Journal articles on the topic 'Gas Turbine Engine Combustion'
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1
Agbadede, Roupa, and Biweri Kainga. "Effect of Water Injection into Aero-derivative Gas Turbine Combustors on NOx Reduction." European Journal of Engineering Research and Science 5, no. 11 (November 21, 2020): 1357–59. http://dx.doi.org/10.24018/ejers.2020.5.11.2180.
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Oxides of Nitrogen (NOx) generated from gas turbines causes enormous harm to human health and the environment. As a result, different methods have been employed to reduce NOx produced from gas turbine combustion process. One of such technique is the injection of water or steam into the combustion chamber to reduce the flame temperature. A twin shaft aero-derivative gas turbine was modelled and simulated using GASTURB simulation software. The engine was modelled after the GE LM2500 class of gas turbine engines. Water injection into the gas turbine combustor was simulated by implanting water-to-fuel ratios of 0 to 0.8, in an increasing order of 0.2. The results show that when water-to-fuel ratio was increased, the Nox severity index reduced. While heat rate and fuel flow increased with water-to-fuel ratio (injection flow rate).
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Agbadede, Roupa, and Isaiah Allison. "Effect of Water Injection into Aero-derivative Gas Turbine Combustors on NOx Reduction." European Journal of Engineering and Technology Research 5, no. 11 (November 21, 2020): 1357–59. http://dx.doi.org/10.24018/ejeng.2020.5.11.2180.
Full textAbstract:
Oxides of Nitrogen (NOx) generated from gas turbines causes enormous harm to human health and the environment. As a result, different methods have been employed to reduce NOx produced from gas turbine combustion process. One of such technique is the injection of water or steam into the combustion chamber to reduce the flame temperature. A twin shaft aero-derivative gas turbine was modelled and simulated using GASTURB simulation software. The engine was modelled after the GE LM2500 class of gas turbine engines. Water injection into the gas turbine combustor was simulated by implanting water-to-fuel ratios of 0 to 0.8, in an increasing order of 0.2. The results show that when water-to-fuel ratio was increased, the Nox severity index reduced. While heat rate and fuel flow increased with water-to-fuel ratio (injection flow rate).
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Zhu, Dengting, Zhenzhong Sun, and Xinqian Zheng. "Turbocharging strategy among variable geometry turbine, two-stage turbine, and asymmetric two-scroll turbine for energy and emission in diesel engines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 7 (November 28, 2019): 900–914. http://dx.doi.org/10.1177/0957650919891355.
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Energy saving and emission reduction are very urgent for internal combustion engines. Turbocharging and exhaust gas recirculation technologies are very significant for emissions and fuel economy of internal combustion engines. Various after-treatment technologies in internal combustion engines have different requirements for exhaust gas recirculation rates. However, it is not clear how to choose turbocharging technologies for different exhaust gas recirculation requirements. This work has indicated the direction to the turbocharging strategy among the variable geometry, two-stage, and asymmetric twin-scroll turbocharging for different exhaust gas recirculation rates. In the paper, a test bench engine experiment was presented to validate the numerical models of the three diesel engines employed with the asymmetric twin-scroll turbine, two-stage turbine, and variable geometry turbine. On the basis of the numerical models, the turbocharging routes among the three turbocharging approaches under different requirements for EGR rates are studied, and the other significant performances of the three turbines were also discussed. The results show that there is an inflection point in the relative advantages of asymmetric, variable geometry, and two-stage turbocharged engines. At the full engine load, when the EGR rate is lower than 29%, the two-stage turbocharging technology has the best performances. However, when the exhaust gas recirculation rate is higher than 29%, the asymmetric twin-scroll turbocharging is the best choice and more appropriate for driving high exhaust gas recirculation rates. The work may offer guidelines to choose the most suitable turbocharging technology for engine engineers and manufacturers to achieve further improvements in engine energy and emissions.
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Chand, Dharmahinder Singh, Daamanjyot Barara, Gautam Ganesh, and Suraj Anand. "Comparison of Efficiency of Conventional Shaped Circular and Elliptical Shaped Combustor." MATEC Web of Conferences 151 (2018): 02002. http://dx.doi.org/10.1051/matecconf/201815102002.
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There have been concerted efforts towards improving the fuel efficiency of the jet engines in the past, with an aim of reducing the incomplete combustion. The process of combustion in a jet engine takes place in the combustor. A study was conducted for enhancement of air-fuel mixing process by computational analysis of an elliptically shaped combustor for a gas turbine engine. The results of computational analysis of an elliptical shape combustor were compared with a circular shape combustor used in gas turbine engines with a identical cross sectional area. The comparison of the computationally derived parameters of the two combustors i.e. temperature, pressure, and velocity are studied and analyzed. The study intends towards the comparison of the combustion efficiencies of the circular and elliptically shaped combustors. The combustion efficency of elliptical chamber is found to be 98.72% at the same time it was observed 56.26% in case of circular type combustor.
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Kru¨ger, U., J. Hu¨ren, S. Hoffmann, W. Krebs, P. Flohr, and D. Bohn. "Prediction and Measurement of Thermoacoustic Improvements in Gas Turbines With Annular Combustion Systems." Journal of Engineering for Gas Turbines and Power 123, no. 3 (October 1, 2000): 557–66. http://dx.doi.org/10.1115/1.1374437.
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Environmental compatibility requires low emission burners for gas turbine power plants. In the past, significant progress has been made developing low NOx and CO burners by introducing lean premixed techniques in combination with annular combustion chambers. Unfortunately, these burners often have a more pronounced tendency to produce combustion-driven oscillations than conventional burner designs. The oscillations may be excited to such an extent that the risk of engine failure occurs. For this reason, the prediction of these thermoacoustic instabilities in the design phase of an engine becomes more and more important. A method based on linear acoustic four-pole elements has been developed to predict instabilities of the ring combustor of the 3A-series gas turbines. The complex network includes the whole combustion system starting from both compressor outlet and fuel supply system and ending at the turbine inlet. The flame frequency response was determined by a transient numerical simulation (step-function approach). Based on this method, possible improvements for the gas turbine are evaluated in this paper. First, the burner impedance is predicted theoretically and compared with results from measurements on a test rig for validation of the prediction approach. Next, the burner impedance in a gas turbine combustion system is analyzed and improved thermoacoustically. Stability analyses for the gas turbine combustion system show the positive impact of this improvement. Second, the interaction of the acoustic parts of the gas turbine system has been detuned systematically in circumferential direction of the annular combustion chamber in order to find a more stable configuration. Stability analyses show the positive effect of this measure as well. The results predicted are compared with measurements from engine operation. The comparisons of prediction and measurements show the applicability of the prediction method in order to evaluate the thermoacoustic stability of the combustor as well as to define possible countermeasures.
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Jansen, M., T. Schulenberg, and D. Waldinger. "Shop Test Result of the V64.3 Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 676–81. http://dx.doi.org/10.1115/1.2906641.
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The V64.3 60-MW combustion turbine is the first of a new generation of high-temperature gas turbines, designed for 50 and 60 Hz simple cycle, combined cycle, and cogeneration applications. The prototype engine was tested in 1990 in the Berlin factories under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearances, strains, vibrations, and exhaust emissions. The paper describes the engine design, the test facility and instrumentation, and the engine performance. Results are given for turbine blade temperatures, compressor and turbine vibrations, exhaust gas temperature, and NOx emissions for combustion of natural gas and fuel oil.
