Journal articles: '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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Yang, Hua Dong, and Hong Xu. "Fouling Influence Factor Analysis of Axial Flow Compressor." Advanced Materials Research 516-517 (May 2012): 619–22. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.619.

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Fouling is an important performance degradation factor of axial flow compressor. In order to reveal fouling mechanism, flow simulation of four cases of NASA rotor37 has been performed, such as clean compressor, compressor with roughness of 50μm, 100μm and 150μm. Thermodynamics performance parameters of compressor at different rotational speed with different roughness are discussed. And then fouling sources and its influence factor are analyzed. Research finds that gas contaminants can deposit in blade surface existed with internal oil and water. Simultaneously, humidity, temperature, flow velocity and contact area are the main factors for the formation of compressor fouling. Finally, research finds that fouling can easily formed in suction surface and fouling level of leading edge is more critical than other locations.

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Cruz-Manzo, Samuel, Vili Panov, and Yu Zhang. "Gas Path Fault and Degradation Modelling in Twin-Shaft Gas Turbines." Machines 6, no. 4 (October 1, 2018): 43. http://dx.doi.org/10.3390/machines6040043.

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In this study, an assessment of degradation and failure modes in the gas-path components of twin-shaft industrial gas turbines (IGTs) has been carried out through a model-based analysis. Measurements from twin-shaft IGTs operated in the field and denoting reduction in engine performance attributed to compressor fouling conditions, hot-end blade turbine damage, and failure in the variable stator guide vane (VSGV) mechanism of the compressor have been considered for the analysis. The measurements were compared with simulated data from a thermodynamic model constructed in a Simulink environment, which predicts the physical parameters (pressure and temperature) across the different stations of the IGT. The model predicts engine health parameters, e.g., component efficiencies and flow capacities, which are not available in the engine field data. The results show that it is possible to simulate the change in physical parameters across the IGT during degradation and failure in the components by varying component efficiencies and flow capacities during IGT simulation. The results also demonstrate that the model can predict the measured field data attributed to failure in the gas-path components of twin-shaft IGTs. The estimated health parameters during degradation or failure in the gas-path components can assist the development of health-index prognostic methods for operational engine performance prediction.

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Stalder, J. P. "Gas Turbine Compressor Washing State of the Art: Field Experiences1." Journal of Engineering for Gas Turbines and Power 123, no. 2 (November 1, 2000): 363–70. http://dx.doi.org/10.1115/1.1361108.

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Technology development in gas turbine compressor washing over the last 10 years and today’s state of the art technology is presented in this paper. Based on various long term field tests and observations, correlation between rate of power degradation and atmospheric conditions can be established. Questions about compressor on line washing with water alone against the use of detergents, as well as washing frequencies are also addressed in this paper. Performance degradation behavior between gas turbines of different sizes and models can be explained with an index of sensitivity to fouling. The implementation of an optimized regime of on line and off line washing in the preventive turbine maintenance program is important. It will improve the plant profitability by reducing the costs of energy production and contribute to a cleaner environment.

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Zhu, Lei, and Hong Fu Zuo. "Predicting Compressor of Gas Turbine Power Plant On-Line Washing Interval Using Proportional Hazards Model." Advanced Materials Research 452-453 (January 2012): 195–99. http://dx.doi.org/10.4028/www.scientific.net/amr.452-453.195.

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Due to compressor fouling, gas turbine efficiency decreases over time, resulting in decreased power output of the plant. To counteract the effects of compressor fouling, compressor on-line and off-line washing procedures are used. The present research is aimed to propose a method of mathematical modeling of offline washing interval which will be estimated as the RUL of compressor based on Proportional hazards model. Application of the proposed prediction method to the case of Civil Aero-engine proved its effectiveness.

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Brun, Klaus, Rainer Kurz, and Harold R. Simmons. "Aerodynamic Instability and Life-Limiting Effects of Inlet and Interstage Water Injection Into Gas Turbines." Journal of Engineering for Gas Turbines and Power 128, no. 3 (March 1, 2004): 617–25. http://dx.doi.org/10.1115/1.2135819.

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Gas turbine power enhancement technologies, such as inlet fogging, interstage water injection, saturation cooling, inlet chillers, and combustor injection, are being employed by end users without evaluating the potentially negative effects these devices may have on the operational integrity of the gas turbine. Particularly, the effect of these add-on devices, off-design operating conditions, nonstandard fuels, and compressor degradation∕fouling on the gas turbine’s axial compressor surge margin and aerodynamic stability is often overlooked. Nonetheless, compressor aerodynamic instabilities caused by these factors can be directly linked to blade high-cycle fatigue and subsequent catastrophic gas turbine failure; i.e., a careful analysis should always proceed the application of power enhancement devices, especially if the gas turbine is operated at extreme conditions, uses older internal parts that are degraded and weakened, or uses nonstandard fuels. This paper discusses a simplified method to evaluate the principal factors that affect the aerodynamic stability of a single-shaft gas turbine’s axial compressor. As an example, the method is applied to a frame-type gas turbine and results are presented. These results show that inlet cooling alone will not cause gas turbine aerodynamic instabilities, but that it can be a contributing factor if for other reasons the machine’s surge margin is already slim. The approach described herein can be employed to identify high-risk applications and bound the gas turbine operating regions to limit the risk of blade life reducing aerodynamic instability and potential catastrophic failure.

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Casari, Nicola, Michele Pinelli, Pier Ruggero Spina, Alessio Suman, and Alessandro Vulpio. "Experimental Assessment of Fouling Effects in a Multistage Axial Compressor." E3S Web of Conferences 197 (2020): 11007. http://dx.doi.org/10.1051/e3sconf/202019711007.

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The study of the adhesion of micro sized particles to gas turbine internal surfaces, commonly known as gas turbine fouling, has gained increasing attention in the last years due to its dramatic effect on machine performance and reliability. On-field fouling analysis is mostly related to visual inspections during overhaul and/or programmed stops, which are performed, in particular, when gas turbine performance degradation falls under predetermined thresholds. However, these analyses, even if performed in the most complete as possible way, are rarely (or never) related to the conditions under which the gas turbine contamination takes place since the affecting parameters are difficult or even impossible to be adequately monitored. In the present work, a small scale multistage axial compressor is used to experimentally simulate the fouling phenomenon. The test rig allows the accurate control of the most relevant operating parameters which influence the fouling phenomenon. The compressor performance loss due to particle contamination has been quantitatively assessed. Soot particles appear stickier, especially in the presence of high humidity, and represent the most harmful operating conditions for the compressor unit. The deposits on the stator vanes and the rotor blades have been detected and post-processed, highlighting the most affected regions of each compressor stage employing an image analysis package tool.

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Aker, G. F., and H. I. H. Saravanamuttoo. "Predicting Gas Turbine Performance Degradation Due to Compressor Fouling Using Computer Simulation Techniques." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 343–50. http://dx.doi.org/10.1115/1.3240259.

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As part of an ongoing investigation into the effects of compressor fouling on gas turbine performance, the stage stacking technique was used in conjunction with generalized turbine characteristics to simulate the performance of two common pipeline engines, the G. E. LM2500 and the Solar Centaur. A linear fouling model was introduced that simulates the progressive buildup of contaminants in the compressor by modifying the appropriate stage flow and efficiency characteristics in a stepwise fashion. This simulation of the onset and progressive nature of compressor fouling allows quantitative analysis of performance deterioration to be performed on the basis of trends noted in monitored parameters. A preliminary study into how severely a given level of fouling will affect engines of different size indicated that stage loading may be the more critical parameter.

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Mrzljak, Vedran, Igor Poljak, Jasna Prpić-Oršić, and Maro Jelić. "Exergy analysis of marine waste heat recovery CO2 closed-cycle gas turbine system." Pomorstvo 34, no. 2 (December 21, 2020): 309–22. http://dx.doi.org/10.31217/p.34.2.12.

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This paper presents an exergy analysis of marine waste heat recovery CO2 closed-cycle gas turbine system. Based on the operating parameters obtained in system exploitation, it is performed analysis of each system component individually, as well as analysis of the whole observed system. While observing all heat exchangers it is found that combustion gases-CO2 heat exchangers have the lowest exergy destructions and the highest exergy efficiencies (higher than 92%). The lowest exergy efficiency of all heat exchangers is detected in Cooler (51.84%). Observed system is composed of two gas turbines and two compressors. The analysis allows detection of dominant mechanical power producer and the dominant mechanical power consumer. It is also found that the turbines from the observed system have much higher exergy efficiencies in comparison to compressors (exergy efficiency of both turbines is higher than 94%, while exergy efficiency of both compressors did not exceed 87%). The whole observed waste heat recovery system has exergy destruction equal to 6270.73 kW, while the exergy efficiency of the whole system is equal to 64.12% at the selected ambient state. Useful mechanical power produced by the whole system and used for electrical generator drive equals 11204.80 kW. The obtained high exergy efficiency of the whole observed system proves its application on-board ships.

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Ohanian, S., and R. Kurz. "Series of Parallel Arrangement in a Two-Unit Compressor Station." Journal of Engineering for Gas Turbines and Power 124, no. 4 (September 24, 2002): 936–41. http://dx.doi.org/10.1115/1.1478074.

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This paper discusses how to determine the arrangement of compressors in a two-unit gas pipeline station where there is no standby unit. The compressors are driven by variable speed drivers such as gas turbines or variable frequency electric motors. Both series and parallel arrangements are analyzed in a transient simulation mode to determine which operation mode is more advantageous. Among the assumptions in this paper are the performance characteristics of the compressor. It will be outlined how these performance characteristics influence the conclusions.

