Relevant bibliographies by topics / Gas-turbines. Compressors Compressors Fouling

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Academic literature on the topic 'Gas-turbines. Compressors Compressors Fouling'

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Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Gas-turbines. Compressors Compressors Fouling"

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Tarabrin, A. P., V. A. Schurovsky, A. I. Bodrov, and J. P. Stalder. "An Analysis of Axial Compressor Fouling and a Blade Cleaning Method." Journal of Turbomachinery 120, no. 2 (April 1, 1998): 256–61. http://dx.doi.org/10.1115/1.2841400.

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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.
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Caguiat, Daniel E. "Rolls Royce/Allison 501-K Gas Turbine Antifouling Compressor Coatings Evaluation." Journal of Turbomachinery 125, no. 3 (July 1, 2003): 482–88. http://dx.doi.org/10.1115/1.1573665.

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The Naval Surface Warfare Center, Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 was tasked by NSWCCD Shipboard Energy Office Code 859 to research and evaluate fouling resistant compressor coatings for Rolls Royce Allison 501-K Series gas turbines. The objective of these tests was to investigate the feasibility of reducing the rate of compressor fouling degradation and associated rate of specific fuel consumption (SFC) increase through the application of anti-fouling coatings. Code 9334 conducted a market investigation and selected coatings that best fit the test objective. The coatings selected were Sermalon for compressor stages 1 and 2 and Sermaflow S4000 for the inlet guide vanes and remaining 12 compressor stages. Both coatings are manufactured by Sermatech International, are intended to substantially decrease blade surface roughness, have inert top layers, and contain an anti-corrosive aluminum-ceramic base coat. Sermalon contains a Polytetrafluoroethylene (PTFE) topcoat, a substance similar to Teflon, for added fouling resistance. Tests were conducted at the Philadelphia Land Based Engineering Site (LBES). Testing was first performed on the existing LBES 501-K17 gas turbine, which had an uncoated compressor. The compressor was then replaced by a coated compressor and the test was repeated. The test plan consisted of injecting a known amount of salt solution into the gas turbine inlet while gathering compressor performance degradation and fuel economy data for 0, 500, 1000, and 1250 KW generator load levels. This method facilitated a direct comparison of compressor degradation trends for the coated and uncoated compressors operating with the same turbine section, thereby reducing the number of variables involved. The collected data for turbine inlet, temperature, compressor efficiency, and fuel consumption were plotted as a percentage of the baseline conditions for each compressor. The results of each plot show a decrease in the rates of compressor degradation and SFC increase for the coated compressor compared to the uncoated compressor. Overall test results show that it is feasible to utilize antifouling compressor coatings to reduce the rate of specific fuel consumption increase associated with compressor performance degradation.
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Awang Saifudin, Awang Raisudin, and Nurul Musfirah Mazlan. "Computational Exploration of a Two-Spool High Bypass Turbofan Engine's Component Deterioration Effects on Engine Performance." Applied Mechanics and Materials 629 (October 2014): 104–8. http://dx.doi.org/10.4028/www.scientific.net/amm.629.104.

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Aircraft engines are exposed to degradation due to several factors such as environmental air pollution, fuel content and ageing or degradation of engine’s components, which are experienced within specified time. While the turbofan in operation, its components deteriorate and consequently affect its performance. This study is aimed to computationally investigate the effect of components degradation on engine performance. A high bypass turbofan engine operated at cruise is selected for this evaluation and the simulation was performed using the Gas Turbine Simulation Program (GSP). The affected components considered are turbines and compressors with deterioration rate ranging from 0% to 5%. The effect of selected deterioration rate on engine thrust and thrust specific fuel consumption (TSFC) is studied. Results obtained show an agreement with literature where reduction in engine thrust and TSFC are observed. Turbine’s fouling has been found to be more severe than erosion in terms of power and efficiency losses. However, in terms of the overall performance, the erosion effect is more severe than fouling.
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Lucas, Radika, Andy Jones, Wesley Ford, and Matt Doyle. "The effective use of data analytics in an advanced compressor performance and degradation monitoring system." APPEA Journal 58, no. 2 (2018): 723. http://dx.doi.org/10.1071/aj17086.

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Origin is the upstream operator and joint venture partner in Australia Pacific LNG. Origin’s integrated gas operations require reliable, sustainable delivery of gas to the downstream LNG facility on Curtis Island. This scale of operation requires establishing a ‘single source of truth’ regarding compressor condition and performance while achieving maximum and reliable compression capacities. Therefore, capability of monitoring performance of centrifugal compressors across the fleet is considered an essential component of production surveillance. Xodus leveraged Origin’s OSIsoft PI AF (PI Historian Asset Framework) tool. This system was used to build a compressor performance and degradation monitoring tool to accurately identify early indications of degradation in a multi-stage centrifugal compression train. The tool utilises live data from the PI historian to calculate key performance indicators which define compressor and driver operation. Dimensionless parameter analysis allows Origin to accurately quantify performance degradation regardless of variations in plant inlet conditions at each gas processing facility. Deviation from baseline performance in dimensionless parameters such as polytropic efficiency, work input number and polytropic head coefficient is used to quantify capacity losses, additional power consumption and increase in suction pressure. The tool provided the ability to use performance indicators to confidently determine the mode and extent of compressor degradation and prevent accelerated fouling which can lead to premature bundle changes. Also, this information helps streamline and has led to a major step change for the decision-making process concerning maximum production from rotating equipment. Additionally, this allowed operations to be confident on the condition of the compressor bundle, continue operation with higher capacities during high demand periods and ensure compressor bundle changeout is optimised for availability and economic aspects.
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Martín-Aragón, Javier, and Manuel Valdés. "A method to determine the economic cost of fouling of gas turbine compressors." Applied Thermal Engineering 69, no. 1-2 (August 2014): 261–66. http://dx.doi.org/10.1016/j.applthermaleng.2013.11.051.

