The Use of Artificial Neural Networks for Performance Prediction of Return Channels for Industrial Centrifugal Compressors

2002 ◽  
Author(s):  
Simone Pazzi ◽  
Francesci Martelli ◽  
Vittorio Michelassi ◽  
Marco Giachi
Keyword(s):  
Performance Prediction ◽  
Navier Stokes ◽  
Geometrical Parameters ◽  
Preliminary Design ◽  
Performance Indices ◽  
Centrifugal Compressors ◽  
Flow Solver ◽  
Design And Optimization ◽  
Return Channel ◽  
Typical Configuration

An innovative procedure for the preliminary design and optimization of return channels for centrifugal compressors is explained. A typical configuration of bladed return channel for industrial centrifugal compressors is analyzed by means of a well-known commercial Navier-Stokes solver. A set of geometrical parameters groups is chosen in order to represent the most significant changes in geometry with respect to the base configuration. A series of new return channel configurations is obtained as the result of variations of one or more geometrical parameters. Each geometry obtained with this procedure is analyzed by the flow solver which returns a set of accurately chosen performance indices quantifying aerodynamic losses and distortions at the eye of the downstream impeller. The results thus obtained are used to train a simple one-layer Neural Network (NN) which is afterwards interrogated to compute some performance maps linking the performance indices to the three most relevant geometrical parameters. A further computation is carried out on some return channel configurations which have not been previously analyzed. The results confirm that the interpolator is able to predict the return channels performances with a good accuracy. The resulting performance maps, validated by some random tests, seem to be a valid tool for performance prediction of this kind of return channels.

The Development of an Aerodynamic Performance Prediction Tool for Modern Axial Flow Compressor Profiles

2006 ◽  
Author(s):  
Dario Bruna ◽  
Carlo Cravero ◽  
Mark G. Turner
Keyword(s):  
Performance Prediction ◽  
Parametric Design ◽  
Flow Analysis ◽  
Axial Flow ◽  
Navier Stokes ◽  
Flow Angle ◽  
Flow Solver ◽  
Aerodynamic Loss ◽  
Axial Flow Compressor ◽  
Flow Compressor

The development of a computational tool (MP-LOS) for the aerodynamic loss modeling and prediction for axial-flow compressor blade sections is presented in this paper. A state-of-the-art quasi 3-D flow solver, MISES, has been used for the flow analysis on existing airfoil geometries in many working conditions. Different values of inlet flow angle, inlet Mach number, AVDR, Reynolds number and solidity have been chosen to investigate a possible working range. The target is a loss prediction formulation that will be introduced into throughflow or axisymmetric Navier-Stokes codes for the performance prediction of multistage axial flow compressors. The loss coefficient has been correlated to the flow parameters that have shown an influence on the profile loss for the blades under study. The proposed correlation, using the described computational approach, can be extended to any profile family with the aid of any code for the parametric design of blade profiles.

Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor

2004 ◽  
Vol 126 (5) ◽  
pp. 799-806 ◽  
Author(s):  
A´rpa´d Veress ◽  
Rene´ Van den Braembussche
Keyword(s):  
Design Method ◽  
Design Procedure ◽  
Leading Edge ◽  
Secondary Flows ◽  
Inverse Design ◽  
Navier Stokes ◽  
Design And Optimization ◽  
The Cross ◽  
Return Channel ◽  
The Impact

The design and optimization of a multistage radial compressor vaneless diffuser, cross-over and return channel is presented. An analytical design procedure for 3D blades with prescribed load distribution is first described and illustrated by the design of a 3D return channel vane with leading edge upstream of the cross-over. The analysis by means of a 3D Navier–Stokes solver shows a substantial improvement of the return channel performance in comparison with a classical 2D channel. Most of the flow separation inside and downstream of the cross-over could be avoided in this new design. The geometry is further improved by means of a 3D inverse design method to smooth the Mach number distribution along the vanes at hub and shroud. The Navier–Stokes analysis shows a rather modest impact on performance but the calculated velocity distribution indicates a more uniform flow and hence a larger operating range can be expected. The impact of vane lean on secondary flows is investigated and further performance improvements have been obtained with negative lean.

An optimum set of loss models for performance prediction of centrifugal compressors

1997 ◽  
Vol 211 (4) ◽  
pp. 331-338 ◽  
Author(s):  
H W Oh ◽  
E S Yoon ◽  
M K Chung
Keyword(s):  
Performance Prediction ◽  
Prediction Method ◽  
General Purpose ◽  
Preliminary Design ◽  
Centrifugal Compressors ◽  
Operational Characteristics ◽  
Performance Curves ◽  
Reliable Performance ◽  
Performance Analyses ◽  
Loss Models

The present study has tested most of the loss models previously published in the open literature and found an optimum set of empirical loss models for a reliable performance prediction of centrifugal compressors. In order to improve the prediction of efficiency curves, this paper recommends a modified parasitic loss model. The performance analyses by using various empirical loss models are also compared with those by the two-zone modelling. Predicted performance curves by the proposed optimum set agree fairly well with experimental data for a variety of centrifugal compressors. The prediction method developed through this study can serve as a tool for preliminary design and assist the understanding of the operational characteristics of general purpose centrifugal compressors.

Low Fidelity Design and Analysis Parametric Tool for General Centrifugal Compressors

2019 ◽  
Author(s):  
Sai Muppana ◽  
Kiran Siddappaji ◽  
Shaaban Abdallah ◽  
Mark Turner
Keyword(s):  
Centrifugal Compressor ◽  
Performance Prediction ◽  
Pressure Ratio ◽  
Design Stage ◽  
Analysis Tool ◽  
Preliminary Design ◽  
Centrifugal Compressors ◽  
Preliminary Design Stage ◽  
Successful Design ◽  
Definition Of

Abstract Performance prediction and blade generation in a preliminary design stage of centrifugal compressors is critical to have a successful design. In this paper, a one-dimensional meanline design and analysis tool has been developed for single-rotor and novel multi-rotor centrifugal impellers. Loss models used for performance prediction of single stage compressors have been extended to single hub multi-rotor compressors to evaluate isentropic efficiency and pressure ratio. Stage conditions like work ratio and stator turning angle are given as input parameters and the tool computes flow properties along the meanline and also, generates velocity triangles, streamlines, smooth definition of blade angles at different spanwise sections. The tool acts a preprocessor for Tblade3 which is an in-house 3D parametric blade geometry generator to create blades. A 0D tool has been developed for multi-rotor impellers to provide an estimate of work ratio. 0D coupled with 1D tool can provide a good preliminary design point. The process of 0D to blade generation has been automated enabling it to connect with high-fidelity analysis. The motivation to create this tool is to calculate flow angles, metal angles, velocity triangles, ease of parametric modification and reduce aero-design cycle time. This tool is modular which adds the flexibility of capability extension. The code is validated with DLR centrifugal compressor experimental data. The 1D tool is also used to calculate performance and blade angles for the novel single hub multi-rotor centrifugal compressor demonstrating the versatility of the low fidelity tool. The tool suite is written in Python and is open source https://github.com/msaisiddhartha/CIMdes.

scholarly journals Design and Optimization of a Fuzzy Logic System for Academic Performance Prediction

Symmetry ◽  
2021 ◽  
Vol 13 (1) ◽  
pp. 133
Author(s):  
Juan A. Rojas ◽  
Helbert E. Espitia ◽  
Lilian A. Bejarano
Keyword(s):  
Academic Performance ◽  
Performance Prediction ◽  
Teaching Methods ◽  
Continuous Monitoring ◽  
Educational Institution ◽  
Educational Institutions ◽  
Educational Support ◽  
Design And Optimization ◽  
Monitoring Process ◽  
Logic System

Currently, in Colombia, different problems in education exist; one of them is the inconvenience in tracing and controlling the learning trajectories that decide the topics taught in the country’s educational institutions. This work aims to implement a logic-based system that allows teachers and educational institutions to carry out a continuous monitoring process of students’ academic performance, facilitating early corrections of errors or failures in teaching methods, to promote educational support spaces within the educational institution.

Simulation of the Gap Resonance Between Two Rectangular Barges in Regular Waves by a Free Surface Viscous Flow Solver

2013 ◽  
Author(s):  
B. Elie ◽  
G. Reliquet ◽  
P.-E. Guillerm ◽  
O. Thilleul ◽  
P. Ferrant ◽  
...  
Keyword(s):  
Experimental Data ◽  
Free Surface ◽  
Viscous Flow ◽  
Stokes Equations ◽  
Resonance Phenomenon ◽  
Navier Stokes ◽  
Regular Waves ◽  
Navier Stokes Equations ◽  
Flow Solver ◽  
Gap Resonance

This paper compares numerical and experimental results in the study of the resonance phenomenon which appears between two side-by-side fixed barges for different sea-states. Simulations were performed using SWENSE (Spectral Wave Explicit Navier-Stokes Equations) approach and results are compared with experimental data on two fixed barges with different headings and bilges. Numerical results, obtained using the SWENSE approach, are able to predict both the frequency and the magnitude of the RAO functions.

Simulation of laminar-turbulent transition with an explicit Navier-Stokes flow solver

1995 ◽  
Vol 11 (6) ◽  
pp. 1187-1194 ◽  
Author(s):  
Lyle D. Dailey ◽  
Ian K. Jennions ◽  
Paul D. Orkwis
Keyword(s):  
Stokes Flow ◽  
Navier Stokes ◽  
Flow Solver ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition
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