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Xu, Hong, Hua Dong Yang, and Guang Ru Hua. "The Effect of Inlet Conditions on Particle Deposition in Axial Flow Compressor." Advanced Materials Research 915-916 (April 2014): 1066–69. http://dx.doi.org/10.4028/www.scientific.net/amr.915-916.1066.

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Axial flow compressor is an important component, so the compressor performance is of crucial. Fouling changes blade geometry and blade surface roughness is increased, thus aerodynamic performance is affected. The flow of gas phase and gas-solid coupling phase are implemented to reveal the effect of inlet condition on particle deposition. Based on Euler-Lagrange model, this paper made numerical simulation of gas-solid two phase flow in the axial flow compressor rotor cascade. Simulation result shows that the increase of inlet temperature can result in the reduction of particle volume fraction. And particle mass concentration is affected by particle mass flow rate.

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He, Xing, Yu Jie Li, and Yong Bao Liu. "Sensitivity Analysis of Measurement Parameters of Marine Inter-Cooled Gas Turbine with Low-Pressure Compressor Fouling." Applied Mechanics and Materials 716-717 (December 2014): 600–603. http://dx.doi.org/10.4028/www.scientific.net/amm.716-717.600.

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According to the mechanism of thermal system modelling method, the implanting the health factors is adopted, the steady state non-1inear performance deterioration model is founded by integrating experience performance with thermodynamics theory. Considering the low-pressure compressor suffer from fouling, the performance deterioration of gas turbine is simulated based on the temperature-control of outlet of combustion chamber. The measurement parameters of variation are obtained; the mechanism and sensitivity of the change are defined. The results illustrate that the outlet pressure of the low-pressure compressor is degenerated obviously, so can be well-monitor sensors. The deterioration of low-pressure shaft speed is strong non-1inear decreased vs. the fouling increased. Thanks to the cooling for air of outlet of low-pressure compressor by intercooler, in conjunction with the power decreased of low-pressure turbine, the temperature of outlet of low-pressure compressor is have not bad influence on the high-pressure compressor. So the temperature without severe cast down, it is not fine for health monitor.

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Perevoschikov, S. I. "DIFFERENTIAL DIAGNOSTICS OF GAS-TURBINE UNITSBY THEIR MAIN COMPONENTS." Oil and Gas Studies, no. 2 (May 1, 2016): 107–15. http://dx.doi.org/10.31660/0445-0108-2016-2-107-115.

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The dependences were obtained which enable to determine the values of the performance factors of gas- turbine units such as gas turbines and axial-flow compressors. The results of testing of the received relations applicability for practical calculations are presented. The test showed the dependences validity for real processes.

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OUTA, Eisuke, Hiroyuki HAMANA, and Ryosuke MITO. "Development and Current Status of the Compressors for Industrial Gas Turbines." Journal of the Society of Mechanical Engineers 119, no. 1173 (2016): 438–41. http://dx.doi.org/10.1299/jsmemag.119.1173_438.

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Tsutsumi, S., and J. Boone. "The Design, Selection, and Application of Oil-Injected Screw Compressors for Fuel Gas Service." Journal of Engineering for Gas Turbines and Power 117, no. 1 (January 1, 1995): 81–87. http://dx.doi.org/10.1115/1.2812785.

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Fuel gas compressors installed in cogeneration systems must be highly reliable and efficient machines, like the other main components, such as gas turbines, gas engines, etc. In the range of gas flow rate and pressure conditions generally required for such systems, the oil-injected screw compressor is often the most suitable compressor type for these requirements. Advantages of oil injected screw compressors are: improved compression efficiency; low discharge gas temperature; high reliability; simple mechanical construction; which all result from injection of lubricant into the compressor. Injected lubricant is discharged together with compressed gas on the high-pressure side but the oil is separated by a fine oil separation system down to a level that causes no problems for the downstream combustion equipment. The oil-injected screw compressor is equipped with an integral stepless capacity control by means of a slide valve, which makes part-load operation possible with reduced power consumption and improves overall system efficiency. As cogeneration systems, which are energy efficient and environmentally sound, are now increasing in number, so oil-injected screw compressors are expected to be used more widely.

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Manwaring, S. R., and D. C. Wisler. "Unsteady Aerodynamics and Gust Response in Compressors and Turbines." Journal of Turbomachinery 115, no. 4 (October 1, 1993): 724–40. http://dx.doi.org/10.1115/1.2929308.

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A comprehensive series of experiments and analyses was performed on compressor and turbine blading to evaluate the ability of current, practical, engineering/analysis models to predict unsteady aerodynamic loading of modern gas turbine blading. This is part of an ongoing effort to improve methods for preventing blading failure. The experiments were conducted in low-speed research facilities capable of simulating the relevant aerodynamic features of turbomachinery. Unsteady loading on compressor and turbine blading was generated by upstream wakes and, additionally for compressors, by a rotating inlet distortion. Fast-response hot-wire anemometry and pressure transducers embedded in the airfoil surfaces were used to determine the aerodynamic gusts and resulting unsteady pressure responses acting on the airfoils. This is the first time that gust response measurements for turbines have been reported in the literature. Several different analyses were used to predict the unsteady component of the blade loading: (1) a classical flat-plate analysis, (2) a two-dimensional linearized flow analysis with a ‘frozen gust’ model, (3) a two-dimensional linearized flow analysis with a “distorted gust” model, (4) a two-dimensional linearized Euler analysis, and (5) a two-dimensional nonlinear Euler analysis. Also for the first time, a detailed comparison of these analyses methods is made and the importance of properly accounting for both vortical and potential disturbances is demonstrated. The predictions are compared with experiment and their abilities assessed to help guide designers in using these prediction schemes.