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Batayev, Nurlan. "Axial compressor fouling detection for gas turbine driven gas compression unit." Indonesian Journal of Electrical Engineering and Computer Science 15, no. 3 (September 1, 2019): 1257. http://dx.doi.org/10.11591/ijeecs.v15.i3.pp1257-1263.

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<span>One of the main reasons of the performance degradation of gas turbines is the axial compressor fouling due to air pollutants. Considering the fact that the fouling leads to high consumption of fuel, reducing of the axial compressor’s discharge air pressure and increasing of the exhaust temperature, thus designing a compressor degradation detection system will allow prevent such issues. Many gas turbine plants lose power due to dirty axial compressor blades, which can add up to 4% loss of power. In case of power plants, the power loosing could be observed by less megawatts produced by generator. But in case of gas compression stations the effect of power loosing could not be quickly detected, because there is not direct measurement of the discharge power produced by gas turbine. This article represents technique for detection of gas turbine axial compressor degradation in case of gas turbine driven natural gas compression units. Calculation of the centrifugal gas compressor power performed using proven methodology. Approach for evaluation of the gas turbine performance based on machine learning prediction model is shown. Adequacy of the model has been made to three weeks’ operation data of the 10 Megawatt class industrial gas turbine.</span>
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Song, T. W., J. L. Sohn, T. S. Kim, J. H. Kim, and S. T. Ro. "An analytical approach to predicting particle deposit by fouling in the axial compressor of the industrial gas turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 3 (May 1, 2005): 203–12. http://dx.doi.org/10.1243/095765005x7547.

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The gas turbine performance deteriorates with increased operating hours. Fouling in the axial compressor is an important factor for the performance degradation of gas turbines. Airborne particles entering the compressor with the air adhere to the blade surface and result in the change of the blade shape, which directly influences the compressor performance. It is difficult to exactly understand the mechanism of compressor fouling because of its slow growth and different length scales of compressor blades. In this study, an analytical method to predict the particle motion in the axial compressor and the characteristics of particle deposition onto blade is proposed as an approach to investigating physical phenomena of fouling in the axial compressor of industrial gas turbines. Calculated results using the proposed method and comparison with measured data demonstrate the feasibility of the model. It was also found that design parameters of the axial compressor such as chord length, solidity, and number of stages are closely related to the fouling phenomena. Likewise, the particle size and patterns of particle distributions are also important factors related to fouling phenomena in the axial compressor.
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Kurz, Rainer. "Natural Gas." Mechanical Engineering 133, no. 04 (April 1, 2011): 52. http://dx.doi.org/10.1115/1.2011-apr-7.

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This article discusses the importance of gas turbines, centrifugal compressors and pumps, and other turbomachines in processes that bring natural gas to the end users. To be useful, the natural gas coming from a large number of small wells has to be gathered. This process requires compression of the gas in several stages, before it is processed in a gas plant, where contaminants and heavier hydrocarbons are stripped from the gas. From the gas plant, the gas is recompressed and fed into a pipeline. In all these compression processes, centrifugal gas compressors driven by industrial gas turbines or electric motors play an important role. Turbomachines are used in a variety of applications for the production of oil and associated gas. For example, gas turbine generator sets often provide electrical power for offshore platforms or remote oil and gas fields. Offshore platforms have a large electrical demand, often requiring multiple large gas turbine generator sets. Similarly, centrifugal gas compressors, driven by gas turbines or by electric motors are the benchmark products to pump gas through pipelines, anywhere in the world.
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Mund, Friederike C., and Pericles Pilidis. "Gas Turbine Compressor Washing: Historical Developments, Trends and Main Design Parameters for Online Systems." Journal of Engineering for Gas Turbines and Power 128, no. 2 (July 27, 2005): 344–53. http://dx.doi.org/10.1115/1.2132378.

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By being exposed to atmospheric conditions gas turbines are inevitably subjected to sources of fouling. The resulting degradation can be partially recovered by cleaning the compressor. Based on open literature and patents, the different approaches leading to the most advanced method of compressor online washing have been compiled. The origins of online washing and the development trends over the decades are outlined, and the current systems are categorized. The introduction of system categories has been justified by a field survey. Additionally, the main design parameters of online washing systems are summarized.
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Lakshminarasimha, A. N., M. P. Boyce, and C. B. Meher-Homji. "Modeling and Analysis of Gas Turbine Performance Deterioration." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 46–52. http://dx.doi.org/10.1115/1.2906808.

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The effects of performance deterioration in both land and aircraft gas turbines are presented in this paper. Models for two of the most common causes of deterioration, viz., fouling and erosion, are presented. A stage-stacking procedure, which uses new installed engine field data for compressor map development, is described. The results of the effect of fouling in a powerplant gas turbine and that of erosion in a aircraft gas turbine are presented. Also described are methods of fault threshold quantification and fault matrix simulation. Results of the analyses were found to be consistent with field observations.
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Dissertations / Theses on the topic "Gas-turbines. Compressors Compressors Fouling"

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Baker, Jonathan D. "Analysis of the sensitivity of multi-stage axial compressors to fouling at various stages." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Sep%5FBaker.pdf.

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Nucara, Pascal. "Design of gas turbine axial compressors for fuel flexibility." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48905/.

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Current gas turbine technology for power generation is generally optimised for natural gas. On the basis of current instabilities in natural gas price and supply, the use of alternative fuels, such as syngas, has recently gained high interest. Due to the different thermodynamic properties of syngas compared to natural gas the behaviour of existing gas turbine components may significantly change. From practical and economic points of view, it is generally considered that in order to meet the new fuel properties, the main effort should be put on the adaptation of conventional gas turbines in integrated gasification combined cycle (IGCC) plants rather than producing a new generation of gas turbine designs from scratch. In addition to the requirement of new combustion technologies, main critical issues are represented by the reduction of compressor surge margin and turbine blade overheating. Solutions might include thermodynamic cycle as well as turbine geometry modifications. The latter would be preferred in terms of power plant performance. The main aim of this thesis is to explore suitable solutions to be applied to gas turbine compressors in order to accommodate syngas combustion. Among others, the use of variable stator vanes (VSVs) and blade radial stacking line modifications are considered. These are investigated on reference geometries available in the public domain. A baseline compressor geometry representative of a conventional heavy-duty gas turbine fueled with natural gas is generated and modified according to the understating gained during this study. The re-designed machine is a result of the application of stator vanes re-staggering in the front stages and blade sweep in the rear stages in order to cope with compressor air supply control and critical flow separation regions respectively. The obtained results show that efficient and stable operation during power modulation can be achieved, while reducing the need of other modifications to the combined cycle plant. It was therefore concluded that the proposed option can be considered a viable option to satisfy some important technical and economic constraints imposed by the integration of an existing gas turbine within an IGCC plant.
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Ekong, Godwin I. "Tip clearance control concepts in gas turbine H.P. compressors." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48906/.

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Li, X. "Predictive condition monitoring of rotating machinery with application to gas turbines and compressors." Thesis, London South Bank University, 2017. http://researchopen.lsbu.ac.uk/2727/.

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Rotating machines, such as gas turbines and compressors, are widely used due to their high performance and robustness. These machines typically operate under adverse conditions, such as high loads and high temperatures and are thus subject to performance degradation and mechanical failure. In an effort to solve this problem, condition-based maintenance (CBM) was introduced to minimize safety risks and operational downtime hazards as well as to reduce maintenance and operation costs. One of the most critical aspects of CBM is the provision of incipient fault diagnosis and prognosis regarding the system's performance under faulty conditions. Traditional monitoring and alarm systems are currently widely used in the oil and gas industry to evaluate whether values of individual sensors exceed a threshold. Predictive maintenance requires techniques that are far more elaborate. Over the past decades, multivariate data-driven methods have attracted interest for condition monitoring in modern industrial plants due to the rapid growth and advancement in data acquisition technology. However, applications of these methods in industry are not widely reported. In view of the lack of research using real industrial data, this investigation focuses on the development of multivariate diagnostic and prognostic models that are applicable to operational industrial gas compressors and turbines, the early detection of faults, the identification of fault-associated variables and the estimation of performance deterioration after the appearance of faults. Although an increasing number of case studies of multivariate statistical monitoring has being reported in the past few years, the data employed in those studies are usually simulated data that are collected from simulation programs. The condition monitoring data of real industrial rotating equipment are generally not accessible by the public due to commercial confidentiality. Using condition monitoring data collected from operational industrial gas compressors and turbines, this work aims to provide case studies to demonstrate the capabilities of novel multivariate statistical monitoring approaches to detect faults and estimate the impacts of those faults on plant operations. Traditional statistical monitoring approaches are based on the assumption that the underlying processes are linear and static. However, this assumption might not hold true for real industrial processes because sensory signals affected by noise and disturbances often show strong nonlinearities, and the operating conditions often vary with time. As a result, static and linear methods may not be suitable for real-world applications because they provide incomplete representations of such systems. To address the limitations of standard multivariate statistical monitoring approaches for systems with both nonlinear and dynamic properties, canonical variate analysis (CVA) together with kernel density estimation (KDE) are employed in this work to detect diverse types of faults in rotating machines. The control limits associated with the proposed model were calculated based on the Hotelling's T^2 and Q metrics. The results obtained showed that the proposed method is effective for providing incipient fault diagnoses in the early stages of performance deterioration. For the purpose of fault diagnosis, 2-D contribution charts are utilized to identify the most fault related variables. The developed contribution plots can provide greater insights into the root causes of the faults and how the faults propagate to the remaining parts of the system. Predictive condition monitoring and preventive maintenance are seen as the means both to achieve high reliability and availability of complex rotating machines and to reduce unplanned production shutdowns. To achieve these goals, it is necessary not only to implement effective fault detection and diagnosis but also to react to the detected faults by continuously assessing and predicting the health status of the system. To test the capabilities of CVA for performance estimation, this method is first used to build a time-invariant state-space model of the dynamic system using purely historical condition monitoring data. The proposed method is applied to rotating equipment operating under both healthy conditions and slowly evolving faulty conditions to demonstrate its applicability and effectiveness. The use of a time-invariant model for system identification limits its application to linear and stationary processes. The use of a time-varying model can overcome this limitation by allowing model adaptation to rapid changes in system operating conditions of time-varying processes. To address the challenge of implementing prognostics in real-world applications with both dynamic and nonlinear properties, the time-invariant CVA model is extended using recursive least squares (RLS), resulting in the improved adaptive CVA prognostic model. The extended CVA method proposed in this work is evaluated using data captured from rotating machines operating under rapidly varying healthy conditions as well as faulty conditions. Furthermore, to account for the impact of environmental factors on a system's performance, in this work, CVA combined with long short-term memory (LSTM) is used to estimate the behaviour of a centrifugal compressor after the occurrence of a fault using data captured during the early stages of deterioration. The results of this study indicate that CVA can effectively capture the system dynamics for large-scale complex rotating machines, thereby enabling the early detection of faults, the diagnosis of the root cause of the detected faults and the prediction of system behaviour after the appearance of faults. A systematic fault detection, isolation and estimation scheme can be developed based on the proposed techniques, based on which the whole plant-wide process can be monitored at both the plant-wide and the unit levels, and the monitoring information can be used to improve maintenance decisions and to reduce unscheduled downtime.
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Vigueras, Zuniga Marco Osvaldo. "Analysis of gas turbine compressor fouling and washing on line." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/2448.

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This work presents a model of the fouling mechanism and the evaluation of compressor washing on line. The results of this research were obtained from experimental and computational models. The experimental model analyzed the localization of the particle deposition on the blade surface and the change of the surface roughness condition. The design of the test rig was based on the cascade blade arrangement and blade aerodynamics. The results of the experiment demonstrated that fouling occurred on both surfaces of the blade. This mechanism mainly affected the leading edge region of the blade. The increment of the surface roughness on this region was 1.0 μm. This result was used to create the CFD model (FLUENT). According to the results of the CFD, fouling reduced the thickness of the boundary layer region and increased the drag force of the blade. The model of fouling was created based on the experiment and CFD results and was used to calculate the engine performance in the simulation code (TURBOMATCH). The engine performance results demonstrated that in five days fouling can affect the overall efficiency by 3.5%. The evaluation of the compressor washing on line was based on the experimental tests and simulation of the engine performance. This system demonstrated that it could recover 99% of the original blade surface. In addition, this system was evaluated in a study case of a Power Plant, where it proved itself to be a techno-economic way to recover the power of the engine due to fouling. The model of the fouling mechanism presented in this work was validated by experimental tests, CFD models and information from real engines. However, for further applications of the model, it would be necessary to consider the specific conditions of fouling in each new environment.
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Abass, Kabir Oliade. "Techno-Economic Analysis of Gas Turbine Compressor Washing to Combat Fouling." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/9230.

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Among the major deterioration problems a gas turbine encountered while in operation is compressor blade fouling. This is the accumulation and adhesion of dirt and sediment on the compressor blade which contributes between 70 to 85% of gas turbine performance loss. Fouling reduces turbine air mass flow capacity, compressor pressure ratio and overall gas turbine efficiency. In most cases, its effect does not manifest immediately in gas turbine power output and efficiency since they are not measured directly. However, it is apparent on the gradual increase in Turbine Entry temperature (TET) and Exhaust Gas Temperature (EGT). More fuel is burnt in the combustion chamber to maintain turbine power output which leads to high combustion flame temperature and thus reduces creep life of hot components. This research seeks to analyse the technical and economic consequences of compressor fouling in overall gas turbine performance. The work begins with simulation of TS3000 engine and examination of its design and off design performance. Subsequently, medium size gas turbine engine was modelled, simulated and its performance at different condition was examined to validate the outcome of field data analysis. Three months field operating data of Hitachi H-25 gas turbine generator used for power generation at bonny oil and gas terminal in Nigeria was collected and corrected to international standard ambient condition, using thermodynamic calculations. These data were analysed to determine the effect of fouling on the engine fuel consumption, power output in order to determine the plant profitability. The above analysis gives an estimation of fuel cost saving benefit of $41,000 over the period of one year plant operation due to regular two weekly compressor online water wash which is a good indication of the engine efficiency.
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Baiense, Jr Joao C. "Vortex Generator Jet Flow Control in Highly Loaded Compressors." Digital WPI, 2014. https://digitalcommons.wpi.edu/etd-theses/916.

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"A flow control method for minimizing losses in a highly loaded compressor blade was analyzed. Passive and active flow control experiments with vortex generator jets were conducted on a seven blade linear compressor cascade to demonstrate the potential application of passive flow control on a highly loaded blade. Passive flow control vortex generator jets use the pressure distribution generated by air flow over the blade profile to drive jets from the pressure side to the suction side. Active flow control was analyzed by pressuring the blade plenum with an auxiliary compressor unit. Active flow control decreased profile losses by approximately 37 % while passive flow control had negligible impact on the profile loss of a highly loaded blade. Passive flow control was able to achieve a jet velocity ratio, jet velocity to upstream velocity, of 0.525. The success of active flow control with a velocity ratio of 0.9 suggests there is potential for passive flow control to be effective. The research presented in this thesis is motivated by the potential savings in the applications of passive flow control in gas turbine axial compressors by increasing the aerodynamic load of each stage. Increased stage loading that is properly controlled can reduce the number of stages required to achieve the desired pressure compression ratio."
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Davis, Milton W. "A stage-by-stage post-stall compression system modeling technique: methodology, validation, and application." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/50002.

