An Analysis of Axial Compressors Fouling and a Cleaning Method of Their Blading

1996 ◽  
Author(s):  
A. P. Tarabrin ◽  
V. A. Schurovsky ◽  
A. I. Bodrov ◽  
J.-P. Stalder
Keyword(s):  
Mathematical Model ◽  
Axial Compressor ◽  
Axial Compressors ◽  
Cleaning Method ◽  
Engine Efficiency ◽  
Calculation Results ◽  
On Line ◽  
Compressor Performance ◽  
High Level ◽  
Industrial Gas Turbine

The paper describes the phenomenon of axial compressor fouling due to aerosols contained in the air. Key parameters having effect on the level of fouling are determined. A mathematical model of a progressive compressor fouling using the stage-by-stage calculation method is developed. Calculation results on the influence of fouling on the compressor performance are presented. A new index of sensitivity of axial compressors to fouling is suggested. The paper gives information about the Turbotect’s deposit cleaning method of compressor blading and the results of its application on an operating industrial gas turbine. Regular on line and off line washings of compressor flow path make it possible to maintain a high level of engine efficiency and output.

An Analysis of Axial Compressor Fouling and a Blade Cleaning Method

1998 ◽  
Vol 120 (2) ◽  
pp. 256-261 ◽  
Author(s):  
A. P. Tarabrin ◽  
V. A. Schurovsky ◽  
A. I. Bodrov ◽  
J.-P. Stalder
Keyword(s):  
Mathematical Model ◽  
Axial Compressor ◽  
Axial Compressors ◽  
Cleaning Method ◽  
Engine Efficiency ◽  
Calculation Results ◽  
On Line ◽  
Compressor Performance ◽  
High Level ◽  
Industrial Gas Turbine

The paper describes the phenomenon of axial compressor fouling due to aerosols contained in the air. Key parameters having effect on the level of fouling are determined. A mathematical model of a progressive compressor fouling using the stage-by-stage calculation method is developed. Calculation results on the influence of fouling on the compressor performance are presented. A new index of sensitivity of axial compressors to fouling is suggested. The paper gives information about Turbotect’s deposit cleaning method of compressor blading and the results of its application on an operating industrial gas turbine. Regular on-line and off-line washings of the compressor flow path make it possible to maintain a high level of engine efficiency and output.

scholarly journals Inter-Stage Dynamic Performance of an Axial Compressor of a Twin-Shaft Industrial Gas Turbine

Machines ◽  
2020 ◽  
Vol 8 (4) ◽  
pp. 83
Author(s):  
Samuel Cruz-Manzo ◽  
Senthil Krishnababu ◽  
Vili Panov ◽  
Chris Bingham
Keyword(s):  
Gas Turbine ◽  
Dynamic Performance ◽  
Axial Compressor ◽  
Modeling Framework ◽  
Axial Compressors ◽  
Stage Performance ◽  
Compressor Map ◽  
Stage Characteristic ◽  
Industrial Gas Turbine ◽  
Semi Empirical

In this study, the inter-stage dynamic performance of a multistage axial compressor is simulated through a semi-empirical model constructed in the Matlab Simulink environment. A semi-empirical 1-D compressor model developed in a previous study has been integrated with a 0-D twin-shaft gas turbine model developed in the Simulink environment. Inter-stage performance data generated through a high-fidelity design tool and based on throughflow analysis are considered for the development of the inter-stage modeling framework. Inter-stage performance data comprise pressure ratio at various speeds with nominal variable stator guide vane (VGV) positions and with hypothetical offsets to them with respect to the gas generator speed (GGS). Compressor discharge pressure, fuel flow demand, GGS and power turbine speed measured during the operation of a twin-shaft industrial gas turbine are considered for the dynamic model validation. The dynamic performance of the axial-compressor, simulated by the developed modeling framework, is represented on the overall compressor map and individual stage characteristic maps. The effect of extracting air through the bleed port in the engine center-casing on transient performance represented on overall compressor map and stage performance maps is also presented. In addition, the dynamic performance of the axial-compressor with an offset in VGV position is represented on the overall compressor map and individual stage characteristic maps. The study couples the fundamental principles of axial compressors and a semi-empirical modeling architecture in a complementary manner. The developed modeling framework can provide a deeper understanding of the factors that affect the dynamic performance of axial compressors.

