis tool. COMPLETE CONTENTS Trends in industrial use of CFD Challenges and methodologies in the design of axial flow fans for high-bypass-ratio, gas turbine engines using steady and unsteady CFD A three-dimensional inverse method based on pressure loading for the design of turbomachinery blades Application of CFD to the design and analysis of axial and centrifugal fans and compressors The design and performance of a transonic flow deswirling system – an application of current CFD design techniques tested against model and full-scale experiments Recent developments in unsteady flow modelling for turbomachinery aeroelasticity Computational investigation of flow in casing treatments for stall delay in axial flow fans Use of CFD for the three-dimensional hydrodynamic design of vertical diffuser pumps Recommendations to designers for CFD pump impeller and diffuser simulations Three dimensional CFD – a possibility to analyse piston pump flow dynamics CFD analysis of screw compressor performance Prediction of aerothermal phenomena in high-speed discstator systems Use of CFD in the design of a shaft seal for high-performance turbomachinery Users and potential users, of CFD for the design of fluid machinery, managers, designers, and researchers working in the field of ‘industrial flows’, will all find Advances of CFD in Fluid Machinery Design a valuable volume discussing state-of-the-art developments in CFD.
Author: Naval Postgraduate Naval Postgraduate School Publisher: ISBN: 9781691582679 Category : Languages : en Pages : 57
Book Description
Previous research at Naval Postgraduate School produced a design procedure for generating gas compressor rotor models using commercial software. This design procedure was improved upon by parameterizing the blade profiles as quadratic functions of axial distance and chord location. An objective function for compressor performance using pressure ratio, efficiency, and massflow was formulated, which applied a holistic view of quantifying the value of a compressor design. An optimization algorithm was implemented within the procedure to seek an optimal design by generating a CAD model, performing computational fluid dynamics (CFD) analysis, and iterating the design function constants toward an optimal solution. The routine found an optimal compressor design; however, inconsistencies in the CFD solution data prevented the routine from finding the expected global maximum.
Author: S. Can Gülen Publisher: Cambridge University Press ISBN: 1108416659 Category : Science Languages : en Pages : 735
Book Description
Everything you wanted to know about industrial gas turbines for electric power generation in one source with hard-to-find, hands-on technical information.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
Aerodynamic shape optimization of axial gas turbines in three dimensional flow is addressed. An effective and practical shape parameterization strategy for turbine stages is introduced to minimize the adverse effects of three-dimensional flow features on the turbine performance. The optimization method combines a genetic algorithm (GA), with a Response Surface Approximation (RSA) of the Artificial Neural Network (ANN) type. During the optimization process, the individual objectives and constraints are approximated using ANN that is trained and tested using a few three-dimensional CFD ow simulations; the latter are obtained using the commercial CFD package Ansys-Fluent. To minimize three-dimensional effects, the stator and rotor stacking curves are taken as the design variable. They are parametrically represented using a quadratic rational Bezier curve (QRBC) whose parameters are directly and explicitly related to the blade lean, sweep and bow, which are used as the design variables. In addition, a noble representation of the stagger angle in the spanwise direction is introduced. The described strategy was applied to optimize the performance of the E/TU-3 axial turbine stage which is designed and tested in Germany. The optimization objectives introduced the isentropic efficiency and the streamwise vorticity, subject to some constraints. This optimization strategy proved to be successful, fexible and practical, and resulted in remarkable improvements in stage performance.
Author: Mohamed Zedan Publisher: ISBN: Category : Aerofoils Languages : en Pages : 0
Book Description
A blade-to-blade inverse design procedure is presented for use in a quasi-3-D design system for multistage axial flow compressors. The procedure is applicable to transonic rotor and stator airfoil sections along axisymmetric stream surfaces. It accounts for the streamtube thickness and radius variations, and can be used in the analysis, fully inverse, and mixed inverse modes. Steady state Euler equations are implemented and formulated in terms of density and local displacement normal to streamline as dependent variables. Three test cases are presented in this paper to illustrate the application of this inverse design technique for optimizing rotor and stator airfoils of highly loaded, high pressure ratio compressor stages. These test cases demonstrate the capability of this procedure to optimize airfoil geometry for minimizing shock and diffusion losses without compromising the airfoil structural integrity.
Author: Araz Arbabi
Author: Araz Arbabi
Author: Rene Van den Braembussche
Author: Robin Elder
Author: Naval Postgraduate Naval Postgraduate School
Author: Louis M. Larosiliere
Author: S. Can Gülen
Author: 
Author: 
Author: Mohamed Zedan
Author: