scholarly journals Derivation of Compressor Stage Characteristics, for Accurate Overall Performance Map Prediction

1994 ◽  
Author(s):  
A. Tsalavoutas ◽  
A. Stamatis ◽  
K. Mathioudakis
Keyword(s):  
Optimization Techniques ◽  
Accurate Prediction ◽  
Test Cases ◽  
Initial Stage ◽  
Performance Map ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
Overall Performance ◽  
Compressor Map ◽  
Physical Phenomena

In the present paper a method for deriving stage characteristics, which can provide accurate prediction of a multistage compressor map is presented. The method combines optimization techniques with the principles of stage stacking. The stage characteristics are produced by modifying some initial generic ones, until the desired accuracy in the prediction at selected points on the overall map is achieved. There are several reasons why prediction based on the initial stage characteristics can be inaccurate, the following three being the main ones. The first is due to inaccuracy in the representation of the stage characteristics themselves. The second is due to lack of exact knowledge of the geometric data of the various stages. Finally the third reason consists of the “weak” modelling representation of complex physical phenomena with one dimensional approaches. Therefore, even when the exact stage characteristics are known, this does not guarantee the accurate prediction of the compressor performance. On account of the above, it is preferable to acquire realistic “effective” stage characteristics which can be used for synthesizing overall compressor characteristics and assessing the effects of stage faults. In this paper, both of these aspects are successfully tackled as demonstrated by applying the method to different test cases.

Compressor Maps and Coupling: Symmetry, Paradox, and Clarity

2021 ◽  
Author(s):  
Benjamin Iwrey
Keyword(s):  
Temperature Ratio ◽  
Independent Variables ◽  
Dependent Variables ◽  
In Series ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
Compressor Map ◽  
Flow Flux ◽  
Operating Points ◽  
Corrected Flow

Abstract The most common compressor map framework, referred to here as the β-framework, will be shown to suffer from limitations that grow more troublesome in the multiple-map environment. When maps are coupled in series in the β-framework, it is very common to find operating points that are physically unrealizable, but these cannot generally be avoided without first generating them. A feasible situation is described in which the β-framework leads to an apparent physical paradox. In the proposed S-framework, the map itself is recast in terms of independent variables (corrected speed and exit corrected flow) and dependent variables (inlet corrected flow and temperature ratio). The propagation of information in map coupling is split into an upstream-marching corrected flow ‘flux’ and a downstream-marching temperature ‘flux’. Finding the equilibrium operating point requires only finding a simple intersection between curves. The S-framework is then developed further into a more compact S’-framework that exhibits a natural set of qualitative symmetries. The S- and S’-frameworks are shown to simplify compressor map expression, resolve the problems shown with the β-framework, and aid intuition with regard to off-design phenomena. The resolution of the paradox using the S’-framework is a new description of multistage compressor performance hysteresis.

The Stacking of Compressor Stage Characteristics to Give an Overall Compressor Performance Map

1962 ◽  
Vol 13 (4) ◽  
pp. 349-367 ◽  
Author(s):  
M. D. C. Doyle ◽  
S. L. Dixon
Keyword(s):  
Axial Compressor ◽  
Compressor Stage ◽  
Individual Stage ◽  
Optimum Performance ◽  
Method Of Calculation ◽  
Multi Stage ◽  
Performance Map ◽  
Compressor Performance ◽  
Overall Performance ◽  
The Individual

SummaryA method of calculation is developed to compute the overall performance of a multi-stage axial compressor, from a knowledge of the individual stage characteristics, by a “stacking” technique. Compressor models are designed and their overall performance calculated. These results are compared to show, qualitatively, the effect of alterations in design and stage performance on overall performance and to find how compressors should be designed for optimum performance.

A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers

2019 ◽  
Vol 0 (0) ◽  
Author(s):  
Antonios Fatsis ◽  
Nikolaos Vlachakis ◽  
George Leontis
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Small Diameter ◽  
Impeller Speed ◽  
Ic Engine ◽  
High Rotational Speed ◽  
Characteristic Lines ◽  
Performance Map ◽  
Compressor Performance ◽  
Compressor Map

Abstract Centrifugal compressor performance map prediction is of primary importance for safe and effective operation of turbochargers. This article is a contribution on compressor map prediction using empirical relations based on automotive turbocharger manufacturers’ performance maps. The present method evaluates the minimum and the maximum air flow rates, as well as the maximum compressor pressure ratio by original empirical equations exploiting impeller geometrical data. Newly introduced equations based on the mass flows and the maximum pressure ratio acquired above provide the compressor characteristic lines. The method is validated by applying it to various commercial automotive turbochargers with known performance maps from their manufacturers. At intermediate values of impeller speed, where the turbocharger is expected to match the engine, the computed compressor map agrees to the manufacturer’s data, while, differences are observed at the maximum impeller speed line. From the cases examined, it can be stated that the present model can be applied to predict small diameter, high rotational speed compressor performance, particularly at the high efficiency region that the turbocharger is supposed to match the IC engine.

