Optimized preliminary design of compact axial compressors: A comparison of two design tools

2013 ◽  
Author(s):  
Soenke Teichel ◽  
Tom Verstraete ◽  
Jorg Seume
Keyword(s):  
Preliminary Design ◽  
Design Tools ◽  
Axial Compressors

scholarly journals SURVEY-BASED ASSESSMENT OF DESIGN SKILL DEVELOPMENT IN ENGINEERING PROJECT COURSES

2011 ◽  
Author(s):  
Brian Frank ◽  
David Strong
Keyword(s):  
Assessment Tool ◽  
Problem Definition ◽  
First Year ◽  
Preliminary Design ◽  
Design Tools ◽  
Engineering Project ◽  
The Third ◽  
Future Improvement ◽  
Before And After ◽  
Design Experience

A pilot of a paper-based assessment tool of design skill is presented. The tool is used to assess the development of skills before and after a first year design experience, and before and after a third year multidisciplinary course in design tools and methodology. The tool is an open-ended survey that may be administered quickly and assessed using a simple rubric. Significant improvements were found over the term of the first year course in the areas of problem definition and testing; improvements were observed in the categories of Conceptual Design, Preliminary Design, and Detailed Design in the third year course. Ideas for future improvement are discussed.

Application of Smith Chart for Non-Repeating Stages in Axial Compressors

2013 ◽  
Author(s):  
Daniel Hernández ◽  
Antonio Antoranz ◽  
Raúl Vázquez
Keyword(s):  
Early Stage ◽  
Axial Compressor ◽  
Preliminary Design ◽  
The Novel ◽  
Flow Angle ◽  
Axial Compressors ◽  
Absolute Flow ◽  
Final Design ◽  
Semi Empirical ◽  
Smith Chart

The configuration of an axial compressor, including the mean radius, the annulus lines, stage loading or number of stages, flow parameter, work split and stage reactions, are all of them selected in the preliminary design phase. For the success of the final design, to attain the proper selection is mandatory. A representative geometry of the airfoils is not available at this early stage of the design process. Therefore the former parameters use to be selected based only on the designer prior experience and/or empirical correlations. Under these circumstances, the so called Smith Chart is a valuable tool that can provide simple guidelines to the designer and a preliminary assessment of the compressor efficiency. The use of this chart can be also extended to get the main features of the airfoils, like flow angles, turning, Mach and Reynolds number, diffusion factor, aspect ratio, etc. as well as to compare different design candidates. Several authors have produced their own diagrams by analytical or semi-empirical approach. The repeating stage hypothesis, which has been usually assumed, implies no change in inlet and outlet absolute flow angles and constant axial velocity throughout the stage. The density rise through the stage is compensated by reducing the annulus height and so the annulus wall slope along the compressor is directly obtained from the continuity equation, being in most of the cases not representative of real compressors. In order to have a more representative annulus, in the present work, the repeating stage hypothesis has not been assumed. The annulus shape (height and slope wall angle) is therefore defined by the designer and in order to close the equations of the problem, the absolute exit flow angle of every stage is required. The optimization of the compressor by the novel proposed method is more complicate because of the higher number of variables. However the method has the advantage to reduce the design iterations due to its more reliable results. The aim of this paper is to introduce the novel method of non-repeating stages and to show how this approach can be used in the preliminary design of an axial compressor.

Dynamic Non-Interference Constraints in Goal-Directed Geometry

1995 ◽  
Author(s):  
Stewart Coulter ◽  
Bert Bras ◽  
David Rosen
Keyword(s):  
Computer Aided Design ◽  
Preliminary Design ◽  
Design Tools ◽  
Multi Objective Optimization ◽  
Computational Framework ◽  
Linkage Design ◽  
Engineering Models ◽  
Aided Design ◽  
Dynamic Interference

Abstract Improvements in computer-aided design tools can significantly increase designer productivity. The ability to explore a variety of possible designs quickly and effectively is essential for a designer. In a previous paper, Goal Directed Geometry (GDG) was introduced as a computational framework for preliminary design, aiding the formulation of engineering models with geometric considerations, and the solution of these models with a multi-objective optimization package. The geometric considerations were limited to static noninterference constraints, introducing a metric and method for prevention of geometric interference between two subassemblies. In this paper, this metric and method are expanded to include the prevention of interference between moving subassemblies, or dynamic interference. Based on a series of repetitive static checks, this metric is intended to be accurate and simple for the designer to use. A case study is presented showing the GDG implementation for a linkage design problem, demonstrating the use of this metric. This parametric GDG model is then solved using an existing optimization program called DSIDES.

