Journal articles on the topic 'Gas turbine combustion chambers'
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1
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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Matyunin, O. O., S. K. Arkhipov, A. A. Shilova, N. L. Bachev, and R. V. Bulbovich. "Analysis of the combustion characteristics of hydrogen and hydrocarbon fuels based on the results of numerical simulation." Problems of the Regional Energetics, no. 3(55) (August 2022): 54–67. http://dx.doi.org/10.52254/1857-0070.2022.3-55.05.
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At present, an upward trend in the field of studying the processes of hydrogen combustion in the combustion chambers of the ground-based gas turbine power plants is obvious. The use of pure hydrogen as a fuel gas would solve the problem of environmental decarbonization. One of the emerging problems is to ensure the stable combustion of such fuels in combustion chambers of various applications. The information-analytical review of studies showed that there is a large number of theoretical and experimental results on the diffusion and homogeneous combustion of hydrogen and hydrogen-containing fuels in various burners and combustion chambers, which are not part of the existing gas turbine power plants. The purpose of this work is a comparative analysis of the gas-dynamic and emission characteristics of the combustion of the hydrogen-air and methane-air components based on the results of numerical simulation of a convertible combustion chamber of a 75 kW microgas turbine power plant. This goal is achieved by numerical simulation of the diffusion combustion of hydrogen and methane with air in a convertible combustion chamber. The most significant result of the work is obtaining the isosurface of the flame, which made it possible to obtain the conditions for stable combustion in the form of the Damköhler criterion and the ratio of the midsection velocity to the velocity of turbulent combustion. The significance of the results obtained lies in the further development of the methodology for the conversion of megawatt-class gas turbine plants to hydrogen and hydrogencontaining fuels.
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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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Mevissen, Frank, and Michele Meo. "A Review of NDT/Structural Health Monitoring Techniques for Hot Gas Components in Gas Turbines." Sensors 19, no. 3 (February 9, 2019): 711. http://dx.doi.org/10.3390/s19030711.
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The need for non-destructive testing/structural health monitoring (SHM) is becoming increasingly important for gas turbine manufacturers. Incipient cracks have to be detected before catastrophic events occur. With respect to condition-based maintenance, the complex and expensive parts should be used as long as their performance or integrity is not compromised. In this study, the main failure modes of turbines are reported. In particular, we focus on the turbine blades, turbine vanes and the transition ducts of the combustion chambers. The existing monitoring techniques for these components, with their own particular advantages and disadvantages, are summarised in this review. In addition to the vibrational approach, tip timing technology is the most used technique for blade monitoring. Several sensor types are appropriate for the extreme conditions in a gas turbine, but besides tip timing, other technologies are also very promising for future NDT/SHM applications. For static parts, like turbine vanes and the transition ducts of the combustion chambers, different monitoring possibilities are identified and discussed.
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Mrzljak, Vedran, Nikola Anđelić, Ivan Lorencin, and Zlatan Car. "Analysis of Gas Turbine Operation before and after Major Maintenance." Journal of Maritime & Transportation Science 57, no. 1 (December 2019): 57–70. http://dx.doi.org/10.18048/2019.57.04.
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This paper presents an analysis of the gas turbine real process (with all losses included) before and after a major maintenance. The analysis of both gas turbine operating regimes is based on data measured during its exploitation. Contrary to authors’ expectations, the major maintenance process did not result either in any decrease in losses or increase in efficiencies for the majority of the gas turbine components. However, the major maintenance influenced positively the gas turbine combustion chambers (reduction in losses and increase in the combustion chambers efficiency). After the major maintenance, the overall process efficiency decreased from 43.796% to 41.319% due to a significant decrease in the air mass flow rate and to an increase in the fuel mass flow rate in combustion chambers. A decrease in the gas turbine produced cumulative and useful power after a major maintenance also increased the specific fuel consumption.
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Brandauer, M., A. Schulz, and S. Wittig. "Mechanisms of Coke Formation in Gas Turbine Combustion Chambers." Journal of Engineering for Gas Turbines and Power 118, no. 2 (April 1, 1996): 265–70. http://dx.doi.org/10.1115/1.2816587.
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New gas turbine combustor designs are developed to reduce pollutant and NOx emissions. In these new combustors, the formation of carbonaceous deposits, especially in prevaporizers, affects the reliability and effectiveness of operation. To avoid deposits, a detailed knowledge of the origins and mechanisms of formation is required. To obtain a deeper insight, the phenomena were studied systematically. The deposits under consideration show differing characteristics suggesting more than one formation mechanism in the combustor. Consequently, the primary goal was to identify the formation mechanisms and, subsequently, to simulate the mechanisms under well-defined conditions in bench tests for determining the relevant parameters of deposit build-up. The mechanisms of formation were identified based on the properties of the deposits in the combustion chamber. In order to characterize the deposits, physical and chemical analysis techniques were utilized. In summary, tests and numerical predictions identified two major paths of formation: a deposit build-up resulting from flame products such as soot or coked droplets and a deposit build-up resulting from liquid fuel impinging the wall accompanied with chemical reactions at the wall. The deposits caused by fuel droplet impingement were intensively studied in bench tests. In analyzing the processes, the influence of wall temperature, fuel composition, and the oxygen content in the environment is shown in detail. In addition, the importance of thermal instabilities of the fuel, previously studied under fuel supply system conditions, is demonstrated for a deposit formation inside a combustion chamber.
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Iurashev, Dmytro, Giovanni Campa, Vyacheslav V. Anisimov, and Ezio Cosatto. "Two-step approach for pressure oscillations prediction in gas turbine combustion chambers." International Journal of Spray and Combustion Dynamics 9, no. 4 (May 30, 2017): 424–37. http://dx.doi.org/10.1177/1756827717711016.
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Currently, gas turbine manufacturers frequently face the problem of strong acoustic combustion-driven oscillations inside combustion chambers. These combustion instabilities can cause extensive wear and sometimes even catastrophic damage of combustion hardware. This requires prevention of combustion instabilities, which, in turn, requires reliable and fast predictive tools. We have developed a two-step method to find a set of operating parameters under which gas turbines can be operated without going into self-excited pressure oscillations. As the first step, an unsteady Reynolds-averaged Navier–Stokes simulation with the flame speed closure model implemented in the OpenFOAM® environment is performed to obtain the flame transfer function of the combustion set-up. As the second step time-domain simulations employing low-order network model implemented in Simulink® are executed. In this work, we apply the proposed method to the Beschaufelter RingSpalt test rig developed at the Technische Universität München. The sensitivity of thermoacoustic stability to the length of a combustion chamber, flame position, gain and phase of flame transfer function and outlet reflection coefficient are studied.