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Hutchins, T. E., and M. Metghalchi. "Energy and Exergy Analyses of the Pulse Detonation Engine." Journal of Engineering for Gas Turbines and Power 125, no. 4 (October 1, 2003): 1075–80. http://dx.doi.org/10.1115/1.1610015.
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Energy and exergy analyses have been performed on a pulse detonation engine. A pulse detonation engine is a promising new engine, which uses a detonation wave instead of a deflagration wave for the combustion process. The high-speed supersonic combustion wave reduces overall combustion duration resulting in an nearly constant volume energy release process compared to the constant pressure process of gas turbine engines. Gas mixture in a pulse detonation engine has been modeled to execute the Humphrey cycle. The cycle includes four processes: isentropic compression, constant volume combustion, isentropic expansion, and isobaric compression. Working fluid is a fuel-air mixture for unburned gases and products of combustion for burned gases. Different fuels such as methane and JP10 have been used. It is assumed that burned gases are in chemical equilibrium states. Both thermal efficiency and effectiveness (exergetic efficiency) have been calculated for the pulse detonation engine and simple gas turbine engine. Comparison shows that for the same pressure ratio pulse detonation engine has better efficiency and effectiveness than the gas turbine system.
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Sarkar, Asis. "A TOPSIS method to evaluate the technologies." International Journal of Quality & Reliability Management 31, no. 1 (December 20, 2013): 2–13. http://dx.doi.org/10.1108/ijqrm-03-2013-0042.
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Purpose – This paper aims to evaluate nine types of electrical energy generation options with regard to seven criteria. The analytic hierarchy process (AHP) was used to perform the evaluation. The TOPSIS method was used to evaluate the best generation technology. Design/methodology/approach – The options that were evaluated are the hydrogen combustion turbine, the hydrogen internal combustion engine, the hydrogen fuelled phosphoric acid fuel cell, the hydrogen fuelled solid oxide fuel cell, the natural gas fuelled phosphoric acid fuel cell, the natural gas fuelled solid oxide fuel cell, the natural gas turbine, the natural gas combined cycle and the natural gas internal combustion engine. The criteria used for the evaluation are CO2 emissions, NOX emissions, efficiency, capital cost, operation and maintenance costs, service life and produced electricity cost. Findings – The results drawn from the analysis in technology wise are as follows: natural gas fuelled solid oxide fuel cells>natural gas combined cycle>natural gas fuelled phosphoric acid fuel cells>natural gas internal combustion engine>hydrogen fuelled solid oxide fuel cells>hydrogen internal combustion engines>hydrogen combustion turbines>hydrogen fuelled phosphoric acid fuel cells> and natural gas turbine. It shows that the natural gas fuelled solid oxide fuel cells are the best technology available among all the available technology considering the seven criteria such as service life, electricity cost, O&M costs, capital cost, NOX emissions, CO2 emissions and efficiency of the plant. Research limitations/implications – The most dominant electricity generation technology proved to be the natural gas fuelled solid oxide fuel cells which ranked in the first place among nine alternatives. The research is helpful to evaluate the different alternatives. Practical implications – The research is helpful to evaluate the different alternatives and can be extended in all the spares of technologies. Originality/value – The research was the original one. Nine energy generation options were evaluated with regard to seven criteria. The energy generation options were the hydrogen combustion turbine, the hydrogen internal combustion engine, the hydrogen fuelled phosphoric acid fuel cell, the hydrogen fuelled solid oxide fuel cell, the natural gas fuelled phosphoric acid fuel cell, the natural gas fuelled solid oxide fuel cell, the natural gas turbine, the natural gas combined cycle and the natural gas internal combustion engine. The criteria used for the evaluation were efficiency, CO2 emissions, NOX emissions, capital cost, O&M costs, electricity cost and service life.
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Langston, Lee S. "Breaking the Barriers." Mechanical Engineering 134, no. 05 (May 1, 2012): 32–37. http://dx.doi.org/10.1115/1.2012-may-2.
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This article explores the new developments in the field of gas turbines and the recent progress that has been made in the industry. The gas turbine industry has had its ups and downs over the past 20 years, but the production of engines for commercial aircraft has become the source for most of its growth of late. Pratt & Whitney’s recent introduction of its new geared turbofan engine is an example of the primacy of engine technology in aviation. Many advances in commercial aviation gas turbine technology are first developed under military contracts, since jet fighters push their engines to the limit. Distributed generation and cogeneration, where the exhaust heat is used directly, are other frontiers for gas turbines. Work in fluid mechanics, heat transfer, and solid mechanics has led to continued advances in compressor and turbine component performance and life. In addition, gas turbine combustion is constantly being improved through chemical and fluid mechanics research.
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Langston, Lee S. "Riding the Surge." Mechanical Engineering 135, no. 05 (May 1, 2013): 37–41. http://dx.doi.org/10.1115/1.2013-may-2.
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This article explores the advantages of gas turbines in the marine industry. Marine gas turbines, which are designed specifically for use on ships, have long been one of the segments of the gas turbine market. One advantage that gas turbines have over conventional marine diesels is volume. Gas turbines are the prime movers for the modern combined cycle electric power plant. Both CFM International (a joint venture of General Electric and France’s Snecma) and Pratt & Whitney are working on new engines for this multibillion dollar single-aisle, narrow-body market. Pratt & Whitney’s new certified PW1500G geared turbofans will have a first flight powering the first Bombardier CSeries aircraft. On land, sea, and air, the surge in gas turbine production is remarkable. The experts suggest that what the steam engine was to the 19th century and the internal combustion engine was to the 20th, the gas turbine might be to the 21st century: the ubiquitous prime mover of choice.
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Smith, Lance L., Hasan Karim, Marco J. Castaldi, Shahrokh Etemad, William C. Pfefferle, Vivek Khanna, and Kenneth O. Smith. "Rich-Catalytic Lean-Burn Combustion for Low-Single-Digit NOx Gas Turbines." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 27–35. http://dx.doi.org/10.1115/1.1787510.
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A new rich-catalytic lean-burn combustion concept (trademarked by PCI as RCL) was tested at industrial gas turbine conditions, in Solar Turbines’ high-pressure (17 atm) combustion rig and in a modified Solar Turbines engine, demonstrating ultralow emissions of NOx<2 ppm and CO<10 ppm for natural gas fuel. For the single-injector rig tests, an RCL catalytic reactor replaced a single swirler/injector. NOx<3 ppm and CO<10 ppm were achieved over a 110°C operating range in flame temperature, including NOx<1 ppm at about 1350°C flame temperature. Combustion noise was less than 0.15% peak to peak. Four RCL catalytic reactors were then installed in a modified (single can combustor) engine. NOx emissions averaged 2.1 ppm over the allowable operating range for this modified engine, with CO<10 ppm and without combustion noise (less than 0.15% peak to peak).
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Richards, G. A., and M. C. Janus. "Characterization of Oscillations During Premix Gas Turbine Combustion." Journal of Engineering for Gas Turbines and Power 120, no. 2 (April 1, 1998): 294–302. http://dx.doi.org/10.1115/1.2818120.
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The use of premix combustion in stationary gas turbines can produce very low levels of Nox emissions. This benefit is widely recognized, but turbine developers routinely encounter problems with combustion oscillations during the testing of new premix combustors. Because of the associated pressure fluctuations, combustion oscillations must be eliminated in a final combustor design. Eliminating these oscillations is often time-consuming and costly because there is no single approach to solve an oscillation problem. Previous investigations of combustion stability have focused on rocket applications, industrial furnaces, and some aeroengine gas turbines. Comparatively little published data is available for premixed combustion at conditions typical of an industrial gas turbine. In this paper, we report experimental observations of oscillations produced by a fuel nozzle typical of industrial gas turbines. Tests are conducted in a specially designed combustor capable of providing the acoustic feedback needed to study oscillations. Tests results are presented for pressure up to 10 atmospheres, with inlet air temperatures up to 588 K (600 F) burning natural gas fuel. Based on theoretical considerations, it is expected that oscillations can be characterized by a nozzle reference velocity, with operating pressure playing a smaller role. This expectation is compared to observed data that shows both the benefits and limitations of characterizing the combustor oscillating behavior in terms of a reference velocity rather than other engine operating parameters. This approach to characterizing oscillations is then used to evaluate how geometric changes to the fuel nozzle will affect the boundary between stable and oscillating combustion.
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Grigoriev, A. V., A. A. Kosmatov, О. A. Rudakov, and A. V. Solovieva. "Theory of gas turbine engine optimal gas generator." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 2 (July 2, 2019): 52–61. http://dx.doi.org/10.18287/2541-7533-2019-18-2-52-61.
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The article substantiates the necessity of designing an optimal gas generator of a gas turbine engine. The generator is to provide coordinated joint operation of its units: compressor, combustion chamber and compressor turbine with the purpose of reducing the period of development of new products, improving their fuel efficiency, providing operability of the blades of a high-temperature cooled compressor turbine and meeting all operational requirements related to the operation of the optimal combustion chamber including a wide range of stable combustion modes, high-altitude start at subzero air and fuel temperature conditions and prevention of the atmosphere pollution by toxic emissions. Methods of optimizing the parameters of coordinated joint operation of gas generator units are developed. These parameters include superficial flow velocities in the boundary interface cross sections between the compressor and the combustion chamber, as well as between the combustion chamber and the compressor turbine. The effective efficiency of the engine thermodynamic cycle is the optimization target function. The required depth of the turbine blades cooling is a functional constraint evaluated with account for calculations of irregularity and instability of the gas temperature field and the actual flow turbulence intensity at the blades’ inlet. We carried out theoretical analysis of the influence of various factors on the gas flow that causes changes in the flow total pressure in the channels of the gas generator gas dynamic model, i.e. changes in the efficiencies of its units. It is shown that the long period (about five years) of the engine final development time, is due to the necessity to perform expensive full-scale tests of prototypes, in particular, it is connected with an incoordinate assignment in designing the values of the flow superficial velocities in the boundary sections between the gas generator units. Designing of an optimal gas generator is only possible on the basis of an integral mathematical model of an optimal combustion chamber.
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Waitz, Ian A., Gautam Gauba, and Yang-Sheng Tzeng. "Combustors for Micro-Gas Turbine Engines." Journal of Fluids Engineering 120, no. 1 (March 1, 1998): 109–17. http://dx.doi.org/10.1115/1.2819633.
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The development of a hydrogen-air microcombustor is described. The combustor is intended for use in a 1 mm2 inlet area, micro-gas turbine engine. While the size of the device poses several difficulties, it also provides new and unique opportunities. The combustion concept investigated is based upon introducing hydrogen and premixing it with air upstream of the combustor. The wide flammability limits of hydrogen-air mixtures and the use of refractory ceramics enable combustion at lean conditions, obviating the need for both a combustor dilution zone and combustor wall cooling. The entire combustion process is carried out at temperatures below the limitations set by material properties, resulting in a significant reduction of complexity when compared to larger-scale gas turbine combustors. A feasibility study with initial design analyses is presented, followed by experimental results from 0.13 cm3 silicon carbide and steel microcombustors. The combustors were operated for tens of hours, and produced the requisite heat release for a microengine application over a range of fuel-air ratios, inlet temperatures, and pressures up to four atmospheres. Issues of flame stability, heat transfer, ignition and mixing are addressed. A discussion of requirements for catalytic processes for hydrocarbon fuels is also presented.
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Wu, Heng, Shufan Zhao, Jijun Zhang, Bo Sun, and Hanqiang Song. "Gas turbine power calculation method of turboshaft based on simulation and performance model." MATEC Web of Conferences 189 (2018): 02003. http://dx.doi.org/10.1051/matecconf/201818902003.
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Gas turbine power of turboshaft engine cannot be measured, a total of five typical steady state point test data from the ground slow state to the maximum state were selected according to the factory acceptance test drive of a certain type of carrier-based helicopter turboshaft engine. Combustion chamber three-dimensional simulation model was established to carry on simulation analysis of different typical steady state combustion process. The simulated combustion chamber exit section parameters are input into the established gas turbine isentropic adiabatic aerodynamic calculation model to obtain the gas turbine power and outlet temperature. Select five typical steady state points of five sets of turboshaft engines on the same type to repeat the above calculation process, and compare the calculated value of gas turbine outlet temperature with the acceptance test values, it is found that the error values are all within 5%, and the effectiveness and accuracy of the gas turbine power calculation method are verified.
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Sadowski, Tomasz, and Przemysław Golewski. "The Analysis of Heat Transfer and Thermal Stresses in Thermal Barrier Coatings under Exploitation." Defect and Diffusion Forum 326-328 (April 2012): 530–35. http://dx.doi.org/10.4028/www.scientific.net/ddf.326-328.530.
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Effectiveness of internal combustion turbines in aero-engines is limited by comparatively low temperature of exhaust gas at the entry to turbine of the engine. A thermal efficiency and other capacities of turbine strongly depend on the ratio of the highest to the lowest temperature of a working medium. Continuous endeavour to increase the thermal resistance of engine elements requires, apart from laboratory investigations, also numerical studies in 3D of different aero-engine parts. In the present work, the effectiveness of the protection of turbine blades by thermal barrier coating and internal cooling under thermal shock cooling was analysed numerically using the ABAQUS code. The phenomenon of heating the blade from temperature of combustion gases was studied. This investigation was preceded by the CFD analysis in the ANSYS Fluent program which allows for calculation of the temperature of combustion gases. The analysis was conducted for different levels of the shock temperature, different thickness of applied TBC, produced from different kinds of materials.
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Zhang, Tian Gang, and Xiao Yun Hou. "NOx Emission Control in Gas Turbines." Applied Mechanics and Materials 66-68 (July 2011): 319–21. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.319.
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The increase, in recent years, in the size and efficiency of gas turbines burning natural gas in combined cycle has occurred against a background of tightening environmental legislation on the emission of nitrogen oxides. The higher turbine entry temperatures required for efficiency improvement tend to increase NOX production. To reduce NOX emissions, new engine core configurations with heat management and active systems, as well as advanced combustor technology, have to be investigated. This paper reviews the various approaches adopted by the main gas turbine manufacturers which are achieving low levels of NOX emission from natural gas combustion.
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Stitzel, Sarah, and Karen A. Thole. "Flow Field Computations of Combustor-Turbine Interactions Relevant to a Gas Turbine Engine." Journal of Turbomachinery 126, no. 1 (January 1, 2004): 122–29. http://dx.doi.org/10.1115/1.1625691.
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The current demands for high-performance gas turbine engines can be reached by raising combustion temperatures to increase power output. High combustion temperatures create a harsh environment that leads to the consideration of the durability of the combustor and turbine sections. This paper presents a computational study of a flow field that is representative of what occurs in a combustor and how that flow field convects through the first downstream stator vane. The results of this study indicate that the development of the secondary flow field in the turbine is highly dependent on the incoming total pressure profile. The endwall heat transfer is also found to depend strongly on the secondary flow field.
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Corman, G. S., A. J. Dean, S. Brabetz, M. K. Brun, K. L. Luthra, L. Tognarelli, and M. Pecchioli. "Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications." Journal of Engineering for Gas Turbines and Power 124, no. 3 (June 19, 2002): 459–64. http://dx.doi.org/10.1115/1.1455637.
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General Electric has developed SiC fiber-reinforced SiC-Si matrix composites produced by silicon melt infiltration for use in gas turbine engine applications. High temperature, high-pressure combustion rig testing, and engine testing has been performed on combustor liners and turbine shrouds made from such MI composites. Frame 5 sized combustor liners were rig tested under lean head end diffusion flame conditions for 150 hours, including 20 thermal trip cycles, with no observed damage to the ceramic liners. Similarly, 46-cm diameter, single-piece turbine shroud rings were fabricated and tested in a GE-2 gas turbine engine. The fabrication and testing of both components are described.
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Selviyanty, Veny, and Aris Fiatno. "ANALISA UNJUK KERJA TURBIN GAS PLTG DUAL FUEL SYSTEM (STUDY KASUS DI PT. XXX SIAK)." Jurnal Teknik Industri Terintegrasi 3, no. 1 (May 14, 2020): 33–48. http://dx.doi.org/10.31004/jutin.v3i1.810.
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PT. XXX serviced the Kawasaki GPB80 gas turbine with the latest data on the use of gas fuel in gas turbine unit 6 on average 32,028 liters / day and the use of diesel fuel in turbine unit 3 is 39,111 liters / day. This research was conducted with field observations and literature studies. Field observations obtained the following data: pressure, temperature at predetermined points, engine generator, the surrounding environment and required supporting data. The specific fuel consumption obtained in unit 6 gas turbines using diesel fuel is 0.049 l / kW hour. turbine efficiency obtained in unit 3 gas turbines using diesel fuel is 9.02%. Decreased Torque performance in unit 3 gas turbine of 6186 Nm caused by an average T2 temperature of 85 0C before entering the combustion chamber so that the combustion process is incomplete in the combustion chamber resulting in thermal efficiency in the unit 3 gas turbine not proportional to the Specific Fuel Consumtion or usage diesel fuel against the effective power produced. The specific fuel consumption in unit 3 gas turbine is 0.06 l / kW.h while the unit 6 gas turbine is 0.04 l / k.W.h.
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Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.
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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.
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Richards, Geo A., Jimmy D. Thornton, Edward H. Robey, and Leonell Arellano. "Open-Loop Active Control of Combustion Dynamics on a Gas Turbine Engine." Journal of Engineering for Gas Turbines and Power 129, no. 1 (March 16, 2006): 38–48. http://dx.doi.org/10.1115/1.2204978.
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Combustion dynamics is a prominent problem in the design and operation of low-emission gas turbine engines. Even modest changes in fuel composition or operating conditions can lead to damaging vibrations in a combustor that was otherwise stable. For this reason, active control has been sought to stabilize combustors that must accommodate fuel variability, new operating conditions, etc. Active control of combustion dynamics has been demonstrated in a number of laboratories, single-nozzle test combustors, and even on a fielded engine. In most of these tests, active control was implemented with closed-loop feedback between the observed pressure signal and the phase and gain of imposed fuel perturbations. In contrast, a number of recent papers have shown that open-loop fuel perturbations can disrupt the feedback between acoustics and heat release that drives the oscillation. Compared to the closed-loop case, this approach has some advantages because it may not require high-fidelity fuel actuators, and could be easier to implement. This paper reports experimental tests of open-loop fuel perturbations to control combustion dynamics in a complete gas turbine engine. Results demonstrate the technique was very successful on the test engine and had minimal effect on pollutant emissions.
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Desmico Ekta W, Muhammad, and Abrar Ridwan. "STUDI KERUSAKAN HIGH PRESSURE TURBINE VANE PESAWAT ATR72-500 WINGS AIR DI BANDARA SULTAN SYARIF KASIIM II PEKANBARU." Jurnal Surya Teknika 7, no. 1 (December 13, 2020): 104–10. http://dx.doi.org/10.37859/jst.v7i1.2357.
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The aircraft can fly as there is a thrust from the engine that causes the aircraft to have speed. The components of the aircraft engines are compressor, combustion chamber, turbine and propeller. High pressure turbine vanes is a component in the Hot section or turbine section that serves to direct the hot gas flow from the combustion chamber to the turbine. The purpose to be achieved in this research is to analyze and find out the cause of high pressure turbine vane damage and know the gas engine efficiency PW127. Cause of damage due to treatment not done according to the schedule until the phenomenon of overtemperature after combustion chamber and the content of impurities in the water laundering results. After the Brayton cycle calculation is obtained the temperature value of the turbine entry 1563oC (1836 K). These results exceed the turbine inlet temperature according to manual maintenance engine. Based on laboratory test, the content of 250 mg/m2 sulfur and 1800 mg/m2 chloride is obtained. This content causes damage by erosion or corrosion of high pressure turbine vane components. The value of gas efficiency is 42% according to the outside Air tempetarure. The thermal efficiency of gases will increase with increasing temperature conditions.
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Kumar, M. V. H. Satish. "Combustion Dynamic Analysis of Gas Turbine Engine." International Journal of Engineering Trends and Technology 50, no. 6 (August 25, 2017): 321–28. http://dx.doi.org/10.14445/22315381/ijett-v50p254.
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Cowell, L. H., R. T. LeCren, and C. E. Tenbrook. "Two-Stage Slagging Combustor Design for a Coal-Fueled Industrial Gas Turbine." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 359–66. http://dx.doi.org/10.1115/1.2906599.
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A full-size combustor for a coal-fueled industrial gas turbine engine has been designed and fabricated. The design is based on extensive work completed through one-tenth scale combustion tests. Testing of the combustion hardware will be completed with a high pressure air supply in a combustion test facility before the components are integrated with the gas turbine engine. The combustor is a two-staged, rich-lean design. Fuel and air are introduced in the primary combustion zone where the combustion process is initiated. The primary zone operates in a slagging mode inertially removing coal ash from the gas stream. Four injectors designed for coal water mixture (CWM) atomization are used to introduce the fuel and primary air. In the secondary combustion zone, additional air is injected to complete the combustion process at fuel lean conditions. The secondary zone also serves to reduce the gas temperatures exiting the combustor. Between the primary and secondary zones is a Particulate Rejection Impact Separator (PRIS). In this device much of the coal ash that passes from the primary zone is inertially separated from the gas stream. The two-staged combustor along with the PRIS have been designated as the combustor island. All of the combustor island components are refractory-lined to minimize heat loss. Fabrication of the combustor has been completed. The PRIS is still under construction. The combustor hardware is being installed at the Caterpillar Technical Center for high pressure test evaluation. The design, test installation, and test plan of the full-size combustor island are discussed.
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Korakianitis, T., L. Meyer, M. Boruta, and H. E. McCormick. "Introduction and Performance Prediction of a Nutating-Disk Engine." Journal of Engineering for Gas Turbines and Power 126, no. 2 (April 1, 2004): 294–99. http://dx.doi.org/10.1115/1.1635394.