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A one-dimensional, stage-by-stage axial compression system mathematical model has been constructed which can describe system behavior during post-stall events such as surge and rotating stall. The model uses a numerical technique to solve the nonlinear conservation equations of mass, momentum, and energy. Inputs for blade forces and shaft work are provided by a set of quasi-steady stage characteristics modified by a first order lagging equation to simulate dynamic stage characteristics. The model was validated with experimental results for a three-stage, low-speed compressor and a nine-stage, high-pressure compressor. Using these models, a parametric study was conducted to determine the effect of inlet resistance, combustor performance, heat transfer, and stage characteristic changes due to hardware modification on post—stall system behavior.
Ph. D.
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Davis, Milton W. Jr. "A stage-by-stage post-stall compression system modeling technique: methodology, validation, and application." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/50002.

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A one-dimensional, stage-by-stage axial compression system mathematical model has been constructed which can describe system behavior during post-stall events such as surge and rotating stall. The model uses a numerical technique to solve the nonlinear conservation equations of mass, momentum, and energy. Inputs for blade forces and shaft work are provided by a set of quasi-steady stage characteristics modified by a first order lagging equation to simulate dynamic stage characteristics. The model was validated with experimental results for a three-stage, low-speed compressor and a nine-stage, high-pressure compressor. Using these models, a parametric study was conducted to determine the effect of inlet resistance, combustor performance, heat transfer, and stage characteristic changes due to hardware modification on post—stall system behavior.
Ph. D.
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De, Villiers Lodewyk Christoffel Barend. "Design of a centrifugal compressor for application in micro gas turbines." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/96052.

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Thesis (MEng)--Stellenbosch University, 2014.
ENGLISH ABSTRACT: This thesis details the methodology for developing a centrifugal compressor for application in a Micro Gas Turbine (MGT). This research forms part of a larger project, namely project Ballast, initiated by the South African Air Force (SAAF) in conjunction with Armscor. The methodology encompasses the development of a mean-line code that makes use of 1-dimensional theory in order to create an initial centrifugal compressor geometry which includes a rotor as well as radial vaned diffuser. This is followed by a Computational Fluid Dynamics (CFD) simulation process during which the compressor is optimised in order to maximise its performance. Before manufacturing a Finite Element Analysis (FEA) is done in order to ensure that the rotor does not fail during testing. The testing of the compressor is done to compare the numerical results with the experimental results and in so doing confirms the design process. A previous student had designed a rotor by making use of a mean-line code as well as a CFD optimisation process. The rotor had a measured total-static pressure ratio of roughly 2.8 at 121 kRPM and a total-total isentropic efficiency of 79.1 % at said rotational speed. The inclusion of a vaned diffuser resulted in a higher total-static pressure ratio and accordingly the compressor designed in this report has a CFD determined total-static pressure ratio of 3.0. The efficiency would however drop and as such a total-total isentropic efficiency of 76.5 % was determined theoretically. The theoretical results correlated well with the experimental results and as such it was concluded that the design methodology developed was sound.
AFRIKAANSE OPSOMMING: Hierdie tesis bespreek die metodologie vir die ontwikkeling van ‘n sentrifugale kompressor vir toepassing in ‘n Mikro-Gasturbine (MGT). Die tesis vorm deel van ‘n groter projek, genaamd die Ballast projek, wat deur die Suid-Afrikaanse Lugmag (SALM) daargestel is in samewerking met Krygkor. Die metodologie behels die ontwikkeling van ‘n middel-lyn kode wat gebruik maak van 1-dimensionele teorie om die aanvanklike geometrie van die kompressor te skep. Die geometrie bevat beide die rotor asook die gelemde radiale diffusor. Hierdie proses word gevolg deur ‘n Berekeningsvloeidinamika (BVD) simulasie waartydens die kompressor geoptimeer word om sodoende die verrigting ten volle te verbeter. Voordat vervaardiging plaasvind word ‘n Eindige Element Analise (EEA) toegepas om te verseker dat die rotor nie sal faal tydens toetse nie. Die toetse word gedoen sodat die eksperimentele resultate met die numeriese resultate vergelyk kan word. Sodoende word die proses waardeur die kompressor ontwikkel word bevestig. ‘n Vorige student het ‘n rotor ontwerp deur gebruik te maak van ‘n middel-lyn kode asook ‘n BVD optimerings proses. Die rotor het ‘n gemete totaal-statiese drukverhouding van ongeveer 2.8 teen 121 kRPM gelewer en ‘n totaal-totale isentropiese benutingsgraad van 79.1 % teen dieselfde omwentelingspoed. Met die insluiting van ‘n gelemde radiale diffuser word ‘n hoër totaal-statiese druk verhouding verwag en as sulks lewer die nuut-ontwerpte kompressor soos in die tesis bespreek ‘n teoretiese totaal-statiese drukverhouding van 3.0. Die benutingsgraad sal egter daal en daarvolgens het die nuwe kompressor ‘n totaal-totale isentropiese benutingsgraad van 76.5 % gelewer. Die eksperimentele resultate het goed ooreengestem met die teoretiese resultate en as sulks was dit besluit dat die ontwerps-metodologie goed is.
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Books on the topic "Gas-turbines. Compressors Compressors Fouling"

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Panin, V. V. Gazodinamicheskai︠a︡ ustoĭchivostʹ kompressorov aviat︠s︡ionnykh GTD. Kiev: Ministerstvo obrazovanii︠a︡ Ukrainy. Kievskiĭ mezhdunar. universitet grazhdanskoĭ aviat︠s︡ii, 1998.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Advanced technology for aero gas turbine components. Neuilly sur Seine, France: AGARD, 1987.