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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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Noiray, Nicolas, and Bruno Schuermans. "On the dynamic nature of azimuthal thermoacoustic modes in annular gas turbine combustion chambers." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 469, no. 2151 (March 8, 2013): 20120535. http://dx.doi.org/10.1098/rspa.2012.0535.
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This paper deals with the dynamics of standing and rotating azimuthal thermoacoustic modes in annular combustion chambers. Simultaneous acoustic measurements have been made at multiple circumferential positions in an annular gas turbine combustion chamber. A detailed statistical analysis of the spatial Fourier amplitudes extracted from these data reveals that the acoustic modes are continuously switching between standing, clockwise and counter-clockwise travelling waves. A theoretical framework from which the modal dynamics can be explained is proposed and supported by real gas turbine data. The stochastic differential equations that govern these systems have been derived and used as a basis for system identification of the measured engine data. The model describes the probabilities of the two azimuthal wave components as a function of the random source intensity, the asymmetry in the system and the strength of the thermoacoustic interaction. The solution of the simplified system is in good agreement with experimental observations on a gas turbine combustion chamber.
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Iurashev, Dmytro, Giovanni Campa, Vyacheslav V. Anisimov, Ezio Cosatto, Luca Rofi, and Edoardo Bertolotto. "Application of a three-step approach for prediction of combustion instabilities in industrial gas turbine burners." Journal of the Global Power and Propulsion Society 1 (July 21, 2017): JCW78T. http://dx.doi.org/10.22261/jcw78t.
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Abstract Recently, because of environmental regulations, gas turbine manufacturers are restricted to produce machines that work in the lean combustion regime. Gas turbines operating in this regime are prone to combustion-driven acoustic oscillations referred as combustion instabilities. These oscillations could have such high amplitude that they can damage gas turbine hardware. In this study, the three-step approach for combustion instabilities prediction is applied to an industrial test rig. As the first step, the flame transfer function (FTF) of the burner is obtained performing unsteady computational fluid dynamics (CFD) simulations. As the second step, the obtained FTF is approximated with an analytical time-lag-distributed model. The third step is the time-domain simulations using a network model. The obtained results are compared against the experimental data. The obtained results show a good agreement with the experimental ones and the developed approach is able to predict thermoacoustic instabilities in gas turbines combustion chambers.
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Al-Dabooni, Seaar Jawad, and Hussein Abdul Shaheed Al-Shawi. "Using Fuzzy Inference System in Gas Turbine to Overcome a High Exhaust Temperature Problem." Journal of Petroleum Research and Studies 12, no. 1(Suppl.) (April 21, 2022): 225–42. http://dx.doi.org/10.52716/jprs.v12i1(suppl.).634.
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The turbine units are at the forefront of equipment in the process of pumping crude oil and exporting it to the oil ports, where there are many types of turbines used in different sites of Iraqi stations whether pumping oil stations or electrical power production stations. One of the most important types of turbines is the gas turbine, which is frequently used in oil depots. One of the remarkable depots in Iraq is Zubair-1 / Basra that exports around 850,000 barrels per day (B/D). Therefore, Zubair-1 should continue pumping the crude oil 24/7, which has five gas turbines (three Rolls-Royce AVON MK 1533 and two Siemens SGT 400). However, the three Rolls-Royce gas turbines in Zubair-1 have not worked in the summer season since 2016, when the ambient temperature goes high around 11:00 am to 3:30 pm. This paper proposes solution to solve a high exhaust temperature (EGT) shutdown signal (a preventing running turbine signal) without effect on the sequence of turbine running stages. The proposal is adding a fuzzy inference system (FIS) that controls the gas turbine in the first two running stages that demonstrates and controls of speed the turbine from 800 RPM to 3000 RPM. The inputs of FIS are the average temperature of eight combustion chambers (exhaust temperatures) and the speed of the gas turbine, while the output of FIS is the control signal to the flow control valve (FCV) with an amplifier to gain the signal.
The FIS proposal has been applied in all three Rolls-Royce jet pumping turbines since April 7, 2021, and they work regularly at all times of the day. The FIS minimizes the maximum average of combustion chambers temperature at midafternoon in June 9, 2021 (48 ˚C ambience temperature) from 689 ˚C to 610 ˚C that means the improvement is around 45%.
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Hussein, Yahya, Sameerah Mustafa, and Suad Danook. "Exergy destruction calculation in gas turbine power plant and showing the effect of ambient temperature on it." Al-Kitab Journal for Pure Sciences 2, no. 2 (December 30, 2018): 276–91. http://dx.doi.org/10.32441/kjps.02.02.p19.
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The purpose of this paper is to estimate the quantity and quality of the useful energy that could be converted to work, this analysis was carried out based on the energy and exergy analysis by using the first and second laws of thermodynamics. This paper study the effect of varying the ambient temperature on the performance of the turbine. Results showed increasing in exergy destruction in the turbine solely and in each of its three components(Air compressor, Combustion chambers and the gas turbine) with increasing in ambient temperature. Also results showed by keeping the load unchanged, the exergy destruction are bigger in higher ambient temperatures than in lower ones. The exergy destruction concentrated in the combustion chambers, where the percent of exergy destruction in the combustion chambers to the total exergy destruction in the plant was(87%) followed by the air compressor(9%) and the lower exergy destruction was in the gas turbine(4%).
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Bellucci, V., P. Flohr, C. O. Paschereit, and F. Magni. "On the Use of Helmholtz Resonators for Damping Acoustic Pulsations in Industrial Gas Turbines." Journal of Engineering for Gas Turbines and Power 126, no. 2 (April 1, 2004): 271–75. http://dx.doi.org/10.1115/1.1473152.
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In this work, the application of Helmholtz resonators for damping low-frequency pulsations in gas turbine combustion chambers is discussed. We present a nonlinear model for predicting the acoustic response of resonators including the effect of purging air. Atmospheric experiments are used to validate the model, which is employed to design a resonator arrangement for damping low-frequency pulsations in an ALSTOM GT11N2 gas turbine. The predicted damper impedances are used as the boundary condition in the three-dimensional analysis of the combustion chamber. The suggested arrangement leads to a significant extension of the low-pulsation operating regime of the engine.
