A New Stage Stacking Technique for Axial-Flow Compressor Performance Prediction

1978 ◽  
Vol 100 (4) ◽  
pp. 698-703 ◽  
Author(s):  
A. R. Howell ◽  
W. J. Calvert
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Dimensional Analysis ◽  
Performance Prediction ◽  
Axial Flow ◽  
One Dimensional ◽  
Through Flow ◽  
Compressor Performance ◽  
Flow Compressor ◽  
Work Done

Modern through-flow solutions, with allowances for losses, etc., give good predictions around design conditions. They are more difficult to apply effectively when individual blade rows are operating under positive stall, negative stall or choke conditions, as can happen off-design in multistage axial-flow compressors of medium and high pressure ratios. A return has been made at the National Gas Turbine Establishment to stage stacking techniques to help solve the off-design performance problems. Basically a new mean radius or one-dimensional analysis has been developed with particular reference to the stall and choke conditions: corrections are then introduced for radial variations and for stage parameters such as blockage and work done factors. Examples on the use of the technique have been selected to illustrate both its success and difficulties.

New Profile Loss Model for Improved Prediction of Transonic Axial Flow Compressor Performance in Choking Region

2015 ◽  
Author(s):  
Sangjo Kim ◽  
Donghyun Kim ◽  
Kuisoon Kim ◽  
Changmin Son ◽  
Myungho Kim ◽  
...  
Keyword(s):  
Performance Prediction ◽  
Incidence Angle ◽  
Axial Flow ◽  
Operating Conditions ◽  
Loss Model ◽  
Axial Flow Compressor ◽  
Compressor Performance ◽  
Loss Models ◽  
Flow Compressor ◽  
Profile Loss

New off-design profile loss models have been developed by performing thorough investigations on compressor performance prediction using one-dimensional stage-stacking approach and three-dimensional computational flow dynamics (CFD) results. Generally, a loss model incorporating various compressor geometry and operating conditions is required to predict the performance of various types of compressors. In this study, three sets of selected loss models were applied to predict axial flow compressor performance using stage-stacking approach. The results were compared with experimental data as well as CFD results. The comparison shows an interesting observation in choking region where the existing loss models cannot capture the rapid decrease in pressure and efficiency while CFD predicted the characteristics. Therefore, an improved off-design profile loss model is proposed for better compressor performance prediction in choking region. The improved model was derived from the correlation between the normalized total loss and the incidence angle. The choking incidence angle, which is a major factor in determining the off-design profile loss, was derived from correlations between the inlet Mach number, throat width-to-inlet spacing ratio, and minimum loss incidence angle. The revised stage-stacking program employing new profile loss model together with a set of loss models was applied to predict a single and multistage compressors for comparison. The results confirmed that the new profile loss model can be widely used for predicting the performance of single and multistage compressor.

scholarly journals A Loss and Deflection Model for Compressor Blading at High Negative Incidence

2019 ◽  
Vol 141 (12) ◽  
Author(s):  
Luis E. Ferrer-Vidal ◽  
Marc Schneider ◽  
Alessandro Allegretti ◽  
Vassilios Pachidis
Keyword(s):  
Performance Prediction ◽  
Axial Flow ◽  
Numerical Approach ◽  
Turning Angle ◽  
Blade Cascade ◽  
Through Flow ◽  
Computational Fluid Dynamics Cfd ◽  
Aerodynamic Parameters ◽  
Flow Compressor ◽  
Performance Estimates

AbstractWhile significant advances have come about for turbomachinery off-design performance characterization using computational fluid dynamics (CFD), the need for quick performance estimates at challenging off-design conditions still requires the use of lower-order models, such as mean-line analyses and through-flow tools. These inviscid tools require blade performance correlations formulated in terms of loss and turning angle as a function of blade geometric and aerodynamic parameters. Traditionally, such correlations have relied on the empirical data from blade cascade tests at nominal incidence conditions. This limitation on the applicability of the blade correlations has caused performance modeling of the sub-idle regime to be off-limits to this type of correlation-based approaches. This paper addresses the development of blade loss and deviation models applicable to the sub-idle regime using a parametric numerical approach. 2D CFD results are used to generate a model that is then applied to mean-line and through-flow analyses aimed at predicting the sub-idle map of an axial flow compressor. The model proves to be a valuable tool for quick sub-idle performance estimates and allows existing correlation-based performance prediction methods to be extended into the sub-idle regime.

