Multall: An Open Source, CFD Based, Turbomachinery Design System

2017 ◽  
Author(s):  
John D. Denton
Keyword(s):  
Design System ◽  
Small Companies ◽  
Input File ◽  
Stream Surface ◽  
Source Codes ◽  
Multi Stage ◽  
Design Systems ◽  
Overall Performance ◽  
Complex Features ◽  
Turbomachinery Design

Turbomachinery design systems are usually the jealously guarded property of large companies, the author is not aware of any for which the source code is freely available. The present paper is aimed providing a freely available system that can be used by individuals or small companies who do not have access to an in-house system. The design system is based on the 3D CFD solver Multall, which has been developed over many years. Multall can obtain solutions for individual blade rows or for multi-stage machines, it can also perform quasi-3D blade-to-blade calculations on a prescribed stream surface and axisymmetric throughflow calculations. Multall is combined with a one-dimensional mean-line program, Meangen, which predicts the blading parameters on a mean stream surface and writes an input file for Stagen. Stagen is a blade geometry generation and manipulation program which generates and stacks the blading, combines it into stages, and writes an input file for Multall. The system can be used to design the main blade path of all types of turbomachines. Although it cannot design complex features such as shroud seals and individual cooling holes these features can be modeled and their effect on overall performance predicted. The system is intended to be as simple and easy to use as possible and the solver is also very fast compared to most CFD codes. A great deal of user experience ensures that the overall performance is reasonably well predicted for a wide variety of machines. This paper describes the system in outline and gives an example of its use. The source codes are written in FORTRAN77 and are freely available for other users to try.

Multall—An Open Source, Computational Fluid Dynamics Based, Turbomachinery Design System

2017 ◽  
Vol 139 (12) ◽  
Author(s):  
John D. Denton
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Three Dimensional ◽  
Design System ◽  
Input File ◽  
Stream Surface ◽  
Source Codes ◽  
Overall Performance ◽  
Complex Features ◽  
Turbomachinery Design

Turbomachinery design systems are usually the jealously guarded property of large companies, and the author is not aware of any for which the source code is freely available. This paper is aimed providing a freely available system that can be used by individuals or small companies who do not have access to an in-house system. The design system is based on the three-dimensional (3D) computational fluid dynamics (CFD) solver Multall, which has been developed over many years. Multall can obtain solutions for individual blade rows or for multistage machines, and it can also perform quasi-3D (Q3D) blade-to-blade calculations on a prescribed stream surface and axisymmetric throughflow calculations. Multall is combined with a one-dimensional (1D) mean-line program, Meangen, which predicts the blading parameters on a mean stream surface and writes an input file for Stagen. Stagen is a blade geometry generation and manipulation program which generates and stacks the blading, combines it into stages, and writes an input file for Multall. The system can be used to design the main blade path of all types of turbomachines. Although it cannot design complex features such as shroud seals and individual cooling holes, these features can be modeled, and their effect on overall performance predicted. The system is intended to be as simple and easy to use as possible, and the solver is also very fast compared to most CFD codes. A great deal of user experience ensures that the overall performance is reasonably well predicted for a wide variety of machines. This paper describes the system in outline and gives an example of its use. The source codes are written in FORTRAN77 and are freely available for other users to try.

CFD-Based Throughflow Solver in a Turbomachinery Design System

2007 ◽  
Author(s):  
Fahua Gu ◽  
Mark R. Anderson
Keyword(s):  
Three Dimensional ◽  
Design System ◽  
Flow Angle ◽  
Stream Surface ◽  
Streamline Curvature ◽  
Machine Performance ◽  
Multi Stage ◽  
Pros And Cons ◽  
Turbomachinery Design ◽  
Different Levels

Throughflow analysis is a critical component for the multi-stage axial turbomachine design. The Euler throughflow approach has been developed over the last couple of decades, but has been less successful than its early peer, the streamline curvature approach. In this paper an Euler throughflow approach is described for engineering applications. It includes the steps needed to construct the stream surface, such as modifications for the incidence and deviation, and the throat area correction. The flow angle difference at the trailing edge and in the downstream non-bladed gap stations is resolved, and the numerical loss from solving the Euler equation is removed as well. This solver has been integrated into a comprehensive turbomachinery design system. It creates and modifies the machine geometries and predicts the machine performance at different levels of approximation, including one-dimensional design and analysis, quasi-three-dimensional methods (blade-to-blade and throughflow) and full-three-dimensional steady-state CFD analysis. The flow injection and extraction functions are described, as is the implementation of the radial mass distribution. Some discussion is dedicated to the shock calculation. Finally, examples are provided to demonstrate the pros and cons of the Euler throughflow approach and also to demonstrate the potential to solve for a wider range of flow conditions, particularly choked and transonic flows that limit stream function based solvers.