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Skiba, D. V., D. A. Maksimov, R. S. Kashapov, and T. S. Kharisov. "Specific features of pressure pulsation control in combustion chambers of land based gas turbine units." VESTNIK of Samara University. Aerospace and Mechanical Engineering 20, no. 4 (January 19, 2022): 40–51. http://dx.doi.org/10.18287/2541-7533-2021-20-4-40-51.
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LLC SPC Teplofizika, developing low-emission combustion chambers with premixing of fuel for ground application gas turbine installations, investigates the problems associated with the occurrence of pressure pulsations in the combustion chambers, as well as with the methods of their registration and measurement. To date, there is no unified method for assessing and calculating the amplitude-frequency characteristics of these pulsations and their measurement in general. This article is based on many years of experience in measuring and recording pressure pulsations under the conditions of a test bench and operation. Methods for evaluating and accumulating measurement results are presented, criteria for determining the average frequency and amplitude of oscillations are developed, reproducible in the course of experiments and during full-scale measurements. To detect vibrating combustion, an additional criterion of coherence of vibrations is also used with the aid of the entropy coefficient. As a result of the computational and experimental study, we find that the pulsation pressure in the volume of the combustion chamber does not allow the use of probes for measuring pressure pulsations in the air volume of the combustion chamber to reliably prevent the occurrence of vibrating combustion during its operation.
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Serbin, Serhiy, Badri Diasamidze, and Marek Dzida. "Investigations of the Working Process in a Dual-Fuel Low-Emission Combustion Chamber for an FPSO Gas Turbine Engine." Polish Maritime Research 27, no. 3 (September 1, 2020): 89–99. http://dx.doi.org/10.2478/pomr-2020-0050.
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AbstractThis investigation is devoted to an analysis of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. The low-emission gas turbine combustion chamber with partial pre-mixing of fuel and air inside the outer and inner radial-axial swirlers was chosen as the object of research. When modelling processes in a dual-flow low-emission gas turbine combustion chamber, a generalized method is used, based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system, taking into consideration nitrogen oxides formation. The Eddy-Dissipation-Concept model, which incorporates Arrhenius chemical kinetics in a turbulent flame, and the Discrete Phase Model describing the interfacial interaction are used in the investigation. The obtained results confirmed the possibility of organizing efficient combustion of distillate liquid fuel in a low-emission gas turbine combustion chamber operating on the principle of partial preliminary formation of a fuel-air mixture. Comparison of four methods of liquid fuel supply to the channels of radial-axial swirlers (centrifugal, axial, combined, and radial) revealed the advantages of the radial supply method, which are manifested in a decrease in the overall temperature field non-uniformity at the outlet and a decrease in nitrogen oxides emissions. The calculated concentrations of nitrogen oxides and carbon monoxide at the flame tube outlet for the radial method of fuel supply are 32 and 9.1 ppm, respectively. The results can be useful for further modification and improvement of the characteristics of dual-fuel gas turbine combustion chambers operating with both gaseous and liquid fuels.
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Nakata, T., M. Sato, T. Ninomiya, and T. Hasegawa. "A Study on Low NOx Combustion in LBG-Fueled 1500°C-Class Gas Turbine." Journal of Engineering for Gas Turbines and Power 118, no. 3 (July 1, 1996): 534–40. http://dx.doi.org/10.1115/1.2816680.
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Developing integrated coal gasification combined-cycle systems ensures cost-effective and environmentally sound options for supplying future power generation needs. The reduction of NOx emissions and increasing the inlet temperature of gas turbines are the most significant issues in gas turbine development in Integrated Coal Gasification Combined Cycle (IGCC) power generation systems. The coal gasified fuel, which is produced in a coal gasifier of an air-blown entrained-flow type has a calorific value as low as 1/10 of natural gas. Furthermore, the fuel gas contains ammonia when a gas cleaning system is a hot type, and ammonia will be converted to nitrogen oxides in the combustion process of a gas turbine. This study is performed in a 1500°C-class gas turbine combustor firing low-Btu coal-gasified fuel in IGCC systems. An advanced rich-lean combustor of 150-MW class gas turbine was designed to hold stable combustion burning low-Btu gas and to reduce fuel NOx emissions from the ammonia in the fuel. The main fuel and the combustion air are supplied into a fuel-rich combustion chamber with strong swirl flow and make fuel-rich flame to decompose ammonia into intermediate reactants such as NHi and HCN. The secondary air is mixed with primary combustion gas dilatorily to suppress the oxidization of ammonia reactants in fuel-lean combustion chamber and to promote a reducing process to nitrogen. By testing under atmospheric pressure conditions, the authors have obtained a very significant result through investigating the effect of combustor exit gas temperature on combustion characteristics. Since we have ascertained the excellent performance of the tested combustor through our extensive investigation, we wish to report on the results.
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Shilova, Alyona. "GAS DYNAMICS OF STABLE COMBUSTION IN THE COMBUSTION CHAMBER OF A GTP WITH EXTERNAL HEATED COMPONENTS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 65 (2021): 92–104. http://dx.doi.org/10.15593/2224-9982/2021.65.10.
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The relevance of the study is due to the need to organize stable low-emission low-temperature combustion of a lean mixture in a single-zone uncooled combustion chamber, which is an integral part of a micro-gas turbine power plant. The stable position of the flame front in combustion chambers of this type mainly depends on the ratio between the average flow rate of the combustible-air mixture and the rate of turbulent combustion. This ratio depends on many factors, the main of which are the pressure and temperature of the components supply, the excess air ratio, the pulsating speed of the gas flow and autoturbulization of the flame, the consumption of the combustible-air mixture. In this work, we investigate the effect of external heating of the components on the expansion of the lower combustion limit and on the stable position of the flame front. The aim of the study is to obtain areas of breakthrough, stable position and flame blowout when organizing low-temperature lean combustion with large values of the excess air ratio; determination of the ranges of relative flow rate, at which a stable position of the flame front is observed, using experimental data and the results of numerical modeling; development of recommendations for determining the geometric appearance of a single-zone uncooled chamber of a micro-gas turbine power plant in the presence of air and fuel gas recuperators. As a result, the dependences of the normal combustion rate on the excess air ratio were obtained taking into account the lower combustion limit, the relationship between the average flow rate and the turbulent combustion rate in various combus-tion modes, and ranges for the relative flow rate in the region of low-temperature stable combustion. Based on the developed gas-dynamic model, the geometric and gas-dynamic parameters and characteristics of turbulent combustion in the flow in the combustion chambers of micro-gas turbine power plants with a capacity of 100 and 300 kW with external heating of air and fuel gas using a turbocompressor with a compression ratio of 3.0 are determined and analyzed.
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Seume, J. R., N. Vortmeyer, W. Krause, J. Hermann, C. C. Hantschk, P. Zangl, S. Gleis, D. Vortmeyer, and A. Orthmann. "Application of Active Combustion Instability Control to a Heavy Duty Gas Turbine." Journal of Engineering for Gas Turbines and Power 120, no. 4 (October 1, 1998): 721–26. http://dx.doi.org/10.1115/1.2818459.
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During the prototype shop tests, the Model V84.3A ring combustor gas turbine unexpectedly exhibited a noticeable “humming” caused by self-excited flame vibrations in the combustion chamber for certain operating conditions. The amplitudes of the pressure fluctuations in the combustor were unusually high when compared to the previous experience with silo combustor machines. As part of the optimization program, the humming was investigated and analyzed. To date, combustion instabilities in real, complex combustors cannot be predicted analytically during the design phase. Therefore, and as a preventive measure against future surprises by “humming,” a feedback system was developed which counteracts combustion instabilities by modulation of the fuel flow rate with rapid valves (active instability control, AIC). The AIC achieved a reduction of combustion-induced pressure amplitudes by 86 percent. The Combustion instability in the Model V84.3A gas turbine was eliminated by changes of the combustor design. Therefore, the AIC is not required for the operation of customer gas turbines.
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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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MATVIIENKO, V. T., A. V. DOLOGLONYAN, and V. A. OCHERETYANYI. "FLEXIBLE COGENERATION TECHNOLOGIES BASED ON GAS TURBINE ENGINES WITH REHEATING OF GAS BEFORE THE POWER TURBINE." Fundamental and Applied Problems of Engineering and Technology, no. 1 (2021): 14–19. http://dx.doi.org/10.33979/2073-7408-2021-345-1-14-19.
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Presents results of a study of the cogeneration gas turbine with reheating of gas before power turbine and turbo-compressor utilizer (TCU). It is shown that the use of an overexpansion turbine in the composition of TCU with reheating of gas increases the specific power by more than 1.5 times, while the efficiency increases by 10...15%. By controlling the temperature of the gas behind the combustion chambers in variable modes, the energy flows produced by the cogeneration gas-turbine are controlled.
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Semenikhin, A. S., D. V. Idrisov, I. V. Chechet, S. G. Matveev, and S. V. Lukachev. "Kinetic model and kerosene surrogate for calculating gas turbine engine emission of carcinogenic hydrocarbons." VESTNIK of Samara University. Aerospace and Mechanical Engineering 21, no. 3 (November 18, 2022): 58–68. http://dx.doi.org/10.18287/2541-7533-2022-21-3-58-68.
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To calculate the emission of carcinogenic polycyclic aromatic hydrocarbons by the combustion chambers of aircraft gas turbine engines, the A17 kinetic model has been developed, characterized by new blocks of elementary chemical reactions of hydrocarbon compounds oxidation and synthesis of polycyclic aromatic hydrocarbons. The results of model validation showed satisfactory agreement with the experimental data and the possibility of applying the model to describe combustion processes in gas turbine engine combustion chambers. A review and numerical study was carried out for 14 surrogates (model fuels) of aviation kerosene, the combustion of which can be described using the A17 model. Simulation of stabilized flame of a previously prepared mixture showed the effectiveness of Drexel, Liu, su4, UM1 surrogates, the predictions for which agree satisfactorily with the experimental data and provide the expected levels of concentration of polycyclic aromatic hydrocarbons. The calculations show the dependence of the concentration of the most carcinogenic polycyclic aromatic hydrocarbon benzo(a)pyrene, and the ratio of the main combustion products CO2/H2O on the molar mass of the fuel. For the experimentally determined value of the molar mass of kerosene TS-1, the smallest deviation (up to 0.25%) is demonstrated by the su4 and UM1 surrogates. Due to the best predictive capability for the ignition delay time, normal flame propagation speed, pyrolysis and combustion products, the su4 and UM1 surrogates can be chosen to calculate the emission of carcinogenic polycyclic aromatic hydrocarbons from aircraft gas turbine engine combustion chambers.
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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.
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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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Aleksandrov, Y. B., T. D. Nguyen, and B. G. Mingazov. "Design and development of combustion chambers for gas turbine engines based on calculations of various levels of complexity." VESTNIK of Samara University. Aerospace and Mechanical Engineering 20, no. 3 (December 1, 2021): 7–23. http://dx.doi.org/10.18287/2541-7533-2021-20-3-7-23.
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The article proposes a method for designing combustion chambers for gas turbine engines based on a combination of the use of calculations in a one-dimensional and three-dimensional formulation of the problem. This technique allows you to quickly design at the initial stage of creating and development of the existing combustion chambers using simplified calculation algorithms. At the final stage, detailed calculations are carried out using three-dimensional numerical calculations. The method includes hydraulic calculations, on the basis of which the distribution of the air flow passing through the main elements of the combustion chamber is determined. Then, the mixing of the gas flow downstream of the flame tube head and the air passing through the holes in the flame tube is determined. The mixing quality determines the distribution of local mixture compositions along the length of the flame tube. The calculation of the combustion process is carried out with the determination of the combustion efficiency, temperature, concentrations of harmful substances and other parameters. The proposed method is tested drawing on the example of a combustion chamber of the cannular type. The results of numerical calculations, experimental data and values obtained using the proposed method for various operating modes of the engine are compared.
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Yellu Kumar, K. R., Adnan Qayoum, Shahid Saleem, and Faisal Qayoum. "Effusion Cooling In Gas Turbine Combustion Chambers - A Comprehensive Review." IOP Conference Series: Materials Science and Engineering 804 (June 17, 2020): 012003. http://dx.doi.org/10.1088/1757-899x/804/1/012003.
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Cirigliano, Daniele, Felix Grimm, Peter Kutne, and Manfred Aigner. "Oxidation-Induced Damage Modeling in Micro Gas-Turbine Combustion Chambers." Procedia Structural Integrity 42 (2022): 1728–35. http://dx.doi.org/10.1016/j.prostr.2022.12.219.
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Maspanov, Sergej, Igor Bogov, Alexander Smirnov, Svetlana Martynenko, and Vladimir Sukhanov. "Analysis of Gas-Turbine Type GT-009 M Low-Toxic Combustion Chamber with Impact Cooling of the Burner Pipe Based on Combustion of Preliminarily Prepared Depleted Air–Fuel Mixture." Energies 15, no. 3 (January 19, 2022): 707. http://dx.doi.org/10.3390/en15030707.
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This article analyzes the mechanism of formation of the main components of harmful emissions characteristic of combustion chambers operating on conventional hydrocarbon fuels. The method of combustion of a preliminarily prepared depleted air–fuel mixture was chosen as the object of the study. This method of suppressing harmful emissions was implemented in the design of a low-toxic combustion chamber developed as applied to the GT-009 M type unit with impact cooling of the burner pipe and provides for stabilization of the main kinetic flame by means of a diffusion-kinetic and a standby burner device. The results of the calculations performed with regard to the operating conditions of the low-toxic combustion chamber at the nominal load of GT-009 M allow us to conclude that the practical use of combustion of a depleted, preprepared, fuel–air mixture in combination with diffusion-kinetic stabilization of combustion is promising. The topic of this article is related to the problem of ecological improvement of gas turbine unit combustion chambers, which determines its utmost importance and relevance.
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Serbin, Serhiy, Badri Diasamidze, Viktor Gorbov, and Jerzy Kowalski. "Investigations of the Emission Characteristics of a Dual-Fuel Gas Turbine Combustion Chamber Operating Simultaneously on Liquid and Gaseous Fuels." Polish Maritime Research 28, no. 2 (June 1, 2021): 85–95. http://dx.doi.org/10.2478/pomr-2021-0025.
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Abstract This study is dedicated to investigations of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. As the object of the research, a low-emission gas turbine combustion chamber with partial premixing of fuel and air inside the outer and inner radial-axial swirls was chosen. The method of the research is based on the numerical solution of the system of differential equations which represent the physical process of mass and energy conservation and transformations and species transport for a multi-component chemically reactive turbulent system, considering nitrogen oxides formation and a discrete ordinates model of radiation. The chemistry kinetics is presented by the 6-step mechanism of combustion. Seven fuel supply operating modes, varying from 100% gaseous fuel to 100% liquid fuel, have been analysed. This analysis has revealed the possibility of the application of computational fluid dynamics for problems of dual-fuel combustion chambers for the design of a floating vessel’s gas turbine. Moreover, the study has shown the possibility of working in different transitional gaseous and liquid fuel supply modes, as they satisfy modern ecological requirements. The dependencies of the averaged temperature, NO, and CO concentrations along the length of the low-emission gas turbine combustion chamber for different cases of fuel supply are presented. Depending on the different operating modes, the calculated emission of nitrogen oxides NO and carbon monoxide CO at the outlet cross-section of a flame tube are different, but, they lie in the ranges of 31‒50 and 23‒24 mg/nm3 on the peak of 100% liquid fuel supply mode. At operating modes where a gaseous fuel supply prevails, nitrogen oxide NO and carbon monoxide CO emissions lie in the ranges of 1.2‒4.0 and 0.04‒18 mg/nm3 respectively.
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Komarov, I. I., D. M. Kharlamova, A. N. Vegera, and V. Y. Naumov. "Study on effect CO2 diluent on fuel cоmbustion in methane-oxygen combustion chambers." Vestnik IGEU, no. 2 (April 30, 2021): 14–22. http://dx.doi.org/10.17588/2072-2672.2021.2.014-022.
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Studying closed gas turbine cycles on supercritical carbon dioxide is currently a promising issue in the development of power energy sector in terms of increasing energy efficiency and minimizing greenhouse gas emissions into the atmosphere. Combustion of methane with oxygen in the combustion chamber occurs not in the nitrogen environment, but in the environment of carbon dioxide, that is the working fluid of the cycle, which is an inhibitor of chemical reactions. A large mass content of such a diluent of the reaction mixture in the volume of the chamber leads to the risks of significant chemical underburning, efficiency decrease of the combustion chamber and the cycle as a whole. The aim of the research is to study the kinetic parameters of the combustion of methane with oxygen in a supercritical CO2 diluent medium to ensure reliable and stable combustion of fuel by assessing the degree of the inhibitory effect of CO2 and determining its permissible amount in the active combustion zone of the combustion chamber. The research method is a numerical simulation of turbulent-kinetic processes of methane combustion in the combustion chamber using the reduced methane combustion mechanism. Ansys Fluent software package has been used. The authers have studied the impact of CO2 diluent on fuel cоmbustion in methane-oxygen combustion chambers. It is found that the combustor flame stabilization takes place if the content of СО2 diluent supplied to the mixture with oxidizer is 0,46–0,5 of mass fraction; additional СО2 diluent forms local low temperature zones which slow down the combustion process. When this happens, adding cooling СО2 into the flame stabilization zone should be eliminated. The study has found that no more than 20 % of the total carbon dioxide content should be supplied to the combustion chamber; to stabilize the flame and reduce its length, it is necessary to install blades to swirl the fuel and oxidizer mixed with CO2 at the inlet of the combustion chamber; CO2 supply for cooling should be carried out not less than 130 mm away from the burner mouth.
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Козел, Дмитрий Викторович. "Выбор геометрических характеристик фронтового устройства и длины камеры сгорания прямоточного типа." Aerospace technic and technology, no. 4sup2 (August 27, 2021): 19–28. http://dx.doi.org/10.32620/aktt.2021.4sup2.03.
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A method has been developed for selecting the geometric characteristics of the front and the length of the direct-flow combustion chamber. Afterburner combustion chambers are of the ramjet type and are used for a short-term increase in the thrust of a gas turbine engine during takeoff, for overcoming the sound barrier by an aircraft and for flying at supersonic speed, and for making maneuvers. As part of ramjet engines, ramjet combustion chambers are used as the main combustion chambers in which the process of fuel combustion and heat supply to the working fluid is ensured. The developed method for selecting the geometric characteristics consists in optimizing the main operating characteristics of the combustion chamber. Mathematical models are proposed for describing the dependence of the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber against the parameters of the flow at the inlet to the combustion chamber and the geometric characteristics of the front device and the length of the combustion chamber. The analysis of the dependences of the combustion chamber working characteristics on the geometric characteristics of the front-line device and its length is carried out. As a result of the analysis of mathematical models, a list of the main geometric characteristics of the front device was determined, on which the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber depend. Optimization parameters, optimization criterion and limits for solving the optimization problem are determined. As an implementation of the optimization method, it is proposed to use a diagram of the combustion chamber performance in the coordinates of the optimization parameters. The developed method makes it possible to ensure the optimal basic operating characteristics of the combustion chamber - total pressure loss, combustion efficiency and combustion stability limits.