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A new type of internal combustion engine and its thermodynamic cycle are introduced. The core of the engine is a nutating nonrotating disk, with the center of its hub mounted in the middle of a Z-shaped shaft. The two ends of the shaft rotate, while the disk nutates. The motion of the disk circumference prescribes a portion of a sphere. A portion of the area of the disk is used for intake and compression, a portion is used to seal against a center casing, and the remaining portion is used for expansion and exhaust. The compressed air is admitted to an external accumulator, and then into an external combustion chamber before it is admitted to the power side of the disk. The accumulator and combustion chamber are kept at constant pressures. The engine has a few analogies with piston-engine operation, but like a gas turbine it has dedicated spaces and devices for compression, burning, and expansion. The thermal efficiency is similar to that of comparably sized simple-cycle gas turbines and piston engines. For the same engine volume and weight, this engine produces less specific power than a simple-cycle gas turbine, but approximately twice the power of a two-stroke engine and four times the power of a four-stroke engine. The engine has advantages in the 10 kW to 200 kW power range. This paper introduces the geometry and thermodynamic model for the engine, presents typical performance curves, and discusses the relative advantages of this engine over its competitors.
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Sato, H., M. Mori, and T. Nakamura. "Development of a Dry Ultra-Low NOx Double Swirler Staged Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 120, no. 1 (January 1, 1998): 41–47. http://dx.doi.org/10.1115/1.2818086.
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This paper describes the development of an ultra-low NOx gas turbine combustor for cogeneration systems. The combustor, called a double swirler staged combustor, utilizes three-staged premixed combustion for low NOx emission. The unique feature of the combustor is its tertiary premix nozzles located downstream of the double swirler premixing nozzles around the combustor liner. Engine output is controlled by simply varying the fuel gas flow, and therefore employs no complex variable geometries for airflow control. Atmospheric combustion tests have demonstrated the superior performance of the combustor. NOx level is maintained at less than 3 ppm (O2 = 15 percent) over the range of engine output between 50 and 100 percent. Assuming the general relationship that NOx emission is proportional to the square root of operating pressure, the NOx level is estimated at less than 9 ppm (O2 = 15 percent) at the actual pressure of 0.91 MPa (abs.). Atmospheric tests have also shown high combustion efficiency; more than 99.9 percent over the range of engine output between 60 and 100 percent. Emissions of CO and UHC are maintained at 0 and 1 ppm (O2 = 15 percent), respectively, at the full engine load.
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Singh, Rahul, Amber Jain, and Harish Kumar. "New Design of Ignition System of Gas Turbine." Applied Mechanics and Materials 592-594 (July 2014): 1662–66. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1662.
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This paper is all about a new type of ignition system for igniting the air-fuel mixture within combustion chamber of a gas turbine engine. In this system there will a separate ignition inside the primary combustion chamber which will be outside the main combustion chamber and responsible for igniting main source of air/fuel mixture inside the combustion chamber. This system is designed to overcome several problems of present ignition system of gas turbine engine and also thermal analysis of this new system has been shown in this paper.
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Sadykova, S. B., A. M. Dostiyarov, A. M. Dostiyarova, and N. R. Kartjanov. "Simulation of the operating conditions in a gas turbine engine combustion chamber." BULLETIN of L.N. Gumilyov Eurasian National University. Technical Science and Technology Series 130, no. 1 (2020): 71–77. http://dx.doi.org/10.32523/2616-68-36-2020-130-1-71-77.
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Korczewski, Zbigniew. "Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes." Polish Maritime Research 18, no. 3 (January 1, 2011): 37–42. http://dx.doi.org/10.2478/v10012-011-0015-x.
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Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes The second part of the article presents the results of operating diagnostic tests of a two- and three-shaft engine with a separate power turbine during the start-up and acceleration of the rotor units. Attention was paid to key importance of the correctness of operation of the automatic engine load control system, the input for which, among other signals, is the rate of increase of the exhaust gas flow temperature. The article presents sample damages of the engine flow section which resulted from disturbed functioning of this system. The unsteady operation of the compressor during engine acceleration was the source of excessive increase of the exhaust gas temperature behind the combustion chamber and partial burning of the turbine blade tips.
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Richards, G. A., R. S. Gemmen, and M. J. Yip. "A Test Device for Premixed Gas Turbine Combustion Oscillations." Journal of Engineering for Gas Turbines and Power 119, no. 4 (October 1, 1997): 776–82. http://dx.doi.org/10.1115/1.2817054.
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We report the design and operation of a test device suitable for studying combustion oscillations produced by commercial-scale gas turbine fuel nozzles. Unlike conventional test stands, this test combustor uses a Helmholtz acoustic geometry to replicate the acoustic response that would otherwise be observed only during complete engine testing. We suggest that successful simulation of engine oscillations requires that the flame geometry and resonant frequency of the test device should match the complete engine environment. Instrumentation for measuring both pressure and heat release variation is described. Preliminary tests suggest the importance of characterizing the oscillating behavior in terms of a nozzle reference velocity and inlet air temperature. Initial tests also demonstrate that the stabilizing effect of a pilot flame depends on the operating conditions.
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Al-Hamdan, Qusai Z., and Munzer S. Y. Ebaid. "Modeling and Simulation of a Gas Turbine Engine for Power Generation." Journal of Engineering for Gas Turbines and Power 128, no. 2 (April 27, 2005): 302–11. http://dx.doi.org/10.1115/1.2061287.
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The gas turbine engine is a complex assembly of a variety of components that are designed on the basis of aerothermodynamic laws. The design and operation theories of these individual components are complicated. The complexity of aerothermodynamic analysis makes it impossible to mathematically solve the optimization equations involved in various gas turbine cycles. When gas turbine engines were designed during the last century, the need to evaluate the engines performance at both design point and off design conditions became apparent. Manufacturers and designers of gas turbine engines became aware that some tools were needed to predict the performance of gas turbine engines especially at off design conditions where its performance was significantly affected by the load and the operating conditions. Also it was expected that these tools would help in predicting the performance of individual components, such as compressors, turbines, combustion chambers, etc. At the early stage of gas turbine developments, experimental tests of prototypes of either the whole engine or its main components were the only method available to determine the performance of either the engine or of the components. However, this procedure was not only costly, but also time consuming. Therefore, mathematical modelling using computational techniques were considered to be the most economical solution. The first part of this paper presents a discussion about the gas turbine modeling approach. The second part includes the gas turbine component matching between the compressor and the turbine which can be met by superimposing the turbine performance characteristics on the compressor performance characteristics with suitable transformation of the coordinates. The last part includes the gas turbine computer simulation program and its philosophy. The computer program presented in the current work basically satisfies the matching conditions analytically between the various gas turbine components to produce the equilibrium running line. The computer program used to determine the following: the operating range (envelope) and running line of the matched components, the proximity of the operating points to the compressor surge line, and the proximity of the operating points at the allowable maximum turbine inlet temperature. Most importantly, it can be concluded from the output whether the gas turbine engine is operating in a region of adequate compressor and turbine efficiency. Matching technique proposed in the current work used to develop a computer simulation program, which can be served as a valuable tool for investigating the performance of the gas turbine at off-design conditions. Also, this investigation can help in designing an efficient control system for the gas turbine engine of a particular application including being a part of power generation plant.