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Valenti, Michael. "Turbines for Synthesis Gas." Mechanical Engineering 120, no. 08 (August 1, 1998): 72–73. http://dx.doi.org/10.1115/1.1998-aug-6.

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This article reviews on one of the most demanding applications for steam turbines, which are providing the extraction steam for the production of ammonia and methanol synthesis gas, or syngas. Dresser-Rand Energy Systems, Wellsville, NY, designed their Syngas Steam Turbine specifically to meet these requirements. Demand is expected to grow for both ammonia and methanol. Ammonia is the source for most of the nitrogen fertilizer produced globally. The capacity in 1996 was 117 million metric tons, up from 113 million metric tons five years earlier. Dresser-Rand approached the syngas project with more than 30 years’ experience as a leading supplier of compression equipment for ammonia plants. The first Syngas Steam Turbine, and its complete compression train including Dresser-Rand DATUM compressors, was shipped to a methanol plant operated by Qatar Fuel Additives Ltd. in the Mesaieed Industrial Area, Qatar. It is scheduled to begin operation by the middle of next year, producing 610,000 metric tons of methanol annually. Dresser-Rand engineers have also adapted their Syngas Turbine technology for different applications.

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Zaita, A. V., G. Buley, and G. Karlsons. "Performance Deterioration Modeling in Aircraft Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 120, no. 2 (April 1, 1998): 344–49. http://dx.doi.org/10.1115/1.2818128.

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Steady-state performance models can be used to evaluate a new engine’s baseline performance. As a gas turbine accumulates operating time in the field, its performance deteriorates due to fouling, erosion, and wear. This paper presents the development of a model for predicting the performance deterioration of aircraft gas turbines. The model accounts for rotating component deterioration based on the aircraft mission profiles and environmental conditions and the engine’s physical and design characteristics. The methodology uses data correlations combined with a stage stacking technique for the compressor and a tip rub model, along with data correlations for the turbine to determine the amount of performance deterioration. The performance deterioration model interfaces with the manufacturer’s baseline engine simulation model in order to create a deteriorated performance model for that engine.

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Bringhenti, C., and J. R. Barbosa. "Methodology for gas turbine performance improvement using variable-geometry compressors and turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 218, no. 7 (November 2004): 541–49. http://dx.doi.org/10.1243/0957650042456980.

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Perevoschikov, S. I. "PROCEDURE OF PARAMETRIC DIAGNOSTICS OF GAS PUMPING UNITSWITH TURBINE DRIVE." Oil and Gas Studies, no. 5 (November 1, 2016): 101–8. http://dx.doi.org/10.31660/0445-0108-2016-5-101-108.

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The article describes the procedure of parametric diagnostics of gas pumping units with a turbine drive which enables to detect the unit state on the minimum information base with determination of the diagnostic conclusions probability. A two-level diagnostics is considered, namely by the units basic components (their injectors and gas turbine units, GTU) and by the GTU components (axial compressors, turbines and combustion chambers).

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Hashmi, Muhammad Baqir, Tamiru Alemu Lemma, and Zainal Ambri Abdul Karim. "Investigation of the Combined Effect of Variable Inlet Guide Vane Drift, Fouling, and Inlet Air Cooling on Gas Turbine Performance." Entropy 21, no. 12 (December 1, 2019): 1186. http://dx.doi.org/10.3390/e21121186.

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Variable geometry gas turbines are susceptible to various malfunctions and performance deterioration phenomena, such as variable inlet guide vane (VIGV) drift, compressor fouling, and high inlet air temperatures. The present study investigates the combined effect of these performance deterioration phenomena on the health and overall performance of a three-shaft gas turbine engine (GE LM1600). For this purpose, a steady-state simulation model of the turbine was developed using a commercial software named GasTurb 12. In addition, the effect of an inlet air cooling (IAC) technique on the gas turbine performance was examined. The design point results were validated using literature results and data from the manufacturer’s catalog. The gas turbine exhibited significant deterioration in power output and thermal efficiency by 21.09% and 7.92%, respectively, due to the augmented high inlet air temperature and fouling. However, the integration of the inlet air cooling technique helped in improving the power output, thermal efficiency, and surge margin by 29.67%, 7.38%, 32.84%, respectively. Additionally, the specific fuel consumption (SFC) was reduced by 6.88%. The VIGV down-drift schedule has also resulted in improved power output, thermal efficiency, and the surge margin by 14.53%, 5.55%, and 32.08%, respectively, while the SFC decreased by 5.23%. The current model can assist in troubleshooting the root cause of performance degradation and surging in an engine faced with VIGV drift and fouling simultaneously. Moreover, the combined study also indicated the optimum schedule during VIGV drift and fouling for performance improvement via the IAC technique.