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Mikielewicz, Kosowski, Tucki, Piwowarski, Stępień, Orynycz, and Włodarski. "Gas Turbine Cycle with External Combustion Chamber for Prosumer and Distributed Energy Systems." Energies 12, no. 18 (September 11, 2019): 3501. http://dx.doi.org/10.3390/en12183501.
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The use of various biofuels, usually of relatively small Lower Heating Value (LHV), affects the gas turbine efficiency. The present paper shows that applying the proposed air by-pass system of the combustor at the turbine exit causes tan increase of efficiency of the turbine cycle increased by a few points. This solution appears very promising also in combined gas/steam turbine power plants. The comparison of a turbine set operating according to an open cycle with partial bypassing of external combustion chamber at the turbine exit (a new solution) and, for comparison, a turbine set operating according to an open cycle with a regenerator. The calculations were carried out for different fuels: gas from biomass gasification (LHV = 4.4 MJ/kg), biogas (LHV = 17.5 MJ/kg) and methane (LHV = 50 MJ/kg). It is demonstrated that analyzed solution enables construction of several kW power microturbines that might be used on a local scale. Such turbines, operated by prosumer’s type of organizations may change the efficiency of electricity generation on a country-wide scale evidently contributing to the sustainability of power generation, as well as the economy as a whole.
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Shaikh, Faisal, and Budimir Rosic. "Unsteady phenomena at the combustor-turbine interface." Journal of the Global Power and Propulsion Society 5 (November 23, 2021): 202–15. http://dx.doi.org/10.33737/jgpps/143042.
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The combustor-turbine interface in a gas turbine is characterised by complex, highly unsteady flows. In a combined experimental and large eddy simulation (LES) study including realistic combustor geometry, the standard model of secondary flows in the nozzle guide vanes (NGV) is found to be oversimplified. A swirl core is created in the combustion chamber which convects into the first vane passages. Four main consequences of this are identified: variation in vane loading; unsteady heat transfer on vane surfaces; unsteadiness at the leading edge horseshoe vortex, and variation in the position of the passage vortex. These phenomena occur at relatively low frequencies, from 50–300 Hz. It seems likely that these unsteady phenomena result in non-optimal film cooling, and that by reducing unsteadiness designs with greater cooling efficiency could be achieved. Measurements were performed in a high speed test facility modelling a large industrial gas turbine with can combustors, including nozzle guide vanes and combustion chambers. Vane surfaces and endwalls of a nozzle guide vane were instrumented with 384 high speed thin film heat flux gauges, to measure unsteady heat transfer. The high resolution of measurements was such to allow direct visualisation in time of large scale turbulent structures over the endwalls and vane surfaces. A matching LES simulation was carried out in a domain matching experimental conditions including upstream swirl generators and transition duct. Data reduction allowed time-varying LES data to be recorded for several cycles of the unsteady phenomena observed. The combination of LES and experimental data allows physical explanation and visualisation of flow events.
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Glavan, Ivica, Igor Poljak, and Mate Kosor. "A gas turbine combustion chamber modeling by physical model." Pomorstvo 35, no. 1 (June 30, 2021): 30–35. http://dx.doi.org/10.31217/p.35.1.4.
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The validity of the gas turbine unit model largely depends on the accuracy of the flue gas temperature value calculation at the gas turbine inlet (TIT). This temperature is determined by the maximum combustion temperature. In variable running mode, the temperature value is regulated by changing the ratio of air and fuel at the inlet to the combustion chamber. The paper presents a model of a gas turbine combustion chamber using Modelica, an object-oriented language for modeling complex physical systems with the aim of determining the temperature of combustion flue gases, specific heat capacity, enthalpy, and flue gas composition at different gas turbine loads.
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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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Neidel, Andreas, Erhan Cagliyan, Anne Jahnke, Susanne Riesenbeck, Thomas Ullrich, and Sebastian Wallich. "TMF Cracking in Metallic Heat Shields of Gas Turbine Combustion Chambers." Materials Testing 54, no. 3 (March 2012): 153–56. http://dx.doi.org/10.3139/120.110308.
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Lamarque, N., and T. Poinsot. "Boundary Conditions for Acoustic Eigenmodes Computation in Gas turbine Combustion Chambers." AIAA Journal 46, no. 9 (September 2008): 2282–92. http://dx.doi.org/10.2514/1.35388.
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Gicquel, L. Y. M., G. Staffelbach, and T. Poinsot. "Large Eddy Simulations of gaseous flames in gas turbine combustion chambers." Progress in Energy and Combustion Science 38, no. 6 (December 2012): 782–817. http://dx.doi.org/10.1016/j.pecs.2012.04.004.
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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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Stepanova, E. L., and P. V. Zharkov. "A study of the dependence between fuel consumption of a heat gas turbine and variation of heat loading of regional consumers having various climatic conditions taking into account determination of structural characteristics of heat exchanging equipment for grid water heating." Proceedings of Irkutsk State Technical University 25, no. 4 (September 1, 2021): 478–87. http://dx.doi.org/10.21285/1814-3520-2021-4-478-487.
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The aim was to optimize the dependence between fuel consumption and heat loading of regional consumers varied due to climatic conditions, taking into account the determination of structural characteristics of heat exchanging equipment for grid water heating in a heat gas turbine. A heat gas turbine comprising two fuel combustion chambers, a waste-heat boiler and a contact heat exchanger to heat makeup grid water was investigated. Scheme and parametric optimization studies were carried out using a mathematic model of a gas turbine created using a software and hardware system developed at the Department of Heat Power Systems of the Melentiev Energy Systems Institute, Siberian Branch of the Russian Academy of Sciences. Th turbine operating conditions differing in heat loads in four suggested operating regions were studied. It was found that an increase in fuel consumption in the second combustion chamber was 29%– 84% compared to that in the first combustion chamber. This rise was recorded when the turbine heat loading was increasing in the considered regions. Data analysis of the scheme and parametric optimization studies showed that, for operating conditions with a higher heat loading, it seems reasonable to ensure the maximum possible heating of makeup grid water as the loading rises. It is also recommended to slightly increase the heat surface area of the makeup grid water heater whose structural materials are less expensive than in a waste-heat boiler. It was shown that the suggested technical solution slightly increases specific capital investments while fully providing electrical and heat power to consumers. The obtained results can be used to select optimal technical solutions ensuring competitiveness in the operation of a heat gas turbine in regions with various climatic characteristics.
