An Educational Software Suite for Teaching Design Strategies for Multistage Axial Flow Compressors

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Dario Bruna ◽  
Carlo Cravero ◽  
Mark G. Turner ◽  
Ali Merchant
Keyword(s):  
Educational Software ◽  
Fluid Dynamic ◽  
Axial Flow ◽  
Complete Information ◽  
Design Parameters ◽  
Design System ◽  
Test Case ◽  
Design Strategies ◽  
Research Activity ◽  
Turbomachinery Design

The T-AXI turbomachinery design system, an axisymmetric methodology recently developed with an educational purpose, has shown great capabilities in the redesign of existing axial flow gas turbine components. Different turbomachines, single or multistage configurations, have been already reproduced with excellent overall performance results: examples are the NASA/GE E3 HP compressor and LP turbine. In this paper, the authors present a detailed analysis of the results of a “case-study” application of the code as a complementary tool to be used during a turbomachinery design course. The NASA/GE E3 HP compressor has been chosen as the test case. Starting from the data available in open literature the different steps of the redesign have been reported: from the flowpath generation through the thermodynamic properties distributions to the overall turbomachine performance analysis. Particular attention has been given to some critical aero design parameters. The links to some interesting and useful literature sources are reported. The free-vortex, the only vortex law included in the first version of the code has been used for a first EEE compressor redesign. Different design vortex methodologies have been implemented in the new release of the code and their effects on the angular momentum are reported. The corresponding geometries can also be interfaced to a mesh generator and then the turbomachinery configurations analyzed by a 3D Navier-Stokes solver. In this way the flow field can be carefully analyzed and the fluid-dynamic physics better understood. With the above software structure the student has the opportunity to test the effects of different design strategies on the turbomachinery performance and to understand the need of a hierarchy of tools that give complete information for the multistage turbomachinery design. Finally, in the last section of the paper, the authors present how a project such as T-AXI, developed from their research activity in turbomachinery, numerical methods and CFD, can be included in the education tool CompEdu.

An Educational Software Suite for Teaching Design Strategies for Multistage Axial Flow Compressors

2007 ◽  
Author(s):  
Dario Bruna ◽  
Carlo Cravero ◽  
Mark G. Turner ◽  
Ali Merchant
Keyword(s):  
Educational Software ◽  
Fluid Dynamic ◽  
Axial Flow ◽  
Complete Information ◽  
Design Parameters ◽  
Design System ◽  
Test Case ◽  
Design Strategies ◽  
Research Activity ◽  
Turbomachinery Design

The T-AXI turbomachinery design system, an axisymmetric methodology recently developed with an educational purpose, has shown great capabilities in the redesign of existing axial flow gas turbine components. Different turbomachines, single or multistage configurations, have been already reproduced with excellent overall performance results: examples are the NASA/GE E3 HP compressor and LP turbine. In this paper the authors present a detailed analysis of the results of a “case-study” application of the code, as a complementary tool to be used during a turbomachinery design course. The NASA/GE E3 HP compressor has been chosen as the test case. Starting from the data available in open literature the different steps of the redesign have been reported: from the flowpath generation through the thermodynamic properties distributions to the overall turbomachine performance analysis. Particular attention has been given to some critical aero design parameters. The links to some interesting and useful literature sources are reported. The free-vortex, the only vortex law included in the first version of the code has been used for a first EEE compressor redesign. Different design vortex methodologies have been implemented in the new release of the code and their effects on the angular momentum are reported. The corresponding geometries can also be interfaced to a mesh generator and then the turbomachinery configurations analyzed by a 3-D Navier-Stokes solver. In this way the flow field can be carefully analyzed and the fluid-dynamic physics better understood. With the above software structure the student has the opportunity to test the effects of different design strategies on the turbomachinery performance and to understand the need of a hierarchy of tools that give complete information for the multistage turbomachinery design. Finally, in the last section of the paper, the authors present how a project such as T-AXI, developed from their research activity in turbomachinery, numerical methods and CFD, can be included in the education tool CompEdu.