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31

Rodgers, C. "Impingement Starting and Power Boosting of Small Gas Turbines." Journal of Engineering for Gas Turbines and Power 107, no. 4 (October 1, 1985): 821–27. http://dx.doi.org/10.1115/1.3239817.

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The technology of high-pressure air or hot-gas impingement from stationary shroud supplementary nozzles onto radial outflow compressors and radial inflow turbines to permit rapid gas turbine starting or power boosting is discussed. Data are presented on the equivalent turbine component performance for convergent/divergent shroud impingement nozzles, which reveal the sensitivity of nozzle velocity coefficient with Mach number and turbine efficiency with impingement nozzle admission arc. Compressor and turbine matching is addressed in the transient turbine start mode with the possibility of operating these components in braking or reverse flow regimes when impingement flow rates exceed design.

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Mishra, R. K. "Fouling and Corrosion in an Aero Gas Turbine Compressor." Journal of Failure Analysis and Prevention 15, no. 6 (September 29, 2015): 837–45. http://dx.doi.org/10.1007/s11668-015-0023-8.

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33

Martis, Dan. "Fuzzy Logic Estimation Applied to Newton Methods for Gas Turbines." Journal of Engineering for Gas Turbines and Power 129, no. 1 (March 1, 2004): 88–96. http://dx.doi.org/10.1115/1.2360597.

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This method, based on fuzzy logic principles, is intended to find the most likely solution of an over-determined system, in specific conditions. The method addresses typical problems encountered in gas turbine performance analysis and, more specifically, to the alignment of a synthesis model with measured data. Generally speaking, the relatively low accuracy of measurements introduces a random noise around the true value of a performance parameter and distorts any deterministic solution of a square matrix-based linear system. The fuzzy logic estimator is able to get very close to the real solution by using additional (pseudo-redundant) parameters and by building the most likely solution based on each of the measurement accuracies. The accuracy—or “quality”—of a measurement is encapsulated within an extra dimension which is defined as fuzzy and which encompasses the whole range of values, between 0 (false) and 1 (true). The value of the method is shown in two examples. The first simulates compressor fouling, the other deals with actual engine test data following a hardware modification. Both examples experience noisy measurements. The method is stable and effective even at high level of noise. The results are within the close vicinity of the expected levels (within 0.2% accuracy) and the accuracy is about ten times lower than the noise level.

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Ritchey, I., E. H. Fisher, and G. D. Agnew. "Water spray cooling of gas turbine cycles." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 214, no. 3 (May 1, 2000): 203–11. http://dx.doi.org/10.1243/0957650001538308.

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Aerodervative gas turbines intercooled by water spray injection systems have recently entered service. A calculation framework is presented which permits the effect of water spray injection for both intercooling and inlet chilling to be evaluated and compared with conventional cooling techniques for a range of cycles. The calculations are based on representative performance maps for compressors and turbines, focusing upon the actual performance benefits that can be realized from existing turbomachinery. The principal conclusions are that spray intercooling can give a greater power boost than conventional intercooling for a given compressor operating envelope spray inlet chilling can give performance benefits comparable with absorption chilling and intercooling is more attractive at ambient temperatures below 15°C, whereas inlet chilling is preferable at higher temperatures.

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35

Mund, F. C., and P. Pilidis. "Online compressor washing: A numerical survey of influencing parameters." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 1 (February 1, 2005): 13–23. http://dx.doi.org/10.1243/095765005x6881.

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Online compressor washing is an advanced method to recover power losses caused by compressor blade fouling without incurring the availability penalty of having to shut down the gas turbine engine. Liquid is sprayed into the compressor at full or near full load to wash off particulates accumulated on the compressor surfaces. In particular, the cleaning of the first stage is vital to reinstate the mass flow of the engine, and a uniform fluid distribution is desirable in order to cover the full annulus. To achieve this, washing systems are generally developed empirically. Owing to the variety of intake duct geometries and gas turbine engines, the design of washing systems is generally related to individual power plants. To illustrate the trends of the main influencing parameters, a numerical investigation has been undertaken, based on an application case of a washing system installed in a heavy-duty gas turbine. The parameters studied using computational fluid dynamics (CFD) were airflow reduction, injection location and direction, droplet mass, and injection velocity. The effectiveness of the washing system was evaluated from the fluid distribution at the compressor inlet plane. It has been shown that, depending on the spray nozzle location, different optimum droplet sizes and injection velocities are required. Consequently, the application of different nozzle types is advisable. The operating condition of the engine has a significant effect on the fluid distribution at the compressor inlet and therefore changes in engine mass flow have to be considered when deciding on a washing scheme.