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Kholmyanskii, I. A. "Fuel Combustion in Combustion Chambers of a Gas–Turbine Engine with a Rotating Injector." Combustion, Explosion, and Shock Waves 40, no. 4 (July 2004): 419–24. http://dx.doi.org/10.1023/b:cesw.0000033564.60113.b7.
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Godin, T., S. Harvey, and P. Stouffs. "High-Temperature Reactive Flow of Combustion Gases in an Expansion Turbine." Journal of Turbomachinery 119, no. 3 (July 1, 1997): 554–61. http://dx.doi.org/10.1115/1.2841157.
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The analysis of the chemical behavior of the working fluid in gas turbines is usually restricted to the combustion chamber sections. However, the current trend toward higher Turbine Inlet Temperatures (TIT), in order to achieve improved thermal efficiency, will invalidate the assumption of frozen composition of the gases in the first stages of the expansion process. It will become necessary to consider the recombination reactions of the dissociated species, resulting in heat release during expansion. In order to quantify the influence of this reactivity on the performance of high TIT gas turbines, a one-dimensional model of the reactive flow has been developed. Preliminary results were reported in a previous paper. The authors concluded that, in the case of expansion of combustion gases in a subsonic static uncurved distributor nozzle, the residual reactivity must be taken into account above a temperature threshold of around 2000 K. The present study extends these results by investigating the reactive flow in a complete multistage turbine set, including a transonic first-stage nozzle. A key result of this study is that heat release during the expansion process itself will be considerable in future high-temperature gas turbines, and this will have significant implications for turbine design techniques. Furthermore, we show that, at the turbine exit, the fractions of NO and CO are very different from the values computed at the combustor outlet. In particular, NO production in the early part of the expansion process is very high. Finally, the effects of temperature fluctuations at the turbine inlet are considered. We show that residual chemical reactivity affects the expansion characteristics in gas turbines with TITs comparable to those attained by modern high-performance machines.
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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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Akbari, N., and N. S. Mehdizadeh. "Thermo-Acoustic Instability Simulation in Gas Turbine." Journal of Mechanics 25, no. 4 (December 2009): 433–40. http://dx.doi.org/10.1017/s1727719100002914.
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ABSTRACTThe main aims of this research are, at first, combustion instability study based on equivalence ratio oscillation, and, secondly, investigation various frequency modes of combustion instability, taking combustion chamber geometry into account. Considering the configuration of the simulated combustion chamber, excitation probability of the longitudinal modes is higher than that of transversal modes. The reason of this fact is that the resonance frequency values of the longitudinal modes are less than those of transversal modes. So, the most important frequency mode, during combustion instability, is the first longitudinal mode. In this paper thermo-acoustic instability model is utilized for pre-mixed gas turbines combustion chamber, founded on equivalence ratio oscillation. For this purpose Lieuwen method is developed in order to attain the phase difference between pressure and heat release oscillations. Results concluded from combustion instability simulation for the first longitudinal mode, considering its importance, are compared with experimental data and good agreement is observed.
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Marin Begović. "MAINTAINING DECLARED PERFORMANCE IN GAS TURBINES DURING INCREASED AMBIENT TEMPERATURES." Journal of Energy - Energija 58, no. 2 (September 16, 2022): 192–207. http://dx.doi.org/10.37798/2009582298.
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The classical gas turbine process is characterised by air compression from its surroundings, heating fuel in the combustion chambers, hence causing the created flue gases to expand in the turbine and thus induce mechanical action. The performance of gas turbine depends on anything that affects the airflow density and/or mass at the compressor inlet. The most obvious changes in gas turbine performance is a reduction in power and an increase in specific fuel consumption following an increase in the ambient temperature, resulting in significant deviations of the guaranteed (and achieved) values at ISO conditions. In cooling air at the compressor inlet at increased ambient temperatures, an increase in the mass flow and compression ratio is achieved, thus preventing a reduction in power and an increase in specific fuel consumption. When using gas turbines in combined cycle cogeneration power plants for the production of electrical and thermal power, increasing mass flow through gas turbines leads to an increase in power transferred by the flue gases to the turbine exhaust, and which in the waste heat recovery boiler at the combined cycle plant transfers to the steam turbine cycle. Consequently, the effect at the combined cycle plant is a more significant reduction in specific fuel consumption. The work has used the example of the GE-PG610FA turbine to show the dependency on surrounding climatic conditions, and the manner in which this dependency can be reduced or removed.
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Braun-Unkhoff, M., E. Goos, T. Kathrotia, T. Kick, C. Naumann, N. Slavinskaya, and U. Riedel. "The Importance of Detailed Chemical Mechanisms in Gas Turbine Combustion Simulations." Eurasian Chemico-Technological Journal 16, no. 2-3 (April 8, 2014): 179. http://dx.doi.org/10.18321/ectj182.
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<p>This paper – in memory of Jürgen Warnatz – summarizes selected recent papers of the Chemical Kinetics Group at the German Aerospace Center in Stuttgart. It shows the need for detailed chemical reaction mechanisms to understand practical combustion systems. A comprehensive description of combustion processes based on detailed mechanisms is especially important in the design of new gas turbine combustion chambers and in the optimization of existing ones to improve efficiency and to reduce pollutant emissions, with fuel-flexibility and load-flexibility ever becoming more important. Different aspects of combustion processes where detailed reaction mechanisms provide useful insights will be covered in this paper: Fuels (alternative jet fuels, biomass based fuels), pollutants (soot), diagnostics (chemiluminescence), and thermochemistry. Furthermore, the underlying thermodynamics inevitably connected with detailed reaction schemes will be addressed. Exemplified results will be presented clearly demonstrating the predictive capabilities of detailed reaction mechanisms to be explored in computational fluid dynamic simulations to further optimize technical combustion systems.</p>
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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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Griffin, Timothy, Sven Gunnar Sundkvist, Knut A˚sen, and Tor Bruun. "Advanced Zero Emissions Gas Turbine Power Plant." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 81–85. http://dx.doi.org/10.1115/1.1806837.