Comparison of Controlled Diffusion Airfoils With Conventional NACA 65 Airfoils Developed for Stator Blade Application in a Multistage Axial Compressor

1985 ◽  
Vol 107 (2) ◽  
pp. 494-498 ◽  
Author(s):  
H. Rechter ◽  
W. Steinert ◽  
K. Lehmann
Keyword(s):  
Axial Compressor ◽  
Test Facility ◽  
Axial Compressors ◽  
Controlled Diffusion ◽  
Diffusion Technique ◽  
Precise Prediction ◽  
Stator Blade ◽  
Compressor Performance ◽  
Velocity Triangle ◽  
Transonic Cascade

In their transonic cascade wind tunnel, DFVLR has done measurements on a conventional NACA 65, as well as on a controlled diffusion airfoil, designed for the same velocity triangle at supercritical inlet condition. These tested cascades represent the first stator hub section of a three-stage axial/one-stage radial combined compressor developed by MTU with the financial aid of the German Ministry of Research and Technology. One aspect of this project was the verification of the controlled diffusion concept for axial compressor blade design, in order to demonstrate the capabilities of some recent research results which are now available for industrial application. The stator blades of the axial compressor section were first designed using NACA 65 airfoils. In the second step, the controlled diffusion technique was applied for building a new stator set. Both stator configurations were tested in the MTU compressor test facility. Cascade and compressor tests revealed the superiority of the controlled diffusion airfoils for axial compressors. In comparison to the conventional NACA blades, the new blades obtained a higher efficiency. Furthermore, a closer matching of the compressor performance data to the design requirements was possible due to a more precise prediction of the turning angle.

Axial Compressor Performance Maintenance

2005 ◽  
Author(s):  
Philip Levine ◽  
Leonard Angello
Keyword(s):  
Thin Film ◽  
Axial Compressor ◽  
Economic Potential ◽  
Performance Loss ◽  
Model Based ◽  
Optimal Maintenance ◽  
On Line ◽  
Compressor Performance

Methods of compressor performance maintenance for large utility combustion turbines continue to evolve. On-line water wash systems used to recover performance loss due to fouling are evolving that use less water. This paper derives a water wash model based on a thin film of water covering the airfoil surfaces. The economic potential for recovering “unrecoverable” losses due to increased roughness and erosion is evaluated. As an outage is needed to remove the compressor cover and perform the maintenance, the approach is to identify the most beneficial maintenance actions and an optimal maintenance interval.

Effect of a Gap Between Inner Casing and Stator Blade on Axial Compressor Performance

2010 ◽  
Author(s):  
Changyong Lee ◽  
Jaewook Song ◽  
Sungryong Lee ◽  
Dongmin Hong
Keyword(s):  
Geometric Modeling ◽  
Axial Compressor ◽  
Flow Distribution ◽  
Navier Stokes ◽  
Engine Operation ◽  
Turbine Engine ◽  
Stator Blade ◽  
Compressor Performance ◽  
Industrial Gas Turbine ◽  
Test Result

The small gap at stator hub section of 10-stage axial compressor of small power class industrial gas turbine engine was studied to confirm its effect on compressor analysis result. This gap is allowed for manufactural tolerance and thermal expansion during engine operation. For the convenient purpose of CFD geometric modeling, such gap was simplified and the 3D Navier-Stokes code was used to predict the compressor performance then compared the results with the case without a gap. In the case of calculation without a gap, the performance was estimated to be lower than that of test result. It is because of the presence of 3D separation at hub corner of every stator except on the 1st and 2nd stator. The CFD calculation shows that, with a gap, the stall observed at hub corner vanished and the predicted compressor performance agrees well with the test result. From this, it is concluded that the existence of a gap between inner casing and stator brings a considerable effects on the compressor flow distribution and must be taken into account in the design.

scholarly journals Development of mathematical model and computer program for primary design of transonic axial compressor

2020 ◽  
Vol 4 (4) ◽  
pp. 16-27
Author(s):  
A. I. Borovkov ◽  
◽  
Yu. B. Galerkin ◽  
O. A. Solovieva ◽  
A. A. Drozdov ◽  
...  
Keyword(s):  
Mathematical Model ◽  
Pressure Loss ◽  
Incidence Angle ◽  
Axial Compressor ◽  
Compressor Stage ◽  
Empirical Coefficient ◽  
Axial Compressors ◽  
Profile Losses ◽  
Transonic Axial Compressor ◽  
The Mathematical Model

The mathematical model underlying the program for calculating and designing axial compressors is presented. The process of calculating the pressure loss in the elements of the axial compressor stage flow path is described. The loss coefficient consists of losses on the limiting surfaces, secondary losses and profile losses. The effect of roughness on the pressure loss is taken into account by introducing the corresponding empirical coefficient. An algorithm for calculating the blades and vanes angles of the impeller and the guide apparatus is presented by calculating the incidence angle and the lag angle of the flow. The flow lag angle is the sum of the lag angle of the flow on the profile and the lag angle due to viscous flow on the limiting surfaces