A Turbomachinery Design Tool for Teaching Design Concepts for Axial-Flow Fans, Compressors, and Turbines

2010 ◽  
Vol 133 (3) ◽  
Author(s):  
Mark G. Turner ◽  
Ali Merchant ◽  
Dario Bruna
Keyword(s):  
Angular Momentum ◽  
Axial Flow ◽  
Design Tool ◽  
Design Parameters ◽  
Design System ◽  
Physical Parameters ◽  
Cross Sectional ◽  
Design Concepts ◽  
Stage Matching ◽  
Turbomachinery Design

A new turbomachinery design system, T-AXI, is described and demonstrated. It is intended primarily for use by educators and students, although it is sophisticated enough for actual designs. The codes, example cases, and user’s manual are available through the authors’ websites. The design system can be used to design multistage compressors and turbines from a small number of physical design parameters. Students can understand the connection between these physical parameters such as the Mach number and flow angles to the cross sectional area and angular momentum. There is also a clear connection between the angular momentum, work, and blade loadings. Loss models are built-in and results are compared against tested geometries. The code also has a built-in blade geometry generator, and the geometry can be the output for running the MISES blade-to-blade solver on each section or visualizing the blades. A single stage compressor from the U.S. Air Force Stage Matching Investigation rig, the 10 stage NASA/GE EEE high pressure compressor, and the NASA/GE EEE 5 stage low pressure turbine have been used to validate T-AXI as a design tool.

A Turbomachinery Design Tool for Teaching Design Concepts for Axial-Flow Fans, Compressors, and Turbines

2006 ◽  
Author(s):  
Mark G. Turner ◽  
Ali Merchant ◽  
Dario Bruna
Keyword(s):  
Angular Momentum ◽  
Web Sites ◽  
Axial Flow ◽  
Design Tool ◽  
Design Parameters ◽  
Design System ◽  
Physical Parameters ◽  
Cross Sectional ◽  
Stage Matching ◽  
Turbomachinery Design

A new turbomachinery design system, T-AXI, is described and demonstrated. It is intended primarily for use by educators and students, although it is sophisticated enough for actual designs. The codes, example cases and a user’s manual are available through the authors’ web sites. The design system can be used to design multistage compressors and turbines from a small number of physical design parameters. Students can understand the connection between these physical parameters such as Mach number and flow angles to the cross sectional area and angular momentum. There is also a clear connection between the angular momentum, work and blade loadings. Loss models are built-in and results are compared against tested geometries. The code also has a built-in blade geometry generator and the geometry can be output for running the MISES blade-to-blade solver on each section or visualizing the blades. A single stage compressor from the US Air Force Stage Matching Investigation rig, the 10 stage NASA/GE EEE high pressure compressor and the NASA/GE EEE 5 stage low pressure turbine have been used to validate T-AXI as a design tool.

CFD-based blade shape optimization of MGT-70(3)axial flow compressor

2019 ◽  
Vol 30 (6) ◽  
pp. 3307-3321 ◽  
Author(s):  
Mohammad Reza Pakatchian ◽  
Hossein Saeidi ◽  
Alireza Ziamolki
Keyword(s):  
Neural Network ◽  
Artificial Neural Network ◽  
Shape Optimization ◽  
Fluid Dynamic ◽  
Axial Compressor ◽  
Axial Flow ◽  
Design Parameters ◽  
Content Type ◽  
Wide Range ◽  
Artificial Neural

Purpose This study aims at enhancing the performance of a 16-stage axial compressor and improving the operating stability. The adopted approaches for upgrading the compressor are artificial neural network, optimization algorithms and computational fluid dynamics. Design/methodology/approach The process starts with developing several data sets for certain 2D sections by means of training several artificial neural networks (ANNs) as surrogate models. Afterward, the trained ANNs are applied to the 3D shape optimization along with parametrization of the blade stacking line. Specifying the significant design parameters, a wide range of geometrical variations are considered by implementation of appropriate number of design variables. The optimized shapes are analyzed by applying computational fluid dynamic to obtain the best geometry. Findings 3D optimal results show improvements, especially in the case of decreasing or elimination of near walls corner separations. In addition, in comparison with the base geometry, numerical optimization shows an increase of 1.15 per cent in total isentropic efficiency in the first four stages, which results in 0.6 per cent improvement for the whole compressor, even while keeping the rest of the stages unchanged. To evaluate the numerical results, experimental data are compared with obtained data from simulation. Based on the results, the highest absolute relative deviation between experimental and numerical static pressure is approximately 7.5 per cent. Originality/value The blades geometry of an axial compressor used in a heavy-duty gas turbine is optimized by applying artificial neural network, and the results are compared with the base geometry numerically and experimentally.