scholarly journals A New Method for the Prediction of Compressor Performance Maps Using One-Dimensional Row-by-Row Analysis

1995 ◽  
Author(s):  
Magdy S. Attia ◽  
M. Taher Schobeiri
Keyword(s):  
Simple Method ◽  
Design Efficiency ◽  
Turbine Engine ◽  
One Dimensional ◽  
Operational Characteristics ◽  
Performance Map ◽  
High Pressure Stage ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
Point Data

This article presents a new and simple method for the prediction of the compressor performance maps based on the geometry and the design point data. The method accurately calculates the compressor performance map based on a comprehensive one-dimensional row-by-row analysis. Off-design efficiency is determined using a modified diffusion factor and an advanced loss calculation method that allows for the accurate prediction of the operational characteristics of the compressor in the post-stall regime. Three different compressor performance maps are generated for low, intermediate and high pressure stage groups using the geometry of the multistage compressor of a power generation gas turbine engine. The results are compared with the maps obtained from experiment.

The Design Analysis of the Damaged Compressor Blade Impact on the Aerodynamic Parameters

2020 ◽  
Author(s):  
Konstantin S. Fedechkin ◽  
Maxim V. Kuzmin ◽  
Evgeni U. Marchukov
Keyword(s):  
Traditional Approach ◽  
Leading Edge ◽  
Calculation Model ◽  
Compressor Blades ◽  
Geometry Model ◽  
Aerodynamic Parameters ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
Compressor Map ◽  
Defects Analysis

Abstract The research is about the traditional approach in defects assessment, like damages in aviation engine blades and problems in their further use based on the defects analysis not in one blade or stage but in the multistage compressor as a whole. When an airplane is in operation there can be incidents: birds in flight and a small stones and different metal object on the ground. When they penetrate into the engine, the fan’s blades are damaged. The software that simulates geometry model of blade damages has been developed. The calculation model of the damaged blade has been developed on the basis of real engine compressors. The calculation model of the compressor covers procedures for mesh generation and CFD code calculations. This model has been verified by experimental data. It has been studied how compressor blades with nicks and bending affect the compressor performance and how compressor map changes. The studies resulted in the following conclusions: -The existing limits on damages size do not cause serious problems in operation. It was confirmed by the calculation result. - As the result of this compressor study, the critical size of blade nicks (more than 4mm or more than 6% blade chord) and bending (more than 0,023b in the leading edge in the circumferential direction) has been identified in terms of aerodynamics.

Use of Experimental Interstage Performance Data to Obtain Optimum Performance of Multistage Axial Compressors

1962 ◽  
Vol 84 (2) ◽  
pp. 187-194 ◽  
Author(s):  
Laurence E. Brown ◽  
Fred G. Groh
Keyword(s):  
Performance Data ◽  
Focus Attention ◽  
Simple Method ◽  
Axial Compressors ◽  
One Stage ◽  
Performance Map ◽  
Multistage Compressors ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
The Individual

Experimental interstage performance data provide the most useful basis currently available for correction of faults in performance of multistage compressors. However, to describe stage performance adequately requires much more information than the amount needed to describe over-all compressor performance, and to interpret the data requires that all of this information be correlated. Because the wealth of the data may conceal its meaning, some simple method is needed to focus attention on the matching of one stage to another and to the over-all compressor as well. A technique is presented whereby performance of individual stages can be depicted graphically upon the performance map of an over-all multistage compressor. Through this presentation the individual and over-all effects can be examined together. Insight is afforded into performance relationships of one stage to another; and faults can be diagnosed if any exist in the matching, radial or axial, of individual stages. Changes of blade geometry can then be prescribed upon a clear and explicit basis. To illustrate use of the technique, data are presented describing gains that have been achieved experimentally.

scholarly journals Influence of Seal Cavity Leakage Flow on Compressor Performance Investigated with a Circumferentially Averaged Method

2021 ◽  
Vol 11 (2) ◽  
pp. 780
Author(s):  
Dong Liang ◽  
Xingmin Gui ◽  
Donghai Jin
Keyword(s):  
Flow Field ◽  
Pressure Ratio ◽  
Interaction Mechanism ◽  
Main Flow ◽  
Leakage Flow ◽  
Destructive Effect ◽  
Through Flow ◽  
Compressor Performance ◽  
Overall Performance ◽  
Flow Blockage