Analysis of the Effect of Multi-Row and Multi-Passage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration: Part 2 — Effects of Additional Structural Mistuning

2017 ◽  
Author(s):  
Johann Gross ◽  
Malte Krack ◽  
Harald Schoenenborn
Keyword(s):  
Epistemic Uncertainty ◽  
Element Model ◽  
Forced Response ◽  
Aerodynamic Loading ◽  
Multi Stage ◽  
Blade Row ◽  
Random Mistuning ◽  
Response Variation ◽  
Stage Analysis ◽  
Turbomachinery Design

The prediction of aerodynamic blade forcing is a very important topic in turbomachinery design. Usually, the wake from the upstream blade row and the potential field from the downstream blade row are considered as the main causes for excitation, which in conjunction with relative rotation of neighboring blade rows, give rise to dynamic forcing of the blades. In addition to those two mechanisms so-called Tyler-Sofrin (or scattered or spinning) modes, which refer to the acoustic interaction with blade rows further up- or downstream, may have a significant impact on blade forcing. In particular, they lead to considerable blade-to-blade variations of the aerodynamic loading. In part 1 of the paper a study of these effects is performed on the basis of a quasi 3D multi-row and multi-passage compressor configuration. Part 2 of the paper proposes a method to analyze the interaction of the aerodynamic forcing asymmetries with the already well-studied effects of random mistuning stemming from blade-to-blade variations of structural properties. Based on a finite element model of a sector, the equations governing the dynamic behavior of the entire bladed disk can be efficiently derived using substructuring techniques. The disk substructure is assumed as cyclically symmetric, while the blades exhibit structural mistuning and linear aeroelastic coupling. In order to avoid the costly multi-stage analysis, the variation of the aerodynamic loading is treated as an epistemic uncertainty, leading to a stochastic description of the annular force pattern. The effects of structural mistuning and stochastic aerodynamic forcing are first studied separately and then in a combined manner for a blisk of a research compressor without and with aeroelastic coupling.

FLEXIBLE PROJECT CUSTOMIZATION IN COMPUTER-AIDED DESIGN SYSTEMS

2021 ◽  
Author(s):  
E. A. Sobolev ◽  
Keyword(s):  
Computer Aided Design ◽  
Printed Circuit Board ◽  
Circuit Board ◽  
Design System ◽  
Programming Environment ◽  
Printed Circuit ◽  
Computer Aided ◽  
Design Systems ◽  
Aided Design ◽  
New Instruments

The article describes customization methods for printed circuit board projects in computer-aided design system Xpedition Enterprise. Two approaches has been detected, first – setting up project using built-in instruments, second – implementation of a new instruments using integrated programming environment.

A CAD-Based Blade Geometry Model for Turbomachinery Aero Design Systems

2003 ◽  
Author(s):  
Ali Merchant ◽  
Robert Haimes
Keyword(s):  
Three Dimensional ◽  
Model Construction ◽  
Design System ◽  
Solid Model ◽  
Design Environment ◽  
Seamless Integration ◽  
Geometry Model ◽  
Design Systems ◽  
Blade Model ◽  
Blade Geometry

A CAD-centric approach for constructing and managing the blade geometry in turbomachinery aero design systems is presented in this paper. Central to the approach are a flexible CAD-based parametric blade model definition and a set of CAD-neutral interfaces which enable construction and manipulation of the blade solid model directly inside the CAD system’s geometry kernel. A bottleneck of transferring geometry data passively via a file-based method is thus eliminated, and a seamless integration between the CAD system, aero design system, and the larger design environment can be achieved. A single consistent CAD-based blade model is available at all stages of the aero design process, forming the basis for coupling the aero design system to the larger multi-disciplinary design environment. The blade model construction is fully parameterized so that geometry updates can be accurately controlled via parameter changes, and geometric sensitivities of the model can be easily calculated for multidisciplinary interaction and design optimization. A clear separation of the parameters that control the three-dimensional shape of the blade (such as lean and sweep) from the parameters that control the elemental profile shape allows any blade profile family or shape definition to be utilized. The blade model definition, construction interface, and implementation approach are described. Applications illustrating solid model construction, parametric modification and sensitivity calculation, which are key requirements for automated aerodynamic shape design, are presented.