Application and Validation of CFD in a Turbomachinery Design System

2003 ◽  
Author(s):  
Mark R. Anderson ◽  
Fahua Gu ◽  
Paul D. MacLeod
Keyword(s):  
High Performance ◽  
Fluid Dynamic ◽  
Detailed Comparison ◽  
Design System ◽  
Flow Solver ◽  
Streamline Curvature ◽  
Wide Range ◽  
Analysis System ◽  
Pressure Changes ◽  
Turbomachinery Design

CFD (Computational Fluid Dynamics) has enjoyed widespread use in the turbomachinery industry for some time. When coupled with other solvers, such as meanline and streamline curvature, it can be an integral part of a comprehensive design and analysis system. The pbCFD (Pushbutton CFD®) product is the CFD component of Concepts NREC’s Agile Engineering Design System®. It is a structured grid CFD flow solver optimized for turbomachinery analysis. Concepts NREC has made an extensive validation effort over a wide range of diverse turbomachinery stages including, compressors, pumps, and turbines for both radial and axial machines. Detailed comparison to test data of 10 different stages is shown in this paper and clearly demonstrates the high performance of pbCFD in quantifying fluid dynamic losses and pressure changes over a wide range of geometries and flow conditions.

Multi-Disciplinary Design Tool for Axial Flow Turbines

2006 ◽  
Author(s):  
S. C. Kenny ◽  
J. E. D. Gauthier ◽  
X. Huang
Keyword(s):  
Fluid Dynamic ◽  
Axial Flow ◽  
Design Tool ◽  
Single Stage ◽  
Test Case ◽  
Preliminary Design ◽  
Turbine Engine ◽  
Fast Screening ◽  
Design Variables ◽  
Performance Estimates

A preliminary design tool has been created to aid in the design of axial flow turbines. The design tool outputs all of the required geometry and flow conditions for the preliminary design of a single stage axial turbine. Inherent to the tool is its ability to produce performance estimates, both aerodynamically and structurally. The aerodynamic analysis is largely empirical based and makes use of the most up-to-date correlations available in the literature. The tool has been created to obtain a fast estimate of performance and a fast screening of various design variables. The design tool is also required in order to produce a geometrical input for more advanced computational fluid dynamic (CFD) and finite element method (FEM) analyses. A test case has been conducted through the design and development of two single stage turbines for a 1-MW gas turbine engine. The results of the design tool were then compared to those results obtained from extensive CFD and FEM analyses to validate the accuracy of the tool. Overall, the results showed excellent agreement both aerodynamically and structurally.

Computer-Aided Analysis of Hydraulic Reaction Turbines

1997 ◽  
Vol 25 (2) ◽  
pp. 73-91 ◽  
Author(s):  
F. Moukalled ◽  
A. Honein
Keyword(s):  
Engineering Students ◽  
Educational Software ◽  
Axial Flow ◽  
Design Parameters ◽  
Computer Aided Analysis ◽  
Complete Set ◽  
Parameter Versus ◽  
Overall Performance ◽  
User Friendly ◽  
Similarity Laws

A microcomputer-based educational software package designed to help mechanical engineering students to understand hydraulic reaction turbines is described. The software is interactive, menu-driven, and easy-to-use, is written in the Pascal computer language, and runs on IBM PC, or compatible, computers. The program can handle radial, mixed, or axial flow turbine problems by solving for unknown variables through a complete set of equations covering the turbine installation. Using similarity laws, model-prototype problems or operation under different conditions can also be tackled. Furthermore, the program is equipped with graphical utilities that include many diagrammatic sketches of reaction turbines, some recommended charts, and the possibility of drawing velocity triangles when corresponding variables are available. The most important feature of the package is an option that allows one to plot the variation of any parameter versus any other one. Through this option, the student can easily understand and discuss the effects of varying design parameters on the overall performance of the machine. Finally, some special features that are important in making the package user-friendly and encouraging-to-use are also available, and the comprehensive example problem provided demonstrates the capabilities of the package as an instructional tool.