Development of Mono and Multihull Resistance Sustainable Marine Technology Development and Green Innovation

2013 ◽  
pp. 9-36
Author(s):  
I. Ketut Aria Pria Utama ◽  
Andi Jamaluddin
Keyword(s):  
Rapid Growth ◽  
Technology Development ◽  
Dominant Mode ◽  
Relative Merit ◽  
Preliminary Design ◽  
Design Tools ◽  
Short Sea Shipping ◽  
Sea Transportation ◽  
Marine Technology ◽  
Naval Architect

During the last decade, multihull ships have rapidly evolved into a dominant mode of sea transportation. Their particular area of proliferation is in short sea shipping where they show considerable superiority over competitive designs in attributes such as power requirements, economy, space availability, and sea keeping quality. The rapid growth of the market has led to the need for an expanded range of multihull designs in terms of size, speed, and payload diversity (passengers, vehicles, containers). However, even now there is a scarcity of publicly available preliminary design tools for multihull vessels. This fact hinders the ship owner and naval architect from being able to quickly assess the relative merit of alternative potential designs without having to resort to expensive expert consultancy solutions.

An Optimizing Method to Balance Aerodynamic Loading for Gas Turbine Engine Preliminary Design

2013 ◽  
Author(s):  
Qiuye Tu ◽  
Xianzhong Huang ◽  
Yang Shi ◽  
Kun Yang ◽  
Li Zhou
Keyword(s):  
Reference Point ◽  
Second Step ◽  
Preliminary Design ◽  
Aerodynamic Optimization ◽  
Turbine Engine ◽  
Axial Compressors ◽  
Aerodynamic Loading ◽  
Dimensional Parameters ◽  
Point Determination ◽  
Set Up

This paper presents a method to balance aerodynamic loading by optimizing the combined efficiencies of co-axial compressors and turbines for engine preliminary design. Relationships between the aerodynamic and dimensional parameters for co-axial compressors and turbines were set up by nonlinear equations. And the boundary conditions of the equations are thermodynamic parameters and Smith Charts of compressors and turbines. The process of the method includes the initial value guess, reference point determination and aerodynamic optimization. The first step solves approximate stage numbers for co-axial compressors and turbines, and other initial values used in the second step. In the second step, an appropriate solution of the equations determines a reference point on the Smith Chart. The first step is required for a better convergence in the second step due to the nature of the Newton-Raphson solver. In the third step, the combined efficiencies of co-axial compressors and turbines are optimized under the specified constraints. An optimizing tool was developed based on the proposed method. An example of a core engine was analyzed by using this tool. The results showed the reliability and high fidelity of the method.

scholarly journals Algorithm development for aerodynamic preliminary design of multi-stage axial compressors

2016 ◽  
Vol 23 (5) ◽  
pp. 2166-2178
Author(s):  
R. Azizi ◽  
R. Ebrahimi ◽  
M. Ziabasharhagh
Keyword(s):  
Preliminary Design ◽  
Algorithm Development ◽  
Axial Compressors ◽  
Multi Stage

Preliminary Design of Axial Compressors Using Artificial Intelligence and Numerical Optimization Techniques

1991 ◽  
Author(s):  
George Holt ◽  
Stuart Bassler
Keyword(s):  
Numerical Optimization ◽  
Axial Compressor ◽  
Lessons Learned ◽  
Optimization Techniques ◽  
Preliminary Design ◽  
Axial Compressors ◽  
Automated Method ◽  
Design Program ◽  
Compressor Design ◽  
Generic Design

This paper discusses an automated method for optimizing multistage axial compressor designs using a generic design software shell called Engineous®, coupled with an aerodynamic compressor design program called CUS5 (Compressor Unification Study 5). Engineous combines heuristic searching and numerical optimization techniques, and expert systems to explore the design space of turbomachinery components by iterating preliminary design analysis programs written in languages such as FORTRAN and C. The application design and development process and the lessons learned are discussed for the Engineous/CUS5 axial compressor application. This particular application calculates and maintains compressor stall prediction values while optimizing at the operating (design) point, and requires a design vs. stall comparison during each iteration. A trial compressor design problem was investigated using the Engineous application, and the preliminary results of the study are included. Also introduced is a method for varying flowpath walls using shape criteria rather than radii points.

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