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Terentʹev, A. N. Remont gazoperekachivai͡u︡shchikh agregatov s gazoturbinnym privodom. Moskva: "Nedra", 1985.

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Symposium of the AGARD Propulsion and Energetics Panel (65th 1985 Bergen, Norway). Heat transfer and cooling in gas turbines: Papers presented at the Propulsion and Energetics Panel 65th Symposium, held in Bergen, Norway, 6-10 May 1985. Neuilly sur Seine, France: North Atlantic Treaty Organization, Advisory Group for Aerospace Research and Development, 1985.

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A, Clark David, Wood Jerry R, United States. Army Aviation Research and Technology Activity. Propulsion Directorate., and Lewis Research Center, eds. Effect of area ratio on the performance of a 5.5:1 pressure ratio centrifugal impeller. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

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United States. National Aeronautics and Space Administration., ed. Design geometry and design/off-design performance computer codes for compressors and turbines. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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United States. National Aeronautics and Space Administration., ed. Wave rotor demonstrator engine assessment. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Wave rotor demonstrator engine assessment. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Kollmann, Karl, Calum E. Douglas, and S. Can Gülen. Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students. ASME, 2021. http://dx.doi.org/10.1115/1.884676.

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This book is a unique blend of history, technology review, theoretical fundamentals, and design guide. The subject matter is primarily piston aeroengine superchargers – developed in Germany during the Second World War (WWII) – which are centrifugal compressors driven either by the main engine crankshaft or by an exhaust gas turbine. The core of the book is an unpublished manuscript by Karl Kollmann, who was a prominent engineer at Daimler-Benz before and during the war. Dr. Kollmann’s manuscript was discovered by Calum Douglas during his extensive research for his earlier book on piston aeroengine development in WWII. It contains a wealth of information on aerothermodynamic and mechanical design of centrifugal compressors in the form of formulae, charts, pictures, and rules of thumb, which, even 75 years later, constitute a valuable resource for engineering professionals and students. In addition to the translation of the original manuscript from German, the authors have completely overhauled the chapters on the aerothermodynamics of centrifugal compressors so that the idiosyncratic coverage (characteristic of German scientific literature at that time) is familiar to a modern reader. Furthermore, the authors added chapters on exhaust gas turbines (for turbo-superchargers), piston aeroengines utilizing them, and turbojet gas turbines. Drawing upon previously unpublished material from the archived German documents, those chapters provide a concise but technically precise and informative look into those technologies, where great strides were made in Germany during the war. In summary, the coverage is intended to be useful not only to history buffs with a technical bent but also to the practicing engineers and engineering students to help with their day-to-day activities in this particular field of turbomachinery.
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P, Shreeve Raymond, and Lewis Research Center, eds. Comparison of calculated and experimental cascade performance for controlled-diffusion compressor stator blading. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

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Book chapters on the topic "Gas-turbines. Compressors Compressors Fouling"

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Vepa, Ranjan. "Dynamic Modeling of Gas Turbines and Compressors." In Lecture Notes in Energy, 211–69. London: Springer London, 2013. http://dx.doi.org/10.1007/978-1-4471-5400-6_5.

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Razak, A. M. Y. "Compressors." In Industrial Gas Turbines, 98–119. Elsevier, 2007. http://dx.doi.org/10.1533/9781845693404.1.98.

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"Compressors." In Industrial Gas Turbines. CRC Press, 2007. http://dx.doi.org/10.1201/9781439823996.ch4.

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"Gas Turbine Compressor Fouling." In Case Studies in Mechanical Engineering, 46–63. Chichester, UK: John Wiley & Sons, Ltd, 2016. http://dx.doi.org/10.1002/9781119119753.ch3.

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Ernesto. "Advances in Aerodynamic Design of Gas Turbines Compressors." In Gas Turbines. Sciyo, 2010. http://dx.doi.org/10.5772/10205.

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"The design and performance prediction of axial-flow turbines compressors." In The Design of High-Efficiency Turbomachinery and Gas Turbines. The MIT Press, 2014. http://dx.doi.org/10.7551/mitpress/9940.003.0015.

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Kollmann, Karl, Calum E. Douglas, and S. Can Gülen. "Exhaust Gas Turbine." In Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students, 255–82. ASME, 2021. http://dx.doi.org/10.1115/1.884676_ch10.