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Blinov, Vitalii L., Oleg V. Komarov, and Egor A. Zaslavskiy. "Estimation of the driven gas turbine unit technical performance using the standard measuring systems." E3S Web of Conferences 178 (2020): 01044. http://dx.doi.org/10.1051/e3sconf/202017801044.

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In large pipeline gas transport systems the operation and maintenance of gas pumping units are carried according to the current number of equivalent working hours of centrifugal gas compressors and gas turbines. Modern terms of lean production require the maintenance procedure to be done according to the current technical performance of equipment. The paper presents a designed and verified methodology of technical performance estimation of gas turbine units using the standard measuring systems. This method includes a verified high-order mathematical model based on the gas dynamic function for the precise analytical description of turbomachinery aerodynamics. The models are defined for different types of multi-shaft gas turbines. In this article the results of technical performance estimation of different gas turbine units are discussed.

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Lyons, J. W., and A. Morrison. "Utility Perspective of Selecting Air Filter for Simple-Cycle, Heavy-Duty Combustion Turbines." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 670–73. http://dx.doi.org/10.1115/1.2906758.

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The combustion turbines evaluated for this study range in size (nominal) from 80 MW to 100 MW and operate at a compression ratio between 10 and 14. Under these conditions the compressor ingests about 500,000 to 725,000 cubic feet of air per minute for its rated output. With this volume of air, even low concentrations of contaminants can result in a significant total amount of contaminants entering the unit, which may cause compressor erosion, fouling, and foreign object damage in the compressor section and cooling air passage blockage, locking of turbine blade roots, and hot corrosion or sulfidation in the turbine section. Adequate protection against the above-mentioned degradation or damage due to poor air quality may be obtained by using properly designed air filters. An inadequate filter system or total lack of one results in a reduction in power and efficiency over the life of the unit and may significantly decrease the intervals between maintenance and thereby increase the cost of maintenance. Consideration should be given to adding an air inlet filter when or after the combustion turbine without air filter is overhauled to reduce future maintenance costs. This study investigates the need for an inlet air filtration system for simple-cycle, heavy-duty combustion turbines from a cost/benefit and operation standpoint. Options for inlet air filters include a self-cleaning pulse type filter, a surface loading cartridge filter without pulse feature, and a three-stage depth loading type media type filter. Benefits are determined by estimates of improvements in performance and effects on the combustion turbine’s longevity and maintenance.

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38

Arbon, I. M. "The Compression of Fuel Gas for Turbines, Engines, and Boilers in Cogeneration Plants." Journal of Engineering for Gas Turbines and Power 117, no. 1 (January 1, 1995): 67–73. http://dx.doi.org/10.1115/1.2812783.

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The proliferation of gas-fired cogeneration plants in recent years had led to many installations being located on sites remote from high-pressure gas pipelines. Since it is often impractical or not cost effective to provide a dedicated high-pressure gas supply, such installations are often based close to alternative sources of fuel, such as small natural gas wells, landfill sites, or sewage digester plants. This paper will look at typical gas sources and composition, requirements of the fired equipment, the types of fuel gas compressors normally used, methods of compressor capacity control, and the development of synthetic and semi-synthetic lubricants for fuel gas compression duty.

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HU, Yunfeng, Fei FANG, Tao WEI, Shuqing LIU, Guangshen JIANG, and Jun CAI. "Analysis of cracking gas compressor fouling by pyrolysis gas chromatography-mass spectrometry." Chinese Journal of Chromatography 31, no. 6 (2013): 596. http://dx.doi.org/10.3724/sp.j.1123.2012.12021.

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Muir, D. E., H. I. H. Saravanamuttoo, and D. J. Marshall. "Health Monitoring of Variable Geometry Gas Turbines for the Canadian Navy." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 244–50. http://dx.doi.org/10.1115/1.3240243.

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The Canadian Department of National Defence has identified a need for improved Engine Health Monitoring procedures for the new Canadian Patrol Frigate (CPF). The CPF propulsion system includes two General Electric LM2500 gas turbines, a high-pressure-ratio engine with multiple stages of compressor variable geometry. A general method for predicting the thermodynamic performance of variable geometry axial compressors has been developed. The new modeling technique is based on a meanline stage-stacking analysis and relies only on the limited performance data typically made available by engine manufacturers. The method has been applied to the LM2500-30 marine gas turbine and the variations in engine performance that can result from a malfunction of the variable geometry system in service have been estimated.

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Doel, D. L. "TEMPER—A Gas-Path Analysis Tool for Commercial Jet Engines." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 82–89. http://dx.doi.org/10.1115/1.2906813.

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Almost from the inception of the gas turbine engine, airlines and engine manufacturers have sought an effective technique to determine the health of the gas-path components (fan, compressors, combustor, turbines) based on available gas-path measurements. The potential of such tools to save money by anticipating the need for overhaul and providing help in work scope definition is substantial, provided they produce reliable results. This paper describes a modern gas-path analysis tool (GE’s TEMPER program), discusses the benefits and problems experienced by current TEMPER users, and suggests promising research areas that may lead to an improved algorithm.