S2 Surface Quasi-3D Aerodynamic Design Using the Continuous Adjoint Method for Multi-Stage Turbine

2014 ◽  
Author(s):  
Lei Chen ◽  
Jiang Chen
Keyword(s):  
Objective Function ◽  
Adjoint Method ◽  
Adjoint Equations ◽  
Design System ◽  
Shape Design ◽  
Aerodynamic Design ◽  
Aerodynamic Shape ◽  
Multi Stage ◽  
Gradient Based ◽  
Continuous Adjoint

The adjoint method eliminates the dependence of the gradient of the objective function with respect to design variables on the flow field making the obtainment of the gradient both accurate and fast. For this reason, the adjoint method has become the focus of attention in recent years. This paper develops a continuous adjoint formulation for through-flow aerodynamic shape design in a multi-stage gas turbine environment based on a S2 surface quasi-3D problem governed by the Euler equations with source terms. Given the general expression of the objective function calculated via a boundary integral, the adjoint equations and their boundary conditions are derived in detail by introducing adjoint variable vectors. As a result, the final expression of the objective function gradient only includes the terms pertinent to those physical shape variations that are calculated by metric variations. The adjoint system is solved numerically by a finite-difference method with explicit Euler time-marching scheme and a Jameson spatial scheme which employs first and third order dissipative flux. Integrating the blade stagger angles and passage perturbation parameterization with the simple steepest decent method, a gradient-based aerodynamic shape design system is constructed. Finally, the application of the adjoint method is validated through a 5-stage turbine blade and passage optimization with an objective function of entropy generation. The result demonstrates that the gradient-based system can be used for turbine aerodynamic design.

scholarly journals Progress and recent trends in generative design

2020 ◽  
Vol 318 ◽  
pp. 01006
Author(s):  
Ioannis Ntintakis ◽  
George E. Stavroulakis
Keyword(s):  
Additive Manufacturing ◽  
Design System ◽  
Generative Design ◽  
Collaborative Tools ◽  
Design And Manufacturing ◽  
Recent Developments ◽  
Recent Trends ◽  
Design Systems ◽  
Intelligent Technology ◽  
Current Systems

Due to recent developments in the field of additive manufacturing enormous advantages have become in product design and manufacturing process. Before the appearance of additive manufacturing, developing very complex or light weight structures was difficult to manufacture. The development of artificial intelligent technology helps to develop new collaborative tools and algorithms. Generative design approach is one of them. The outcome model from a generative design study is not depending only from designer/engineer experience or his knowledge. Designers can react with sophisticated algorithms through CAD programs to specify the shape and the topology of the model. A significant tool on a generative design system is topology optimization which is able to generate different solutions. The changes in design process are significant. A rough conceptual design (sketch) or a 3d model is first prepared. Then, boundary conditions, safety factor, manufacturing limitations and materials properties are defined. The generative design system generates potential solutions. It’s up to the designer to find the design that best fits to his need. In this paper the review covers the limitations of current systems through the study of specific design cases using commercial generative design systems.