Loss Sources and Magnitudes in Axial-Flow Compressors

1976 ◽  
Vol 98 (3) ◽  
pp. 411-424 ◽  
Author(s):  
C. C. Koch ◽  
L. H. Smith
Keyword(s):  
Fluid Dynamic ◽  
Axial Flow ◽  
Boundary Layer Theory ◽  
Design Parameters ◽  
Vector Diagram ◽  
Airfoil Surface ◽  
Aerodynamic Loading ◽  
Wide Range ◽  
Compressor Design ◽  
Multistage Compressor

A method is presented for calculating the design point efficiency potential of a multistage compressor. Design parameters that affect the efficiency are vector diagram shape, aerodynamic loading level, aspect ratio, solidity, clearances, airfoil maximum and edge thicknesses, annulus area contraction, Mach number, Reynolds number, airfoil surface finish, and part-span shroud placement. Losses associated with off-design operation, blading unsuited to the aerodynamic environment, or poor hardware quality are not considered. The loss model is constructed using rational fluid-dynamic elements, such as boundary layer theory, whenever feasible in an attempt to minimize empirical influences, although some empiricism inevitably enters. The resulting formulation is found to be in satisfactory agreement with multistage compressor experience that covers a wide range of the design parameters.

scholarly journals Clogging sensitivity of flow distributors designed for radially elongated hexagonal pillar array columns: a computational modelling

2021 ◽  
Vol 11 (1) ◽  
Author(s):  
Farideh Haghighi ◽  
Zahra Talebpour ◽  
Amir Sanati-Nezhad
Keyword(s):  
Pressure Drop ◽  
Aspect Ratio ◽  
Contact Zone ◽  
Separation Efficiency ◽  
Fluid Dynamic ◽  
Computational Modelling ◽  
Channel Width ◽  
Fluid Distribution ◽  
Design Parameters ◽  
Pillar Array

AbstractFlow distributor located at the beginning of the micromachined pillar array column (PAC) has significant roles in uniform distribution of flow through separation channels and thus separation efficiency. Chip manufacturing artifacts, contaminated solvents, and complex matrix of samples may contribute to clogging of the microfabricated channels, affect the distribution of the sample, and alter the performance of both natural and engineered systems. An even fluid distribution must be achieved cross-sectionally through careful design of flow distributors and minimizing the sensitivity to clogging in order to reach satisfactory separation efficiency. Given the difficulty to investigate experimentally a high number of clogging conditions and geometries, this work exploits a computational fluid dynamic model to investigate the effect of various design parameters on the performance of flow distributors in equally spreading the flow along the separation channels in the presence of different degrees of clogging. An array of radially elongated hexagonal pillars was selected for the separation channel (column). The design parameters include channel width, distributor width, aspect ratio of the pillars, and number of contact zone rows. The performance of known flow distributors, including bifurcating (BF), radially interconnected (RI), and recently introduced mixed-mode (MMI) in addition to two new distributors designed in this work (MMII and MMIII) were investigated in terms of mean elution time, volumetric variance, asymmetry factors, and pressure drop between the inlet and the monitor line for each design. The results show that except for pressure drop, the channel width and aspect ratio of the pillars has no significant influence on flow distribution pattern in non-clogged distributors. However, the behavior of flow distributors in response to clogging was found to be dependent on width of the channels. Also increasing the distributor width and number of contact zone rows after the first splitting stage showed no improvement in the ability to alleviate the clogging. MMI distributor with the channel width of 3 µm, aspect ratio of the pillars equal to 20, number of exits of 8, and number of contact zones of 3 exhibited the highest stability and minimum sensitivity to different degrees of clogging.

Application of Bifurcation Theory to Axial Flow Compressor Instability

1989 ◽  
Vol 111 (4) ◽  
pp. 426-433 ◽  
Author(s):  
F. E. McCaughan
Keyword(s):  
Parameter Space ◽  
Bifurcation Theory ◽  
Qualitative Difference ◽  
Axial Flow ◽  
Complete Information ◽  
Rotating Stall ◽  
Numerical Work ◽  
System Parameters ◽  
Parametric Effects ◽  
Flow Compressor

When a compression system becomes unstable, the mode of response depends on the operating and system parameters, such as throttle setting and B parameter. Previous numerical work on the model developed by Moore and Greitzer has provided a limited picture of the parametric effects. Applying bifurcation theory to a single-harmonic version of the model has supplied much more complete information, defining the boundaries of each mode of response in the parameter space. Specifically this is shown in a plot of B versus throttle setting, which compares well with the corresponding map produced experimentally. We stress the importance of the shape of the rotating stall characteristic. The analysis shows the qualitative difference between classic surge and deep surge.

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