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As discussed in Chapter 2, the supercharger (basically, an air compressor) can also be driven by an exhaust gas turbine. In this case, the overall system is referred to as a turbocharger or turbosupercharger (Abgasturbolader in German). The focus in Kollmann’s manuscript is exclusively on radial compressors used as superchargers driven by a gear drive connected to the main engine shaft. This is not so surprising considering that, although significant R&D effort was spent on the turbine design (especially, turbine blade cooling), turbocharged German aircraft engines did not enter service until the end of the war. Even then, the service experience was limited to Junkers Ju 388 (mostly for high altitude reconnaissance) powered by two 1,500-HP BMW 801 J turbocharged engines. Many other designs (e.g., the DB 623) were eventually abandoned. The dilemma facing the German engineers at the time (1940s) was this: whether to develop an aircraft engine from the get-go with a turbocharger or to develop a turbocharger to be fitted into an existing engine (e.g., the DB 603). Since the need for the turbochargers arose during the war by the need for higher flight altitudes (10 to 14 km), e.g., to attack the Allied bomber formations and their fighter escort, the urgency of the situation made the choice for them1. Not surprisingly, they went with the latter option.
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Kollmann, Karl, Calum E. Douglas, and S. Can Gülen. "Alternative Systems." In Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students, 229–40. ASME, 2021. http://dx.doi.org/10.1115/1.884676_ch8.

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The idea of precompression of the cylinder charge air is as old as the internal combustion itself. It is generally accepted that the first supercharger design in the modern sense was actually a turbocharger, patented in 1905 by the Swiss engineer Alfred Büchi (1879-1959). It comprised an axial compressor, an aftercooler and an exhaust gas turbine applied to a radial piston-cylinder engine as shown in the German patent drawings in Figure 8-1. Not surprisingly, it took him more than two decades to make the system work due to low component efficiencies, i.e., the problem that bedeviled all early gas turbine inventors due to the insufficient knowledge of aerodynamics.
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Conference papers on the topic "Gas-turbines. Compressors Compressors Fouling"

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Kurz, Rainer, and Klaus Brun. "Fouling Mechanisms in Axial Compressors." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45012.

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Fouling of compressor blades is an important mechanism leading to performance deterioration in gas turbines over time. Fouling is caused by the adherence of particles to airfoils and annulus surfaces. Particles that cause fouling are typically smaller than 2 to 10 microns. Smoke, oil mists, carbon, and sea salts are common examples. Fouling can be controlled by appropriate air filtration systems, and can often be reversed to some degree by detergent washing of components. The adherence of particles is impacted by oil or water mists. The result is a build-up of material that causes increased surface roughness and to some degree changes the shape of the airfoil (if the material build up forms thicker layers of deposits). Fouling mechanisms are evaluated based on observed data, and a discussion on fouling susceptibility is provided. A particular emphasis will be on the capabilities of modern air filtration systems.
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Seddigh, F., and H. I. H. Saravanamuttoo. "A Proposed Method for Assessing the Susceptibility of Axial Compressors to Fouling." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-348.

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Although the overall effect of compressor fouling on engine performance has been recognized for many years, remarkably little has been published on the quantifiable effects. Mathematical modelling of compressors using stage stacking methods has recently been used for a systematic study of compressor fouling and earlier investigations led to an interest in the effects of engine size and compressor stage loading. This paper presents a proposed index showing the susceptibility of compressors to fouling, which could be useful in helping operators to determine cleanup intervals. Three engines of widely differing performance were used in developing this index and additional operator experience would be useful in confirming its validity.
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Tarabrin, A. P., V. A. Schurovsky, A. I. Bodrov, and J. P. Stalder. "An Analysis of Axial Compressors Fouling and a Cleaning Method of Their Blading." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-363.

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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.
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Meher-Homji, Cyrus B., Mustapha Chaker, and Andrew F. Bromley. "The Fouling of Axial Flow Compressors: Causes, Effects, Susceptibility, and Sensitivity." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59239.

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Increased fuel costs have created a strong incentive for gas turbine operators to understand, minimize and control performance deterioration. The most prevalent deterioration problem faced by gas turbine operators is compressor fouling. Fouling causes a drop in airflow, pressure ratio and compressor efficiency, resulting in a “re-matching” of the gas turbine and compressor and a drop in power output and thermal efficiency. This paper addresses the causes and effects of fouling and provides a comprehensive treatment of the impact of salient gas turbine design parameters on the susceptibility and sensitivity to compressor fouling. Simulation analysis of ninety two (92) gas turbines of ranging from a few kW to large engines rated at greater than 300 MW has been conducted. It is hoped that this paper will provide practical information to gas turbine operators.
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Yang, Huadong, and Xia Zhang. "Study on Washing Strategy Model of Gas Turbines." In ASME 2015 Power Conference collocated with the ASME 2015 9th International Conference on Energy Sustainability, the ASME 2015 13th International Conference on Fuel Cell Science, Engineering and Technology, and the ASME 2015 Nuclear Forum. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/power2015-49281.

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Fouling in the compressor and turbine, from particles (such as dust, pollen, seed, insect and unburned hydrocarbon) deposited on the blade results in the change of blade profile, thus flow area is reduced. Many researches have demonstrated that fouling can result in the reduction of power and efficiency, and can result in the increase running costs. At present, the most effective control method for gas turbine fouling is off-line washing, but off-line washing may seriously affect the unit’s benefit. So, it is very important to determine the optimal washing cycle. In previous studies, many researchers determine the washing time based on the reduction level of thermodynamic parameters, such as the change of compressor pressure ratio. But, research demonstrated that other failure modes (such as erosion, corrosion and tip clearance increase) can result in the similar change. So, it is not reasonable based on the change of single thermodynamic parameter. However, the fouling in the compressor and turbine cannot directly be observed. In this paper, washing strategy model is proposed. At present, off-line washing criteria about gas turbines are mostly established according to compressors of clean gas turbines and the washing cost is neglected. This model pay attention to economical off-line washing interval based on the principle of minimum mean generalized crank washing cost. For the performance deterioration rate of gas turbine due to fouling, it can be obtained by combining reverse method with optical measuring technology. The washing cost includes running additional cost and shutdown cost. For running additional cost, it includes two aspects. The first running additional cost is the cost of power reduction due to the decrease of mass flow rate. The second running additional cost is the cost of the heat rate increase due to the decrease of gas turbine efficiency. For downtime cost, it is the cost of power loss due to the unit downtime. The calculation result indicates the optimal off-line interval is approximately 80 hours. Compared with traditional washing criteria, the model improved the availability of equipment. Compared with the actual interval, the model improved operation security. Finally, the influence factors such as washing number, shutdown time, and fuel price and degradation rate are analyzed. The result shows the model is greatly influenced by these factors.
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Mæland, Dagfinn, and Lars E. Bakken. "Fouling Effects on Wet Gas Compressor Performance: An Experimental Investigation." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59543.