Performance Predicting Modeling of Axial-Flow Compressor at Design and Off-Design Conditions

2008 ◽  
Author(s):  
Ali Madadi ◽  
Ali Hajilouy Benisi
Keyword(s):  
Performance Prediction ◽  
Work Performance ◽  
Axial Flow ◽  
Accurate Method ◽  
Performance Characteristics ◽  
One Dimensional ◽  
Axial Flow Compressor ◽  
Dimensional Modeling ◽  
Flow Compressor ◽  
Axial Flow Compressors

Axial flow compressor is one of the most important parts of gas turbine units. Therefore, its design and performance prediction are very important. One-dimensional modeling is a simple, fast and accurate method for performance prediction of any type of compressors with different geometries. In this approach, inlet flow conditions and compressor geometry are known and by considering various compressor losses, velocity triangles at rotor, and stator inlets and outlets are determined, and then compressor performance characteristics are predicted. Numerous models have been developed theoretically and experimentally for estimating various types of compressor losses. In present work, performance characteristics of the axial-flow compressor are predicted based on one-dimensional modeling approach. In this work, models of Lieblein, Koch-Smith, Herrig, Johnsen-Bullock, Pollard-Gostelow, Aungier, Hunter-Cumpsty Reneau are implemented to consider compressor losses, incidence angles, deviation angles, stall and surge conditions. The model results are compared with experimental data to validate the model. This model can be used for various types of single stage axial-flow compressors with different geometries, as well as multistage axial-flow compressors.

Compressor Performance With Water Injection

2001 ◽  
Author(s):  
J. H. Horlock
Keyword(s):  
Specific Heat ◽  
Gas Turbine ◽  
Dimensional Analysis ◽  
Water Injection ◽  
Operating Conditions ◽  
Water Droplets ◽  
One Dimensional ◽  
Design Performance ◽  
Effective Specific Heat ◽  
Compressor Performance

There has been renewed interest recently in the injection of water at inlet to gas turbine plants. As is to be expected there is a drop in temperature at the inlet face to the compressor and this obviously has an effect on compressor performance. But a second effect occurs within the early stages of the compressor itself, associated with an increase in the effective specific heat due to continuing evaporation of the water droplets. Consequently there are movements away from design operating conditions on the stage characteristics. A one-dimensional analysis of compressor off-design performance is developed to illustrate these effects, which appear to be appreciable, even for very small quantities of water injection.

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.

Improving a one-dimensional centrifugal compressor performance prediction method

2005 ◽  
Vol 219 (8) ◽  
pp. 653-659 ◽  
Author(s):  
E Swain
Keyword(s):  
Centrifugal Compressor ◽  
Performance Prediction ◽  
Fluid Dynamic ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Prediction Method ◽  
Compressor Cascade ◽  
One Dimensional ◽  
Compressor Performance ◽  
Cfd Analyses

A one-dimensional centrifugal compressor performance prediction technique that has been available for some time is updated as a result of extracting the component performance from three-dimensional computational fluid dynamic (CFD) analyses. Confidence in the CFD results is provided by comparison of overall performance for one of the compressor examples. The extracted impeller characteristic is compared with the original impeller loss model, and this indicated that some improvement was desirable. The position of least impeller loss was determined using a traditional axial compressor cascade method, and suitable algebraic expressions were derived to match the CFD data. The merit of the approach lies with the relative ease that CFD component performance currently can be achieved and adjusting one-dimensional methods to agree with the CFD-derived models.

Design and Development of a 12:1 Pressure Ratio Compressor for the Ruston 6-MW Gas Turbine

1982 ◽  
Author(s):  
F. Carchedi ◽  
G. R. Wood
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Aerodynamic Design ◽  
Design And Development ◽  
Surge Line ◽  
Flow Compressor ◽  
Industrial Gas Turbine ◽  
Spanwise Flow

This paper describes the design and development of a 15-stage axial flow compressor for a −6MW industrial gas turbine. Detailed aspects of the aerodynamic design are presented together with rig test data for the complete characteristic including stage data. Predictions of spanwise flow distributions are compared with measured values for the front stages of the compressor. Variable stagger stator blading is used to control the position of the low speed surge line and the effects of the stagger changes are discussed.

The Elimination of Wall Effects in Axial-Flow Compressor Stages

1953 ◽  
Vol 57 (508) ◽  
pp. 241-243
Author(s):  
J. M. Stephenson
Keyword(s):  
Velocity Profile ◽  
Axial Velocity ◽  
Radial Profile ◽  
Axial Flow ◽  
Gas Velocity ◽  
Wall Effects ◽  
Axial Velocity Component ◽  
Axial Velocity Profile ◽  
Flow Compressor ◽  
Work Done

Compressor stages are usually designed on the assumption that the gas velocity is nowhere affected by the friction at the walls. The only way in which viscosity is taken into account is in the assumed efficiency, and in a guessed “work-done factor,” which ensures that by aiming high the required work is actually attained.It is known that the radial profile of the axial velocity component becomes more and more peaked through successive stages of a compressor, so that the assumptions just quoted become very inaccurate. It is possible that the efficiency of a stage could be raised considerably if the axial velocity profile were controlled; moreover up to 20 per cent. more work could be done if a “ work-done factor ” did not have to be applied.

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