Interstage Injection System for Heavy Duty Industrial Gas Turbine Model 7EA

2001 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Injection System ◽  
Heavy Duty ◽  
Gas Turbine Unit ◽  
Line System ◽  
Axial Compressors ◽  
New Methods ◽  
Start Up ◽  
On Line ◽  
Industrial Gas Turbine

This paper describes new methods of cleaning large multistage axial compressors that are the part of Gas Turbine Unit (GTU). Existing, standard method of compressor cleaning are on-line and off-line. In both cases of compressor cleaning clean water and appropriate detergents are mixed to remove dirt deposits from the blade surface. The on-line system is attractive because the cleaning is done when GTU is under full load. The on-line compressor cleaning slows down inevitable dirt depositing. Offline cleaning is much more effective than on-line cleaning. The negative side of off-line cleaning is that GTU must be shut down. In case of large GTU the processes of shut down and start up require significant amount of time. This paper also incorporates the efforts required to install Inter-stage Injection System (IIS) in one GTU in Watson Cogeneration Company (WCC).

Aerodynamic and Thermodynamic Effects of Coolant Injection on Axial Compressors

1963 ◽  
Vol 14 (4) ◽  
pp. 331-348 ◽  
Author(s):  
P. G. Hill
Keyword(s):  
Axial Compressor ◽  
Experimental Results ◽  
Axial Compressors ◽  
Coolant Injection ◽  
Work Distribution ◽  
Compressor Performance ◽  
Thermodynamic Effects ◽  
The Ideal

SummaryA study has been made of the effects of inlet coolant injection upon axial compressor performance, using the results of tests on turboshaft engines. It is shown that evaporation of the coolant changes the stage work distribution as well as the ideal compression work and that these effects may be estimated by elementary thermodynamic methods. Simplified prediction procedures are suggested and compared with experimental results.

A Contribution to the Analysis of Axial Compressor Performance

1964 ◽  
Vol 15 (1) ◽  
pp. 39-52 ◽  
Author(s):  
H. Pearson
Keyword(s):  
Axial Compressor ◽  
Effective Area ◽  
Area Ratio ◽  
Unique Characteristic ◽  
Axial Compressors ◽  
Compressor Performance ◽  
Stage Characteristic

SummaryThe concept of an idealised “unique” stage characteristic is employed to analyse and understand the performance of axial compressors. It is shown that there exists a “matching” line across the compressor characteristics at any point of which all the stages are operating at the same point of their “unique” stage characteristic, and that this matching line is readily obtainable, almost from inspection. Simple calculations lead to a derivation of both this “unique” characteristic and the effective area ratio of the compressor. The behaviour of the stages at other points than the matching line is readily understandable and presents a simpler picture of compressor performance than is often obtainable from actually measured stage characteristics.

Redesign of a Multistage Axial Compressor for a Heavy Duty Industrial Gas Turbine (GT11NMC)

2005 ◽  
Author(s):  
Sasha M. Savic ◽  
Marco A. Micheli ◽  
Andreas C. Bauer
Keyword(s):  
Power Output ◽  
Gas Turbines ◽  
Axial Compressor ◽  
Rotor Blades ◽  
Engine Efficiency ◽  
Controlled Diffusion ◽  
Surge Margin ◽  
Compressor Design ◽  
Augmentation Techniques ◽  
Industrial Gas Turbine

Different approaches to compressor design exist in industrial practice. This paper describes two design philosophies that can be followed with compressor development (re-staggering and new airfoil design), and reports on field experience gained with an advanced compressor design using CDA (Controlled Diffusion Airfoils) profiles. The first philosophy described is based on incremental changes of compressor design, consisting of keeping the same blade profiles and re-staggering a number of rotor blades and/or stator vanes. The second philosophy described is to utilize advanced CDA profiles in compressor design, optimized for increased mass-flow and backpressure. The second philosophy was followed in the development of a compressor upgrade for ALSTOM’s GT11NM gas turbines, where a significant increase in GT power output (exceeding 10%) and improved overall engine efficiency (+0.4% additive) at unchanged surge margin were achieved. Power output and improved efficiency resulted solely from the advanced blade design, requiring no additional power augmentation techniques. These figures were measured on a natural gas-fired GT operating in an open-cycle power plant.

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