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Leonard, G., and J. Stegmaier. "Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 542–46. http://dx.doi.org/10.1115/1.2906853.
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This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first-stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90 percent relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.
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Dzida, Marek. "On the possible increasing of efficiency of ship power plant with the system combined of marine diesel engine, gas turbine and steam turbine, at the main engine - steam turbine mode of cooperation." Polish Maritime Research 16, no. 1 (January 1, 2009): 47–52. http://dx.doi.org/10.2478/v10012-008-0010-z.
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On the possible increasing of efficiency of ship power plant with the system combined of marine diesel engine, gas turbine and steam turbine, at the main engine - steam turbine mode of cooperation This paper presents a concept of a ship combined high-power system consisted of main piston engine and associated with it: gas power turbine and steam turbine subsystems, which make use of energy contained in exhaust gas from main piston engine. The combined system consisted of a piston combustion engine and an associated with it steam turbine subsystem, was considered. An algorithm and results of calculations of the particular subsystems, i.e. of piston combustion engine and steam turbine, are presented. Assumptions and limitations taken for calculations, as well as comparison of values of some parameters of the system and results of experimental investigations available from the literature sources, are also given. The system's energy optimization was performed from the thermodynamic point of view only. Any technical - economical analyses were not carried out. Numerical calculations were performed for a Wärtsilä slow-speed diesel engine of 52 MW output power.
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Liever, Peter A., Clifford E. Smith, and Geoffrey D. Meyers. "Fluid Modeling vs. Pollution." Mechanical Engineering 121, no. 01 (January 1, 1999): 64–66. http://dx.doi.org/10.1115/1.1999-jan-5.
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This article reviews how computational fluid dynamics (CFD) analysis provides an enhanced understanding of a low-emission combustion system. When AlliedSignal Engines in Phoenix wanted its ASE40 industrial gas turbine to meet tough new standards for nitrogen oxide emissions, the company decided to try a design that injected water into the combustion zone so the system would burn cooler. AlliedSignal combined full-scale engine tests and computer models to study the effect of water injection on the ASE40. CFD provided detailed flow field information not available from engine tests. This information allowed engineers to verify the effectiveness of the numerous design changes made in axial air swirlers, mixing jets, and cooling flows. Work is also in progress on a dual-fuel system with water injection, using the same gas/water manifold and combustor. Oil fuel will be introduced through the original water circuit, with water being introduced into the gas side. This system will be distributed for the European market by AlliedSignal’s partner, Motoren-und Turbinen-Union (MTU) of Friedrichshafen, Germany.
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Fukudome, Takero, Sazo Tsuruzono, Tetsuo Tatsumi, Yoshihiro Ichikawa, Tohru Hisamatsu, and Isao Yuri. "Development of Silicon Nitride Components for Gas Turbine." Key Engineering Materials 287 (June 2005): 10–15. http://dx.doi.org/10.4028/www.scientific.net/kem.287.10.
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Silicon nitride is one of the most practical candidates for ceramic gas turbines. The SN282 is silicon nitride material developed by Kyocera for gas turbines. Several new technologies have been developed to achieve materialization of ceramic gas turbines, such as material, fabrication process, evaluation / analysis technology. Recent technology is focused on recession of silicon-based ceramics under combustion gas. Environmental Barrier Coatings (EBCs) are developed to suppress these recession. We have found rare-earth element silicate and yttrium stabilized zirconium oxide (YSZ) have high corrosion resistance to the combustion gas. These materials were applied to the ceramic gas turbine components. The components with EBCs were evaluated in the actual engine tests. We have confirmed that the EBCs effectively work for the recession resistance.
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Karaman, Mehmet, Ibrahim Özkol, and Güven Kömürgöz. "Heat Transfer Enhancement in Turbine Blade Internal Cooling Ducts." Advanced Materials Research 1016 (August 2014): 743–47. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.743.
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Gas turbine is a type of rotary engine that consists of compressor, combustion chamber, and turbine sections. This type of engine works in the Brayton Cycle principle that is compression of atmospheric flow, combustion of air-fuel mixture and expanding high temperature combustion flow to generate power output from turbine. The aim of this study is to determine the duct geometry and flow conditions of the gas turbine blades having the internal cooling ducts that acquire highest heat transfer on turbine blades. For different design of internal duct geometries and flow conditions, Fluent solver is used and solutions are validated with Han’s experimental results.
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Торба, Юрий Иванович, Сергей Игоревич Планковский, Олег Валерьевич Трифонов, Евгений Владимирович Цегельник, and Дмитрий Викторович Павленко. "МОДЕЛИРОВАНИE ПРОЦЕССА ГОРЕНИЯ В ФАКЕЛЬНЫХ ВОСПЛАМЕНИТЕЛЯХ ГТД." Aerospace technic and technology, no. 7 (August 31, 2019): 39–49. http://dx.doi.org/10.32620/aktt.2019.7.05.
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The aim of the work was the development and testing of methods for modeling the combustion process in the torch igniters of gas turbine engines. To achieve it, the finite element method was used. The main results of the work are the substantiation of the need to optimize the torch igniters of gas turbine engines. The practice of operating torch igniters of various designs has shown that the stability of their work depends on the parameters of gas turbine engines and external factors (air and fuel temperature, size of fuel droplets, fuel and air consumption, as well as its pressure). At the same time, the scaling of the geometry of the igniter design does not ensure its satisfactory work in the composition of the GTE with modified parameters. In this regard, an urgent task is to develop a combustion model in a flare igniter to optimize its design. A computational model of a torch igniter for a gas turbine engine of a serial gas-turbine engine in a software package for numerical three-dimensional thermodynamic simulation of AN-SYS FLUENT has been developed. To reduce the calculation time and the size of the finite element model, recommendations on the adaptation of the geometric model of the igniter for numerical modeling are proposed. The mod-els of flow turbulence and combustion, as well as initial and boundary conditions, are selected and substantiated. Verification of the calculation results obtained by comparison of numerical simulation with the data of tests on a specialized test bench was performed. It is shown that the developed computational model makes it possible to simulate the working process in the torch igniters of the GTE combustion chambers of the investigated design with a high degree of confidence. The scientific novelty of the work consists in substantiating the choice of the combustion model, the turbulence model, as well as the initial and boundary conditions that provide adequate results to the full-scale experiment on a special test bench. The developed method of modeling the combustion process in gas turbine torch igniters can be effectively used to optimize the design of igniters based on GTE operation conditions, as well as combustion initialization devices to expand the range of stable operation of the combustion chamber.
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Lefebvre, A. H. "The Role of Fuel Preparation in Low-Emission Combustion." Journal of Engineering for Gas Turbines and Power 117, no. 4 (October 1, 1995): 617–54. http://dx.doi.org/10.1115/1.2815449.