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Alozie, O., Y. G. Li, M. Diakostefanis, X. Wu, X. Shong, and W. Ren. "Assessment of degradation equivalent operating time for aircraft gas turbine engines." Aeronautical Journal 124, no. 1274 (January 9, 2020): 549–80. http://dx.doi.org/10.1017/aer.2019.153.

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ABSTRACTThis paper presents a novel method for quantifying the effect of ambient, environmental and operating conditions on the progression of degradation in aircraft gas turbines based on the measured engine and environmental parameters. The proposed equivalent operating time (EOT) model considers the degradation modes of fouling, erosion, and blade-tip wear due to creep strain, and expresses the actual degradation rate over the engine clock time relative to a pre-defined reference condition. In this work, the effects of changing environmental and engine operating conditions on the EOT for the core engine booster compressor and the high-pressure turbine were assessed by performance simulation with an engine model. The application to a single and multiple flight scenarios showed that, compared to the actual engine clock time, the EOT provides a clear description of component degradation, prediction of remaining useful life, and sufficient margin for maintenance action to be planned and performed before functional failure.

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43

Niccolini Marmont Du Haut Champ, Carlo Alberto, Aristide Fausto Massardo, Mario Luigi Ferrari, and Paolo Silvestri. "Surge prevention in gas turbines: an overview over historical solutions and perspectives about the future." E3S Web of Conferences 113 (2019): 02003. http://dx.doi.org/10.1051/e3sconf/201911302003.

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The aim of the present work is to retrace experimental, analytical and numerical analyses which deal with compressor instability phenomena, such as rotating stall and surge. While the first affects only the machine itself, the second involves the whole energy system. Surge onset is characterized by strong pressure and mass flow rate fluctuations which can even lead to reverse flow through the compressor. Experimental studies on prevention of axial compressor fluid dynamic instabilities, which can be propagated and eventually damage the solid structure, have been carried out by many authors. The first important studies on this topic tried to underline the main aspects of the complex detailed mechanism of surge, by replacing the compression system with an equivalent conceptual lumped parameter model. This is specially meant to capture the unsteady behaviour and the transient response of the compression system itself, particularly its dependence on variations in the volume of discharge downstream and in the settings of the throttle valve at its outlet (which simulates the actual load coupled to the compressor). Greitzer’s model is still regarded as the milestone for new investigations about active control and stabilization of surge and, more generally, about active suppression of aerodynamic instabilities in turbomachinery. During the last years, a lot of simulations and experimental studies about surge have been conducted on multistage centrifugal compressors with different architectures (e.g. equipped with vaneless or vaned diffusers). Moreover, further kinds of analysis try to extend the stable working zone of compressors, identifying stall and surge precursors extractable from information contained in the vibro-acoustical and rotodynamic response of the system.

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Wang, Ya Rong, and Pei Rong Wang. "Steam Flow in Nozzle and the Nozzle Calculation." Applied Mechanics and Materials 433-435 (October 2013): 1975–78. http://dx.doi.org/10.4028/www.scientific.net/amm.433-435.1975.

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The adiabatic flow process of gas or steam in a nozzle is not only widely used in steam turbines or other power equipment, but also applied to ejectors, impeller-type compressors, burners and other thermal devices in air conditioning, ventilation and gas engineering. In this paper we will describe steam flow in nozzle and the nozzle calculation, especially the relationship between the flow velocity and the flow area. We will describe the calculation on the velocity through a nozzle and the calculation on the area of the nozzle by an example.

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Yucel, U., and J. Y. Kazakia. "Analytical Prediction Techniques for Axisymmetric Flow in Gas Labyrinth Seals." Journal of Engineering for Gas Turbines and Power 123, no. 1 (May 12, 2000): 255–57. http://dx.doi.org/10.1115/1.1340630.

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Labyrinth seals are commonly found in turbines and compressors. Their objective is to control gas leakage from high pressure regions to low pressure regions. The correct prediction and control of this leakage is crucial for the efficient and economic operation of turbomachinery. In this paper we present approaches for obtaining the above prediction in a simple analytical and explicit method. Both constant and pressure dependent flow coefficients are incorporated in the present study which extends to the higher inlet/outlet pressure differences. The results obtained with our methods compare favorably with the ones obtained by both numerical and experimental techniques. In many cases there is hardly a distinction between our results and the numerical prediction.

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Dwivedi, Vijay Kumar, Satish Chand, and K. N. Pandey. "Analysis of Hybrid (Hydrodynamic/Hydrostatic) Journal Bearing." Advanced Materials Research 650 (January 2013): 385–90. http://dx.doi.org/10.4028/www.scientific.net/amr.650.385.