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The AZEP “advanced zero emissions power plant” project addresses the development of a novel “zero emissions,” gas turbine-based, power generation process to reduce local and global CO2 emissions in the most cost-effective way. Process calculations indicate that the AZEP concept will result only in a loss of about 4% points in efficiency including the pressurization of CO2 to 100 bar, as compared to approximately 10% loss using conventional tail-end CO2 capture methods. Additionally, the concept allows the use of air-based gas turbine equipment and, thus, eliminates the need for expensive development of new turbomachinery. The key to achieving these targets is the development of an integrated MCM-reactor in which (a) O2 is separated from air by use of a mixed-conductive membrane (MCM), (b) combustion of natural gas occurs in an N2-free environment, and (c) the heat of combustion is transferred to the oxygen-depleted air by a high temperature heat exchanger. This MCM-reactor replaces the combustion chamber in a standard gas turbine power plant. The cost of removing CO2 from the combustion exhaust gas is significantly reduced, since this contains only CO2 and water vapor. The initial project phase is focused on the research and development of the major components of the MCM-reactor (air separation membrane, combustor, and high temperature heat exchanger), the combination of these components into an integrated reactor, and subsequent scale-up for future integration in a gas turbine. Within the AZEP process combustion is carried out in a nearly stoichiometric natural gas/O2 mixture heavily diluted in CO2 and water vapor. The influence of this high exhaust gas dilution on the stability of natural gas combustion has been investigated, using lean-premix combustion technologies. Experiments have been performed both at atmospheric and high pressures (up to 15 bar), simulating the conditions found in the AZEP process. Preliminary tests have been performed on MCM modules under simulated gas turbine conditions. Additionally, preliminary reactor designs, incorporating MCM, heat exchanger, and combustor, have been made, based on the results of initial component testing. Techno-economic process calculations have been performed indicating the advantages of the AZEP process as compared to other proposed CO2-free gas turbine processes.
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Spadaccini, C. M., J. Peck, and I. A. Waitz. "Catalytic Combustion Systems for Microscale Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 129, no. 1 (September 28, 2005): 49–60. http://dx.doi.org/10.1115/1.2204980.
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As part of an ongoing effort to develop a microscale gas turbine engine for power generation and micropropulsion applications, this paper presents the design, modeling, and experimental assessment of a catalytic combustion system. Previous work has indicated that homogenous gas-phase microcombustors are severely limited by chemical reaction timescales. Storable hydrocarbon fuels, such as propane, have been shown to blow out well below the desired mass flow rate per unit volume. Heterogeneous catalytic combustion has been identified as a possible improvement. Surface catalysis can increase hydrocarbon-air reaction rates, improve ignition characteristics, and broaden stability limits. Several radial inflow combustors were micromachined from silicon wafers using deep reactive ion etching and aligned fusion wafer bonding. The 191mm3 combustion chambers were filled with platinum-coated foam materials of various porosity and surface area. For near stoichiometric propane-air mixtures, exit gas temperatures of 1100K were achieved at mass flow rates in excess of 0.35g∕s. This corresponds to a power density of ∼1200MW∕m3; an 8.5-fold increase over the maximum power density achieved for gas-phase propane-air combustion in a similar geometry. Low-order models, including time-scale analyses and a one-dimensional steady-state plug-flow reactor model, were developed to elucidate the underlying physics and to identify important design parameters. High power density catalytic microcombustors were found to be limited by the diffusion of fuel species to the active surface, while substrate porosity and surface area-to-volume ratio were the dominant design variables.
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Crosa, G., F. Pittaluga, A. Trucco, F. Beltrami, A. Torelli, and F. Traverso. "Heavy-Duty Gas Turbine Plant Aerothermodynamic Simulation Using Simulink." Journal of Engineering for Gas Turbines and Power 120, no. 3 (July 1, 1998): 550–56. http://dx.doi.org/10.1115/1.2818182.
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This paper presents a physical simulator for predicting the off-design and dynamic behavior of a single shaft heavy-duty gas turbine plant, suitable for gas-steam combined cycles. The mathematical model, which is nonlinear and based on the lumped parameter approach, is described by a set of first-order differential and algebraic equations. The plant components are described adding to their steady-state characteristics the dynamic equations of mass, momentum, and energy balances. The state variables are mass flow rates, static pressures, static temperatures of the fluid, wall temperatures, and shaft rotational speed. The analysis has been applied to a 65 MW heavy-duty gas turbine plant with two off-board, silo-type combustion chambers. To model the compressor, equipped with variable inlet guide vanes, a subdivision into five partial compressors is adopted, in serial arrangement, separated by dynamic blocks. The turbine is described using a one-dimensional, row-by-row mathematical model, that takes into account both the air bleed cooling effect and the mass storage among the stages. The simulation model considers also the air bleed transformations from the compressor down to the turbine. Both combustion chambers have been modeled utilizing a sequence of several sub-volumes, to simulate primary and secondary zones in presence of three hybrid burners. A code has been created in Simulink environment. Some dynamic responses of the simulated plant, equipped with a proportional-integral speed regulator, are presented.
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Wang, Kefu, Feng Li, Tao Zhou, and Yiqun Ao. "Numerical Study of Combustion and Emission Characteristics for Hydrogen Mixed Fuel in the Methane-Fueled Gas Turbine Combustor." Aerospace 10, no. 1 (January 10, 2023): 72. http://dx.doi.org/10.3390/aerospace10010072.
Full textAbstract:
The aeroderivative gas turbine is widely used as it demonstrates many advantages. Adding hydrogen to natural gas fuels can improve the performance of combustion. Following this, the effects of hydrogen enrichment on combustion characteristics were analyzed in an aeroderivative gas turbine combustor using CFD simulations. The numerical model was validated with experimental results. The conditions of the constant mass flow rate and the constant energy input were studied. The results indicate that adding hydrogen reduced the fuel residues significantly (fuel mass at the combustion chamber outlet was reduced up to 60.9%). In addition, the discharge of C2H2 and other pollutants was reduced. Increasing the volume fraction of hydrogen in the fuel also reduced CO emissions at the constant energy input while increasing CO emissions at the constant fuel mass flow rate. An excess in the volume fraction of added hydrogen changed the combustion mode in the combustion chamber, resulting in fuel-rich combustion (at constant mass flow rate) and diffusion combustion (at constant input power). Hydrogen addition increased the pattern factor and NOx emissions at the outlet of the combustion chamber.