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The attainment of very low pollutant emissions, in particular oxides of nitrogen (NOx), from gas turbines is not only of considerable environmental concern but has also become an area of increasing competitiveness between the different engine manufacturers. For stationary engines, the attainment of ultralow NOx has become the foremost marketing issue. This paper is devoted primarily to current and emerging technologies in the development of ultralow emissions combustors for application to aircraft and stationary engines. Short descriptions of the basic design features of conventional gas turbine combustors and the methods of fuel injection now in widespread use are followed by a review of fuel spray characteristics and recent developments in the measurement and modeling of these characteristics. The main gas-turbine-generated pollutants and their mechanisms of formation are described, along with related environmental risks and various issues concerning emissions regulations and recently enacted legislation for limiting the pollutant levels emitted by both aircraft and stationary engines. The impacts of these emissions regulations on combustor and engine design are discussed first in relation to conventional combustors and then in the context of variable-geometry and staged combustors. Both these concepts are founded on emissions reduction by control of flame temperature. Basic approaches to the design of “dry” low-NOx and ultralow-NOx combustors are reviewed. At the present time lean, premix, prevaporize combustion appears to be the only technology available for achieving ultralow NOx emissions from practical combustors. This concept is discussed in some detail, along with its inherent problems of autoignition, flashback, and acoustic resonance. Attention is also given to alternative methods of achieving ultralow NOx emissions, notably the rich-burn, quick-quench, lean-burn, and catalytic combustors. These concepts are now being actively developed, despite the formidable problems they present in terms of mixing and durability. The final section reviews the various correlations now being used to predict the exhaust gas concentrations of the main gaseous pollutant emissions from gas turbine engines. Comprehensive numerical methods have not yet completely displaced these semi-empirical correlations but are nevertheless providing useful insight into the interactions of swirling and recirculating flows with fuel sprays, as well as guidance to the combustion engineer during the design and development stages. Throughout the paper emphasis is placed on the important and sometimes pivotal role played by the fuel preparation process in the reduction of pollutant emissions from gas turbines.
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Dzida, Marek, and Jerzy Girtler. "Operation Evaluation Method for Marine Turbine Combustion Engines in Terms of Energetics." Polish Maritime Research 23, no. 4 (December 1, 2016): 67–72. http://dx.doi.org/10.1515/pomr-2016-0071.
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Abstract An evaluation proposal (quantitative determination) of any combustion turbine engine operation has been presented, wherein the impact energy occurs at a given time due to Energy conversion. The fact has been taken into account that in this type of internal combustion engines the energy conversion occurs first in the combustion chambers and in the spaces between the blade of the turbine engine. It was assumed that in the combustion chambers occurs a conversion of chemical energy contained in the fuel-air mixture to the internal energy of the produced exhaust gases. This form of energy conversion has been called heat. It was also assumed that in the spaces between the blades of the rotor turbine, a replacement occurs of part of the internal energy of the exhaust gas, which is their thermal energy into kinetic energy conversion of its rotation. This form of energy conversion has been called the work. Operation of the combustion engine has been thus interpreted as a transmission of power receivers in a predetermined time when there the processing and transfer in the form (means) of work and heat occurs. Valuing the operation of this type of internal combustion engines, proposed by the authors of this article, is to determine their operation using physical size, which has a numerical value and a unit of measurement called joule-second [joule x second]. Operation of the combustion turbine engine resulting in the performance of the turbine rotor work has been presented, taking into account the fact that the impeller shaft is connected to the receiver, which may be a generator (in the case of one-shaft engine) or a propeller of the ship (in the case of two or three shaft engine).
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Rusakov, A. N. "Selection of Optimal Gas-Dynamic Parameters of Radial-Axial Turbines in Their Joint Operation with Reciprocating Internal Combustion Engines." Proceedings of Higher Educational Institutions. Маchine Building, no. 6 (735) (June 2021): 58–66. http://dx.doi.org/10.18698/0536-1044-2021-6-58-66.
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The study of radial-axial (centripetal) turbines is important for science and technology. They are widely used in the refrigeration industry, internal combustion engines, and power engineering, both in the form of auxiliary units and in autonomous power units. The article offers a method for selecting the gas-dynamic parameters of the centripetal turbine in order to obtain the highest efficiency and the best size of the turbine. The increased manufacturability of the turbine is provided due to the absence of a straightener at the outlet of the impeller and the use of straight blades in the impeller. The dependence of the efficiency of a centripetal turbine on the profiles of the blades and the radial dimensions of the nozzle apparatus and the impeller, as well as on the length of the impeller blades is investigated. Considering the recommended optimal parameters, the calculation of a pulsed centripetal turbine operating in conjunction with a four-stroke piston internal combustion engine is performed.
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Hayashi, Jun, Hideki Moriai, Noriaki Nakatsuka, Kazuki Tainaka, and Fumiteru Akamatsu. "Measurement of Combustion Field in Gas Turbine Engine." Journal of the Visualization Society of Japan 31, no. 120 (2011): 27. http://dx.doi.org/10.3154/jvs.31.27.
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Pien, Pao Chi. "Limited-Temperature Compound Cycle Hybrid Piston-Turbine Engine." Journal of Ship Production 19, no. 04 (November 1, 2003): 217–22. http://dx.doi.org/10.5957/jsp.2003.19.4.217.
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A new hybrid piston-turbine engine is presented comprised of a power turbine driven by exhaust gas of a new 4SDI engine utilizing a new piston-cam assembly powertrain and operating on a limited-temperature compound cycle. The limited-temperature compound cycle has a prolonged combustion process under a limited combustion temperature. By limiting the combustion temperature, NOx formation is avoided; by prolonging combustion, more complete combustion occurs, minimizing particulates and other noxious emissions. The power turbine extends the expansion process started in the 4SDI engine to reach the atmospheric pressure for achieving high fuel economy. The piston-cam powertrain, which features reciprocating pistons that oscillate cam followers, through a rocking yoke mechanism to rotate a power output camshaft, significantly reduces engine friction losses to achieve high mechanical efficiency. The new hybrid piston-turbine engine, which can be developed with existing technologies, has particularly beneficial application to ship propulsion.
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Perevoschikov, S. I. "CALCULATION OF EFFECTIVE COMBUSTION PRODUCTS TEMPERATURE BEFORE THE GAS-TURBINE ENGINES POWER TURBINES." Oil and Gas Studies, no. 1 (February 28, 2016): 100–106. http://dx.doi.org/10.31660/0445-0108-2016-1-100-106.
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The article describes derivation of relationships permitting to calculate the temperature of combustion products before the power turbines of gas-turbine engines taking into account a partial return of the lost earlier power of the combustion products in the previous turbines. Using these relationships data significantly improves determination of the gas-turbine engines effective output by their operation data.
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Бойко, Людмила Георгиевна, Олег Владимирович Кислов, and Наталия Владимировна Пижанкова. "МЕТОД РАСЧЕТА ТЕРМОГАЗОДИНАМИЧЕСКИХ ПАРАМЕТРОВ ТУРБОВАЛЬНОГО ГТД НА ОСНОВЕ ПОВЕНЦОВОГО ОПИСАНИЯ ЛОПАТОЧНЫХ МАШИН. ЧАСТЬ 1. ОСНОВНЫЕ УРАВНЕНИЯ." Aerospace technic and technology, no. 1 (February 25, 2018): 48–58. http://dx.doi.org/10.32620/aktt.2018.1.05.