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The Hybrid (hydrodynamic/ hydrostatic) journal bearing system has found wide spread application in high speed rotating machines such as compressors, gas turbines, steam turbines, etc. The present studies include solution of Reynolds equation for hydrodynamic journal bearing with infinitely long approximation (ILA), infinitely short bearing approximation (ISA) and finite journal bearing approximation. Further Finite Journal bearing approximation considers two dimensional solution of Reynolds equation with natural boundary condition, which cannot be solved by analytical method. So, here the solutions for finite journal bearing have been done with finite difference method (a MATLAB® code is prepared for finite difference method) to get bearing performance parameters such as load capacity, Sommerfeld no., etc.

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Prisacariu, Vasile, Constantin Rotaru, and Mihai Leonida Niculescu. "Considerations and simulations about Pulse Detonation Engine." MATEC Web of Conferences 290 (2019): 04009. http://dx.doi.org/10.1051/matecconf/201929004009.

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PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo-gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens.

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Sharma, Sidharath, Jorge García-Tíscar, John M. Allport, Simon Barrans, and Ambrose K. Nickson. "Effects of ported shroud casing treatment on the acoustic and flow behaviour of a centrifugal compressor." International Journal of Engine Research 21, no. 6 (October 7, 2019): 998–1011. http://dx.doi.org/10.1177/1468087419880431.

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Centrifugal turbomachines of smaller sizes operating at higher speeds have become pervasive due to the increased specific power and reliability achieved by improvements in manufacturing, materials and computational methods. The presence of these small turbomachines, specifically compressors, in helicopters, unmanned aerial vehicles, auxiliary power units, turbochargers and micro gas turbines necessitates superior aerodynamic performance over a broad operational range, which is widely achieved by ported shroud casing designs. In addition to aerodynamic performance, acoustic emissions have become a critical aspect of design for these small centrifugal compressors due to high operational speeds. Furthermore, the literature on the acoustic effects of the casing treatment is rather limited. Therefore, the impact of ported shroud casing treatment on the acoustic and flow features of the compressor operating at the design and near-surge conditions have been quantified by numerically modelling the open and blocked configuration of the compressors. Upon comparing with experimental results, the numerical spectra are shown to capture the differences between the two configurations at the investigated operating points with reasonable accuracy. Although the casing treatment is generally seen to decrease the overall acoustic emission of the compressor at both operating conditions, increased propagation of tonal content in the direction upstream to the impeller is observed, particularly for design operation. Broadband characteristics in the lower and medium frequency regions usually associated with near-surge operation including ‘whoosh’ noise are observed to be alleviated by the ported shroud casing treatment.

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Kurz, R., and K. Brun. "Degradation in Gas Turbine Systems." Journal of Engineering for Gas Turbines and Power 123, no. 1 (November 1, 2000): 70–77. http://dx.doi.org/10.1115/1.1340629.

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Any prime mover exhibits the effects of wear and tear over time. The problem of predicting the effects of wear and tear on the performance of any engine is still a matter of discussion. Because the function of a gas turbine is the result of the fine-tuned cooperation of many different components, the emphasis of this paper is on the gas turbine and its driven equipment (compressor or pump) as a system, rather than on isolated components. We will discuss the effect of degradation on the package as part of a complex system (e.g., a pipeline, a reinjection station, etc.). Treating the gas turbine package as a system reveals the effects of degradation on the match of the components as well as on the match with the driven equipment. This article will contribute insights into the problem of gas turbine system degradation. Based on some detailed studies on the mechanisms that cause engine degradation, namely, changes in blade surfaces due to erosion or fouling, and the effect on the blade aerodynamics; changes in seal geometries and clearances, and the effect on parasitic flows; and changes in the combustion system (e.g., which result in different pattern factors), the effects of degradation will be discussed. The study includes a methodology to simulate the effects of engine and driven equipment degradation. With a relatively simple set of equations that describe the engine behavior, and a number of linear deviation factors which can easily be obtained from engine maps or test data, the equipment behavior for various degrees of degradation will be studied. A second model, using a stage by stage model for the engine compressor, is used to model the compressor deterioration. The authors have avoided to present figures about the speed of degradation, because it is subject to a variety of operational and design factors that typically cannot be controlled entirely.

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Wu, C. Y. "Arbitrary Surface Flank Milling of Fan, Compressor, and Impeller Blades." Journal of Engineering for Gas Turbines and Power 117, no. 3 (July 1, 1995): 534–39. http://dx.doi.org/10.1115/1.2814127.

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It is generally conceived that a blade surface is flank millable if it can be closely approximated by a ruled surface; otherwise the slow machining process of point milling has to be employed. However, we have now demonstrated that the ruled surface criterion for flank milling is neither necessary nor sufficient. Furthermore, many complex arbitrary surfaces typical of our blades in fans, axial compressors, and centrifugal impellers in aviation gas turbines are actually closely flank millable and can be rendered exactly flank millable with one or more passes per surface often without sacrificing, indeed usually with gain, in performance.

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

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