The Importance of Circumferential Non-uniformities in a Passage-Averaged Quasi-Three-Dimensional Turbomachinery Design System

1986 ◽  
Vol 108 (2) ◽  
pp. 240-245 ◽  
Author(s):  
I. K. Jennions ◽  
P. Stow
Keyword(s):  
Pressure Gradient ◽  
Guide Vane ◽  
Three Dimensional ◽  
Radial Pressure ◽  
Turbine Rotor ◽  
Design System ◽  
Radial Pressure Gradient ◽  
Flow Effects ◽  
Nozzle Guide ◽  
Turbomachinery Design

The purpose of this paper is to show, for both rotating and non-rotating blade rows, the importance of including circumferential non-uniform flow effects in a quasi-three-dimensional blade design system. The paper follows from previous publications on the system in which the mathematical analysis and computerized system are detailed. Results are presented for a different stack of the nozzle guide vane presented previously and for a turbine rotor. In the former case it is again found that the blade force represents a major contribution to the radial pressure gradient, while for the rotor the radial pressure gradient is dominated by centrifugal effects. In both examples the effects of circumferential non-uniformities are detailed and discussed.

scholarly journals Fastener products lightweight design and forming process simulation

2018 ◽  
Vol 185 ◽  
pp. 00030
Author(s):  
Jinn-Jong Sheu ◽  
Chien-Jen Ho ◽  
Cheng-Hsien Yu ◽  
Kuo-Ting Wu
Keyword(s):  
Topology Optimization ◽  
Lightweight Design ◽  
Integrated Design ◽  
Optimization Method ◽  
Design System ◽  
Forming Process ◽  
Multi Stage ◽  
Die Stress ◽  
Final Design ◽  
Evaluation Stage

In this research, an integrated design system was established to design the product of nuts with flange and generate the lightweight geometry of product. The multi-stage forming process was evaluated using the CAE simulations. The topology optimization method was used to achieve the lightweight design, that included keeping necessary geometrical features and remove the excess volumes. The topological discrete model had been remodelled into a meaningful geometry which is able to satisfy the requirement of proof load of fastener specification. The final design of the lightweight geometry was adopted to test the capability of carrying proof load required using CAE simulations with the boundary conditions of the related ASTM standard. In the evaluation stage, the finite element method was used to do the topology optimization, the proof load evaluation, the forging process and the die stress analysis. The simulation results showed the lightweight design was able to reduce the weight of product and maintain enough mechanical strength. The proposed process and die designs were able to obtain the lightweight product without defects.

The Architecture and Application of Preliminary Design Systems

2011 ◽  
Author(s):  
Fabian Donus ◽  
Stefan Bretschneider ◽  
Reinhold Schaber ◽  
Stephan Staudacher
Keyword(s):  
Conceptual Design ◽  
Design System ◽  
Target Market ◽  
Preliminary Design ◽  
Design Phase ◽  
Planning Phase ◽  
Conceptual Design Phase ◽  
Engine Design ◽  
Design Systems ◽  
Aero Engines

The development of every new aero-engine follows a specific process; a sequence of steps or activities which an enterprise employs to conceive, design and commercialize a product. Typically, it begins with the planning phase, where the technology developments and the market objectives are assessed; the output of the planning phase is the input to the conceptual design phase where the needs of the target market are then identified, and alternative product concepts are generated and evaluated, and one or more concepts are subsequently selected for further development based on the evaluation. For aero-engines, the main goal of this phase is therefore to find the optimum engine cycle for a specific set of boundary conditions. This is typically done by conducting parameter studies where every calculation point within the study characterizes one specific engine design. Initially these engines are represented as pure performance cycles. Subsequently, other disciplines, such as Aerodynamics, Mechanics, Weight, Cost and Noise are accounted for to reflect interdisciplinary dependencies. As there is only very little information known about the future engine at this early phase of development, the physical design algorithms used within the various discipline calculations must, by default, be of a simple nature. However, considering the influences among all disciplines, the prediction of the concept characteristics translates into a very challenging and time intensive exercise for the pre-designer. This is contradictory to the fact that there are time constraints within the conceptual design phase to provide the results. Since the early 1970’s, wide scale efforts have been made to develop tools which address the multidisciplinary design of aero-engines within this phase. These tools aim to automatically account for these interdisciplinary dependencies and to decrease the time used to provide the results. Interfaces which control the input and output between the various subprograms and automated checks of the calculation results decrease the possibility of user errors. However, the demands on the users of such tools are expected to even increase, as such systems can give the impression that the calculations are inherently performed correctly. The presented paper introduces MTU’s preliminary design system Modular Performance and Engine Design System (MOPEDS). The results of simple calculation examples conducted using MOPEDS show the influences of the various disciplines on the overall engine system and are used to explain the architecture of such complex design systems.

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