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Gas turbine engines processes mathematic simulations are widely used in different steps of its living cycle. All engine simulations may be divided into different difficulty levels: higher simulation level allows doing a more precise description of physical processes in main units of gas turbine engines and their elements. It gives the opportunity for getting better arrangement of calculation results and experimental data, reduce the quality of factors, which are traditionally used in determine engine operational characteristics with 1-level models.The purpose of the article is to describe the thermogasdynamic parameters and maintenance perfomances calculation method, which based on second level mathematic simulation. Its main feature is blade-to-blade turbomachines description (multistage compressor and multistage cooling gas turbine), which allows to take into account blade and flow path geometrical parameters. Their changing during the gas turbine engine design and development processes influence its performances: thrust, fuel consumption, efficiency as functions of values of flow rate, rotational speed, engine entrance conditions and so on. All these dependences could be defined by using proposed calculation method.In distinction from methods which are noted, this method allows to concede compressor or turbine incidence angles, drag values, pressure ratio, surge margin in design and off-design engine regimes. The opportunity to take into account by-passing and air bleeding from compressor blade channels and their engine parameters influence is very important also.The article includes calculation method main points, block-scheme, equations system, which gives the opportunity of alignment the engine units and their elements in wide range of state working regimes. Set of equations consists of flow rate balance equations through the stages of multistage compressor and turbine, combustion chamber and connected channels. Also system includes power balance equations, by-passing, air bleeding from compressor stages channels, its admission into the cooling turbine stages and accounts their thermodynamic parameters. Compressors and turbines maps parameters are calculated with main turbomachinery theory lows and semi-empirical dependences.This article is the first in series of articles, which considers this problem
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Snyder, T. S., T. J. Rosfjord, J. B. McVey, A. S. Hu, and B. C. Schlein. "Emission and Performance of a Lean-Premixed Gas Fuel Injection System for Aeroderivative Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 118, no. 1 (January 1, 1996): 38–45. http://dx.doi.org/10.1115/1.2816547.
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A dry-low-NOx, high-airflow-capacity fuel injection system for a lean-premixed combustor has been developed for a moderate pressure ratio (20:1) aeroderivative gas turbine engine. Engine requirements for combustor pressure drop, emissions, and operability have been met. Combustion performance was evaluated at high power conditions in a high-pressure, single-nozzle test facility, which operates at full base-load conditions. Single digit NOx levels and high combustion efficiency were achieved. A wide operability range with no signs of flashback, autoignition, or thermal problems was demonstrated. NOx sensitivities to pressure and residence time were found to be small at flame temperatures below 1850 K (2870°F). Above 1850 K some NOx sensitivity to pressure and residence time was observed and was associated with the increased role of the thermal NOx production mechanism at elevated flame temperatures.
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Cherednichenko, Oleksandr, Serhiy Serbin, and Marek Dzida. "Investigation of the Combustion Processes in the Gas Turbine Module of an FPSO Operating on Associated Gas Conversion Products." Polish Maritime Research 26, no. 4 (December 1, 2019): 149–56. http://dx.doi.org/10.2478/pomr-2019-0077.
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Abstract In this paper, we consider the issue of thermo-chemical heat recovery of waste heat from gas turbine engines for the steam conversion of associated gas for offshore vessels. Current trends in the development of offshore infrastructure are identified, and the composition of power plants for mobile offshore drilling units and FPSO vessels is analyzed. We present the results of a comparison of power-to-volume ratio, power-to-weight ratio and efficiency for diesel and gas turbine power modules of various capacities. Mathematical modeling methods are used to analyze the parameters of an alternative gas turbine unit based on steam conversion of the associated gas, and the estimated efficiency of the energy module is shown to be 50%. In the modeling of the burning processes, the UGT 25000 serial low emission combustor is considered, and a detailed analysis of the processes in the combustor is presented, based on the application of a 35-reaction chemical mechanism. We confirm the possibility of efficient combustion of associated gas steam conversion products with different compositions, and establish that stable operation of the gas turbine combustor is possible when using fuels with low calorific values in the range 7–8 MJ/kg. It is found that the emissions of NOx and CO during operation of a gas turbine engine on the associated gas conversion products are within acceptable limits.
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Tolpadi, A. K. "Calculation of Two-Phase Flow in Gas Turbine Combustors." Journal of Engineering for Gas Turbines and Power 117, no. 4 (October 1, 1995): 695–703. http://dx.doi.org/10.1115/1.2815455.
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A method is presented for computing steady two-phase turbulent combusting flow in a gas turbine combustor. The gas phase equations are solved in an Eulerian frame of reference. The two-phase calculations are performed by using a liquid droplet spray combustion model and treating the motion of the evaporating fuel droplets in a Lagrangian frame of reference. The numerical algorithm employs nonorthogonal curvilinear coordinates, a multigrid iterative solution procedure, the standard k-ε turbulence model, and a combustion model comprising an assumed shape probability density function and the conserved scalar formulation. The trajectory computation of the fuel provides the source terms for all the gas phase equations. This two-phase model was applied to a real piece of combustion hardware in the form of a modern GE/SNECMA single annular CFM56 turbofan engine combustor. For the purposes of comparison, calculations were also performed by treating the fuel as a single gaseous phase. The effect on the solution of two extreme situations of the fuel as a gas and initially as a liquid was examined. The distribution of the velocity field and the conserved scalar within the combustor, as well as the distribution of the temperature field in the reaction zone and in the exhaust, were all predicted with the combustor operating both at high-power and low-power (ground idle) conditions. The calculated exit gas temperature was compared with test rig measurements. Under both low and high-power conditions, the temperature appeared to show an improved agreement with the measured data when the calculations were performed with the spray model as compared to a single-phase calculation.
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McGuirk, J. J. "The aerodynamic challenges of aeroengine gas-turbine combustion systems." Aeronautical Journal 118, no. 1204 (June 2014): 557–99. http://dx.doi.org/10.1017/s0001924000009386.
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Abstract The components of an aeroengine gas-turbine combustor have to perform multiple tasks – control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The ‘rich-burn’ concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the ‘lean-burn’ injectors required to meet the ever more stringent NO x emissions regulations are introduced, demonstrating that a new multi-disciplinary and ‘whole system’ approach is required. For example, high swirl causes complex unsteady injector aerodynamics; the threat of thermo-acoustic instabilities means both aerodynamic and aeroacoustic characteristics of injectors and other air admission features must be considered; and high injector mass flow means potentially strong compressor/combustor and combustor/turbine coupling. The paper illustrates how research at Loughborough University, based on complementary use of advanced experimental and computational methods, and applied to both isolated sub-components and fully annular combustion systems, has improved understanding and identified novel ideas for combustion system design.
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Cherednichenko, Oleksandr, Serhiy Serbin, and Marek Dzida. "Application of Thermo-chemical Technologies for Conversion of Associated Gas in Diesel-Gas Turbine Installations for Oil and Gas Floating Units." Polish Maritime Research 26, no. 3 (September 1, 2019): 181–87. http://dx.doi.org/10.2478/pomr-2019-0059.
Full textAbstract:
Abstract The paper considers the issue of thermo-chemical recovery of engine’s waste heat and its further use for steam conversion of the associated gas for oil and gas floating units. The characteristics of the associated gas are presented, and problems of its application in dual-fuel medium-speed internal combustion engines are discussed. Various variants of combined diesel-gas turbine power plant with thermo-chemical heat recovery are analyzed. The heat of the gas turbine engine exhaust gas is utilized in a thermo-chemical reactor and a steam generator. The engines operate on synthesis gas, which is obtained as a result of steam conversion of the associated gas. Criteria for evaluating the effectiveness of the developed schemes are proposed. The results of mathematical modeling of processes in a 14.1 MW diesel-gas turbine power plant with waste heat recovery are presented. The effect of the steam/associated gas ratio on the efficiency criteria is analyzed. The obtained results indicate relatively high effectiveness of the scheme with separate high and low pressure thermo-chemical reactors for producing fuel gas for both gas turbine and internal combustion engines. The calculated efficiency of such a power plant for considered input parameters is 45.6%.