In order to investigate the effect of seal cavity leakage flow on a compressor’s performance and the interaction mechanism between the leakage flow and the main flow, a one-stage compressor with a cavity under the shrouded stator was numerically simulated using an inhouse circumferentially averaged through flow program. The leakage flow from the shrouded stator cavity was calculated simultaneously with main flow in an integrated manner. The results indicate that the seal cavity leakage flow has a significant impact on the overall performance of the compressor. For a leakage of 0.2% of incoming flow, the decrease in the total pressure ratio was 2% and the reduction of efficiency was 1.9 points. Spanwise distribution of the flow field variables of the shrouded stator shows that the leakage flow leads to an increased flow blockage near the hub, resulting in drop of stator performance, as well as a certain destructive effect on the flow field of the main passage.

scholarly journals Simulation of Compressor Performance Deterioration due to Erosion

1989 ◽  
Author(s):  
W. Tabakoff ◽  
A. N. Lakshminarasimha ◽  
M. Pasin
Keyword(s):  
Fault Model ◽  
Experimental Results ◽  
Performance Tests ◽  
Individual Stage ◽  
One Stage ◽  
Before And After ◽  
Performance Deterioration ◽  
Compressor Performance ◽  
Multistage Compressor ◽  
The Individual

Experimental results obtained from cascades and one stage compressor performance tests before and after erosion were used to test a fault model to represent erosion. This model was implemented on a stage stacking program developed to demonstrate the effect of erosion in a multistage compressor. The effect of the individual stage erosion on the overall compressor performance is also demonstrated.

Active control of surge in centrifugal compressors using a brain emotional learning-based intelligent controller

2015 ◽  
Vol 230 (16) ◽  
pp. 2828-2839 ◽  
Author(s):  
Ali Jokar ◽  
Roozbeh Zomorodian ◽  
Mohammad Bagher Ghofrani ◽  
Pooya Khodaparast
Keyword(s):  
Neural Network ◽  
Artificial Neural Network ◽  
High Fidelity Simulation ◽  
Variable Speed ◽  
Load Line ◽  
Neuro Fuzzy ◽  
Performance Map ◽  
Compressor Performance ◽  
Artificial Neural ◽  
Brain Emotional Learning

Efforts have been targeted at providing a comprehensive simulation of a centrifugal compressor undergoing surge. In the simulation process, an artificial neural network was utilized to produce an all-inclusive performance map encompassing those speeds not available in the provided curves. Two positive scenarios for the shaft speed, constant, and variable, were undertaken, and effects of load line on the dynamic response of the compressor have been studied. In order to achieve high-fidelity simulation in the variable speed case, an artificial neural network was utilized to produce an all-inclusive performance map encompassing those speeds not available in the provided curves. Moreover, effects of dynamic characteristics of throttle valve were also investigated. A novel controlling scheme, based on neuro-fuzzy control philosophy, was implemented to stabilize the compressor performance in the unstable region. Results indicate that if applied, this scheme could produce practical and satisfactory outcomes, possessing certain virtues compared to available techniques.

scholarly journals Evolutionary Algorithms for Constrained Parameter Optimization Problems

1996 ◽  
Vol 4 (1) ◽  
pp. 1-32 ◽  
Author(s):  
Zbigniew Michalewicz ◽  
Marc Schoenauer
Keyword(s):  
Nonlinear Programming ◽  
Evolutionary Algorithms ◽  
Evolutionary Computation ◽  
Numerical Optimization ◽  
Optimization Problems ◽  
Optimization Techniques ◽  
Test Cases ◽  
Nonlinear Constraints ◽  
Nonlinear Programming Problem ◽  
General Nonlinear Programming

Evolutionary computation techniques have received a great deal of attention regarding their potential as optimization techniques for complex numerical functions. However, they have not produced a significant breakthrough in the area of nonlinear programming due to the fact that they have not addressed the issue of constraints in a systematic way. Only recently have several methods been proposed for handling nonlinear constraints by evolutionary algorithms for numerical optimization problems; however, these methods have several drawbacks, and the experimental results on many test cases have been disappointing. In this paper we (1) discuss difficulties connected with solving the general nonlinear programming problem; (2) survey several approaches that have emerged in the evolutionary computation community; and (3) provide a set of 11 interesting test cases that may serve as a handy reference for future methods.

Sign in / Sign up

Export Citation Format

Share Document