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Abstract Achieving profitability in mature areas such as the Norwegian continental shelf forces the oil and gas industry to apply innovative solutions to increase oil recovery and to reduce both operational and investment costs. Wet gas compressors are promising machines for increasing oil recovery from existing fields and to allow for production from small satellite fields in the proximity of existing infrastructure. A prerequisite for successful implementation of subsea wet gas compressors high reliability. Knowledge of possible failure modes is important. The effect of performance degradation due to fouling has been observed during wet gas compressor testing at K-Lab and has initiated further work to better understand and quantify the effects of fouling in wet conditions compared to dry conditions. A test campaign was conducted at the Norwegian University of Science and Technology (NTNU) to investigate the effect of fouled centrifugal compressor performance in both wet and dry conditions. The results documenting these effects are presented together with a proposed model for correcting the effects of fouling between dry and wet conditions.
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Tarabrin, A. P., V. A. Schurovsky, A. I. Bodrov, and J. P. Stalder. "Influence of Axial Compressor Fouling on Gas Turbine Unit Perfomance Based on Different Schemes and With Different Initial Parameters." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-416.

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This paper presents an attempt of a quantitative evaluation of deterioration, due to fouling, in the performance of gas turbine units of different schemes (one-shaft, two-shaft and three-shaft) but with axial compressors of the same type and dimensions. This paper also examines the influence of the gas turbine unit initial parameters (inlet turbine temperature and pressure ratio) on the gas turbine unit sensitivity to axial compressor fouling. The evaluation of the gas turbine unit sensitivity to fouling is performed based on the small deviations method. The index of sensitivity to fouling (ISF) proposed in (Tarabrin et al, 1996) is used. It is proposed that not only the ISF characterizing the axial compressor sensitivity to fouling but also the scheme and the initial gas turbine unit parameters influencing the gas turbine unit sensitivity to axial compressor fouling, should be taken into consideration.
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Mezheritsky, A. D., and A. V. Sudarev. "The Mechanism of Fouling and the Cleaning Technique in Application to Flow Parts of the Power Generation Plant Compressors." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-103.

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The baseline principles and deposit formation mechanism in the axial and centrifugal compressors of the power plants of various applications are discussed in the paper. The results of experimental investigation of fouling effect on the compressor and plant performances as well as the dismantling technique of deposit cleaning are shown.
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Simpson, Karl, Joel Sanford, and Lavon Finnefrock. "Redesign of LDPE Secondary Compressor Valves to Better Tolerate Polyethylene Wax Fouling." In ASME 2016 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/pvp2016-63021.

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This paper discusses the redesign of valves in high-pressure reciprocating compressors used in the manufacture of Low Density Polyethylene (LDPE) resin. The compressors have Multi-poppet (MPV) style valves which are affected by LDPE wax fouling. This fouling causes the poppets to stick open leading to gas recirculation (valve leakage) and associated process fluid heating. This heating can cause the compressors to shut down on high discharge temperatures requiring operations personnel to push process gas through the valves to try to clear the waxes, or to have maintenance personnel replace the valves. Poppets sticking due to wax fouling can also result in compressor gas discharge temperatures increasing high enough to cause Ethylene decomposition (Decomp) which can cause the production line to vent to atmosphere. This paper describes analysis and testing to change the valve design from MPV, to Single-poppet (SPV) style valves to reduce the effects of wax fouling.
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Sun, HaiOu, Lisong Wang, Lei Wan, and Feng Qu. "Study on the Performance Variation of Compressor Under Salt Fog Scale." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75981.

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Compressors are crucial to the efficient operation of a gas turbine; however, fouling, caused by adherence of particles to surfaces, can have a negative effect on compressor performance. In this study, a NASA Stage 35 single-stage axial-flow compressor was employed as the model for numerical simulation using the ANSYS CFX software of the effects caused by mild and severe fouling under salt fog scale. To measure these effects, two distinct models were used. For mild fouling, the simulated stator blade surface roughness was altered nonuniformly; for severe fouling, the simulated stator blade thick-ness was altered. Results indicated that surface roughness caused by mild fouling only has a small effect on compressor performance and no effect on the stable working range. However, changes in the blade thickness as a result of severe fouling have a large effect on compressor performance and a clear effect on the stability of the compressor’s working range. The fouling causes an increase in the boundary layer at the trailing edge of the suction side of the blade thereby increasing the loss of flow; fouling effect after emergence angle, wide design value, and increasing blade of circumferential stress.
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